Airworthiness Directives; Bombardier, Inc. Airplanes, 23202-23206 [2016-08960]
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Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
(2) Replace the current electrical cable with
the new standard one in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–92–1052, dated
December 5, 2007. During the replacement,
ensure that the anti-chafing protection
specified in Airbus Service Bulletin A320–
92–1049, as required by paragraph (h)(1) of
this AD, remains in place.
(i) Additional Modification
For airplanes on which the installation
specified in Airbus Service Bulletin A320–
24–1062, Revision 05, dated June 27, 2002,
has been done: Within 60 months after the
effective date of this AD, install insulators
and cable ties, in accordance with
‘‘Modification—Additional Work (Introduced
at Revision No. 06)’’ of the Accomplishment
Instructions of Airbus Service Bulletin A320–
24–1062, Revision 07, dated November 28,
2011.
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(j) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraphs (g) and (i) of
this AD, if those actions were performed
before the effective date of this AD using
Airbus Service Bulletin A320–24–1062,
Revision 06, dated June 26, 2007, which is
not incorporated by reference in this AD.
(2) This paragraph provides credit for
actions required by paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–92–1049, dated July 23, 2007,
which is not incorporated by reference in this
AD.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, 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, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
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the DOA, the approval must include the
DOA-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0198, dated
September 5, 2014, 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–2016–5591.
(2) For service information identified in
this AD, 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@
airbus.com; Internet https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on April 4,
2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–08953 Filed 4–19–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5593; Directorate
Identifier 2015–NM–184–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2015–02–
23, for certain Bombardier, Inc. Model
CL–600–1A11 (CL–600), CL–600–2A12
(CL–601), and CL–600–2B16 (CL–601–
3A, and CL–601–3R Variants) airplanes.
AD 2015–02–23 currently requires
repetitive inspections for fractured or
incorrectly oriented fasteners on the
inboard flap hinge-box forward fittings
on both wings, and replacement of all
fasteners if necessary. The preamble to
AD 2015–02–23 explains that we
consider the requirements interim
action and are considering further
rulemaking. We now have determined
that further rulemaking is indeed
necessary, and that replacement of the
fasteners is necessary. This proposed
AD would require terminating action to
replace the fasteners on the inboard flap
SUMMARY:
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hinge-box forward fittings on both
wings. We are proposing this AD to
detect and correct incorrectly oriented
or fractured fasteners, which could
result in detachment of the flap hingebox and the flap surface, and
consequent reduced controllability of
the airplane.
DATES: We must receive comments on
this proposed AD by June 6, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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.
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–
5593; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Aerospace Engineer, Airframe
and Mechanical Systems Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7329; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
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Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–5593; Directorate Identifier
2015–NM–184–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
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Discussion
On January 20, 2015, we issued AD
2015–02–23, Amendment 39–18092 (80
FR 5670, February 3, 2015) (‘‘AD 2015–
02–23’’). AD 2015–02–23 requires
actions intended to address an unsafe
condition on certain Bombardier, Inc.
Model CL–600–1A11 (CL–600), CL–
600–2A12 (CL–601), and CL–600–2B16
(CL–601–3A, and CL–601–3R Variants)
airplanes. AD 2015–02–23 corresponds
to Canadian Emergency Airworthiness
Directive CF–2013–39R2, dated
December 12, 2014 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’). The MCAI was issued by
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada.
The preamble to AD 2015–02–23
explains that we consider the
requirements interim action and are
considering further rulemaking. We
have now determined that further
rulemaking is indeed necessary and
that, instead of continuing repetitive
inspections, replacement of the
incorrectly oriented fasteners is
necessary. This proposed AD follows
from that determination. This proposed
AD would require terminating action to
replace the fasteners on the inboard flap
hinge-box forward fittings on affected
wings.
The repetitive inspections can only
detect if a fastener head has fractured
and sheared off. For incorrectly oriented
fasteners, it is not possible to detect
whether a crack has already initiated
and propagated. The fastener fracture
speed is unpredictable due to the
variability in the quality of the hole
preparation prior to fastener installation
and whether there was any
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misalignment in the installation of the
fasteners. The failure of two fasteners
could result in the loss of the flap
attachment, causing flap asymmetry and
consequent reduced controllability of
the airplane.
We are proposing this AD to detect
and correct incorrectly oriented or
fractured fasteners, which could result
in detachment of the flap hinge-box and
the flap surface, and consequent
reduced controllability of the airplane.
Related Service Information Under 1
CFR Part 51
Bombardier has issued Alert Service
Bulletins A600–0763, Revision 02,
dated December 9, 2014, including
Appendices 1 and 2, dated September
26, 2013; and A601–0627, Revision 02,
dated December 9, 2014, including
Appendices 1 and 2, dated September
26, 2013. The service information
describes procedures for repetitive
inspections of the fasteners on the
inboard flap hinge-box forward fittings
on both wings, and replacement of
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.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type designs.
Clarification of Intent of the MCAI
Paragraph C. of Canadian Emergency
AD CF–2013–39R2, dated December 12,
2014, specifies to do the replacement on
‘‘both’’ wings. We have clarified with
TCCA that the intent of paragraph C. of
Canadian Emergency AD CF–2013–
39R2, dated December 12, 2014, is that
for airplanes on which any incorrectly
oriented fastener, and no fractured or
missing fastener, was detected, the
replacement only needs to be done on
the affected wing on which incorrectly
oriented fasteners were found but none
were found to be fractured.
The replacement of all forward and aft
fasteners, regardless of condition or
orientation, at wing station (WS) 76.50
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and WS 127.25, on the affected wings,
constitutes terminating action. Fasteners
that have cracks or fractures were
already addressed by the requirements
of AD 2015–02–13, which is restated in
this proposed AD.
Costs of Compliance
We estimate that this proposed AD
affects 120 airplanes of U.S. registry.
The actions required by AD 2015–02–
23, and retained in this proposed AD,
take about 1 work-hour per product, at
an average labor rate of $85 per workhour. Based on these figures, the
estimated cost of the actions that are
required by AD 2015–02–23 is $85 per
product.
We also estimate that it would take
about 59 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. We have
received no definitive data that would
enable us to provide cost estimates for
the parts cost. Based on these figures,
we estimate the cost of this proposed
AD on U.S. operators to be $601,800, or
$5,015 per product.
In addition, we estimate that any
necessary follow-on actions will take
about 58 work-hours and require parts
costing $753, for a cost of $5,683 per
product. We have no way of
determining the number of aircraft that
might need this action.
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all available
costs in our cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
(1) Bombardier, Inc. Model CL–600–1A11
(CL–600) airplanes, having serial numbers (S/
Ns) 1004 through 1085 inclusive.
(2) Bombardier, Inc. Model CL–600–2A12
(CL–601) airplanes, having S/Ns 3001
through 3066 inclusive.
(3) Bombardier, Inc. Model CL–600–2B16
(CL–601–3A and CL–601–3R Variants)
airplanes, having S/Ns 5001 through 5194
inclusive.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(g) Retained Inspection on Airplanes Not
Previously Inspected, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2015–02–23, with no
changes. For airplanes that have not been
inspected as required by paragraph (g) of AD
2014–03–17, as of February 18, 2015 (the
effective date of AD 2015–02–23): Within 10
flight cycles after February 18, 2015, or 100
flight cycles after March 6, 2014 (the effective
date of AD 2014–03–17), whichever occurs
first, do a detailed visual inspection for
incorrect orientation and any fractured or
missing fastener heads of each inboard flap
fastener of the hinge-box forward fitting at
wing station (WS) 76.50 and WS 127.25, on
both wings, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (g)(1) and (g)(2) of this AD.
Accomplishing the inspection required by
this paragraph terminates the requirements of
paragraph (g) of AD 2014–03–17 for the
inspected airplane only.
(1) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(2) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2015–02–23, Amendment 39–18092 (80
FR 5670, February 3, 2015), and adding
the following new AD:
■
Bombardier, Inc.: Docket No. FAA–2016–
5593; Directorate Identifier 2015–NM–
184–AD.
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(a) Comments Due Date
We must receive comments by June 6,
2016.
(b) Affected ADs
This AD replaces AD 2015–02–23,
Amendment 39–18092 (80 FR 5670, February
3, 2015) (‘‘AD 2015–02–23’’). This AD affects
AD 2014–03–17, Amendment 39–17754 (79
FR 9389, February 19, 2014) (‘‘AD 2014–03–
17’’).
(c) Applicability
This AD applies to the Bombardier, Inc.
airplanes identified in paragraphs (c)(1),
(c)(2), and (c)(3) of this AD, certificated in
any category.
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(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports of
incorrectly oriented fasteners. We are issuing
this AD to detect and correct incorrectly
oriented or fractured fasteners, which could
result in detachment of the flap hinge-box
and the flap surface, and consequent reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(h) Retained Corrective Actions for
Paragraph (g) of This AD, With Revised
Paragraph (h)(2) of This AD
(1) This paragraph restates the
requirements of paragraph (h)(1) of AD 2015–
02–23, with no changes. If, during any
inspection required by paragraph (g) of this
AD, all fasteners are found correctly oriented
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and not fractured, and no fastener heads are
missing (fasteners found intact): No further
action is required by this AD.
(2) This paragraph restates the
requirements of paragraph (h)(2) of AD 2015–
02–23, with revised references to
replacement paragraphs. If, during any
inspection required by paragraph (g) of this
AD, any fastener is found incorrectly
oriented but no fasteners are fractured or are
missing a fastener head (fasteners found
intact), repeat the inspection required by
paragraph (g) of this AD thereafter at
intervals not to exceed 10 flight cycles until
the replacements specified in paragraph
(h)(3), (k), or (n) of this AD is accomplished.
(3) This paragraph restates the
requirements of paragraph (h)(3) of AD 2015–
02–23, with no changes. If, during any
inspection required by paragraph (g) of this
AD, any fastener is found fractured or has a
missing fastener head: Before further flight,
remove and replace all forward and aft
fasteners (regardless of orientation or
condition) at WS 76.50 and WS 127.25, on
both wings, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (h)(3)(i) and (h)(3)(ii) of this AD,
except as required by paragraph (m) of this
AD. After accomplishing the replacements
required by this paragraph, no further action
is required by this AD.
(i) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(ii) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013.
(i) Retained Inspection for Airplanes
Previously Inspected and Found To Have
Incorrectly Oriented Fastener(s), With No
Changes
This paragraph restates the requirements of
paragraph (i) of AD 2015–02–23, with no
changes. For airplanes on which an
inspection required by paragraph (g) or (j) of
AD 2014–03–17, has been done as of the
effective date of this AD, and on which any
incorrectly oriented fastener was found but
no fasteners were fractured (fasteners found
intact): Except as provided by paragraph (l)
of this AD, within 10 flight cycles after
February 18, 2015 (the effective date of AD
2015–02–23), or within 100 flight cycles after
accomplishing the most recent inspection
required by AD 2014–03–17, whichever
occurs first, do a detailed visual inspection
for any fractured or missing fastener heads of
each inboard flap fastener of the hinge-box
forward fitting at WS 76.50 and WS 127.25,
on both wings. Do the inspection in
accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraphs (i)(1) and
(i)(2) of this AD. Accomplishing the
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inspection required by this paragraph
terminates the requirements of paragraphs (g)
and (j) of AD 2014–03–17 for the inspected
airplane only.
(1) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(2) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013.
(j) Retained Corrective Actions for
Paragraph (i) of This AD, With Revised
Reference to Additional, New Requirements
(1) This paragraph restates the
requirements of paragraph (j)(1) of AD 2015–
02–23, with revised reference to additional,
new requirements. If, during any inspection
required by paragraph (i) of this AD, no
fasteners are found fractured or have missing
fastener heads (fasteners are intact), repeat
the inspection required by paragraph (i) of
this AD thereafter at intervals not to exceed
10 flight cycles until the replacement
specified in paragraph (j)(2), (k), or (n) of this
AD is accomplished.
(2) This paragraph restates the
requirements of paragraph (j)(2) of AD 2015–
02–23, with no changes. If, during any
inspection required by paragraph (i) of this
AD, any fastener is found fractured or has a
missing fastener head: Before further flight,
remove and replace all forward and aft
fasteners (regardless of orientation or
condition) at WS 76.50 and WS 127.25, on
both wings, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (j)(2)(i) and (j)(2)(ii) of this AD,
except as required by paragraph (m) of this
AD. After accomplishing the replacements
required by this paragraph, no further action
is required by this AD.
(i) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(ii) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013.
(k) Retained Optional Terminating Action
for Incorrectly Oriented Fasteners, With No
Changes
This paragraph restates the provisions of
paragraph (k) of AD 2015–02–23, with no
changes. Replacement of all forward and aft
fasteners (regardless of orientation or
condition) at WS 76.50 and WS 127.25, on
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both wings, terminates the requirements of
this AD. The replacement must be done in
accordance with the Accomplishment
Instructions of the applicable service
information specified in paragraphs (k)(1)
and (k)(2) of this AD, except as provided by
paragraph (m) of this AD. Doing the
replacements specified in this paragraph
terminates the requirements of paragraphs (g)
and (j) of AD 2014–03–17, only for the
airplane on which the replacement was done.
(1) For Model CL–600–1A11 (CL–600)
airplanes having S/Ns 1004 through 1085
inclusive: Bombardier Alert Service Bulletin
A600–0763, Revision 02, dated December 9,
2014, including Appendices 1 and 2, dated
September 26, 2013.
(2) For Model CL–600–2A12 (CL–601)
airplanes having S/Ns 3001 through 3066
inclusive, and Model CL–600–2B16 (CL–
601–3A and CL–601–3R Variants) airplanes
having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013.
(l) Retained Exception for Previously
Replaced Fasteners, With No Changes
This paragraph restates the provisions of
paragraph (l) of AD 2015–02–23, with no
changes. Replacement of all fractured and
incorrectly oriented forward and aft
fasteners, as specified in paragraph (i) or (k)
of AD 2014–03–17, if done before the
effective date of this AD, is considered
acceptable for compliance with the
requirements of this AD.
(m) Retained Exception to the Service
Information, With No Changes
This paragraph restates the requirements of
paragraph (m) of AD 2015–02–23, with no
changes. Where Bombardier Alert Service
Bulletin A600–0763, Revision 02, dated
December 9, 2014, including Appendices 1
and 2, dated September 26, 2013; and
Bombardier Alert Service Bulletin A601–
0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated
September 26, 2013; specify to contact
Bombardier for repair instructions, 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
Bombardier’s TCCA Design Approval
Organization (DAO).
(n) New Requirement of This AD:
Terminating Action
For airplanes on which any incorrectly
oriented fastener, and no fractured or missing
fastener, was detected during any inspection
required by paragraph (g), (h)(2), (i), and (j)(1)
of this AD: Within 24 months after the
effective date of this AD, replace all forward
and aft fasteners, regardless of condition or
orientation, at WS 76.50 and WS 127.25, on
affected wings, in accordance with the
Accomplishment Instructions of the
applicable service information specified in
paragraphs (k)(1) and (k)(2) of this AD, except
as provided by paragraph (m) of this AD.
Doing the replacements specified in this
paragraph terminates the requirements of this
AD. Doing the replacements specified in this
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
23205
paragraph terminates the requirements of
paragraphs (g) and (j) of AD 2014–03–17,
only for the airplane on which the
replacement was done.
(o) Credit for Previous Actions
This paragraph restates the provisions of
paragraph (n) of AD 2015–02–23, with new
credit for paragraph (n) of this AD. This
paragraph provides credit for actions
required by paragraphs (g), (h), (i), and (n) of
this AD, if those actions were performed
before the effective date of this AD using the
applicable service information identified in
paragraphs (o)(1) through (o)(4) of this AD.
(1) Bombardier Alert Service Bulletin
A600–0763, including Appendices 1 and 2,
dated September 26, 2013, which was
previously incorporated by reference on
March 6, 2014 (79 FR 9389, February 19,
2014).
(2) Bombardier Alert Service Bulletin
A600–0763, Revision 01, dated February 26,
2014, including Appendices 1 and 2, dated
September 26, 2013, which is not
incorporated by reference in this AD.
(3) Bombardier Alert Service Bulletin
A601–0627, including Appendices 1 and 2,
dated September 26, 2013, which was
previously incorporated by reference on
March 6, 2014 (79 FR 9389, February 19,
2014).
(4) Bombardier Alert Service Bulletin
A601–0627, Revision 01, dated February 26,
2014, including Appendices 1 and 2, dated
September 26, 2013, which is not
incorporated by reference in this AD.
(p) 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,
Engine and Propeller Directorate, FAA; or
TCCA; or Bombardier, Inc.’s TCCA DAO. If
approved by the DAO, the approval must
include the DAO-authorized signature.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Emergency Airworthiness Directive CF–
2013–39R2, dated December 12, 2014, for
related information. This MCAI may be
E:\FR\FM\20APP1.SGM
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23206
Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2016–5593.
(2) 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. You may view this
service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on April 8,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–08960 Filed 4–19–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5464; Directorate
Identifier 2015–NM–097–AD]
RIN 2120–AA64
Airworthiness Directives; Dassault
Aviation Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2011–10–
01, for all Dassault Aviation Model
FALCON 7X airplanes. AD 2011–10–01
currently requires repetitive functional
tests of the ram air turbine (RAT) heater
and repair if necessary. Since we issued
AD 2011–10–01, we received a revision
of an airworthiness limitations items
(ALI) document, which introduces new
and more restrictive maintenance
requirements and airworthiness
limitations for airplane structures and
systems. This proposed AD would
require revising the maintenance or
inspection program to incorporate new
maintenance requirements and
airworthiness limitations. We are
proposing this AD to prevent reduced
structural integrity and reduced control
of these airplanes due to the failure of
system components.
DATES: We must receive comments on
this proposed AD by June 6, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
Lhorne on DSK5TPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
14:51 Apr 19, 2016
Jkt 238001
• 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 NPRM, contact Dassault Falcon Jet
Corporation, Teterboro Airport, P.O.
Box 2000, South Hackensack, NJ 07606;
telephone: 201–440–6700; Internet:
https://www.dassaultfalcon.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5464; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1137;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–5464; Directorate Identifier
2015–NM–097–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
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Frm 00019
Fmt 4702
Sfmt 4702
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On April 20, 2011, we issued AD
2011–10–01, Amendment 39–16682 (76
FR 25535, May 5, 2011). AD 2011–10–
01 requires actions intended to address
an unsafe condition on all Dassault
Aviation Model FALCON 7X airplanes.
Since we issued AD 2011–10–01, we
received a revision of an ALI document,
Chapter 5–40–00, Airworthiness
Limitations, DGT 107838, Revision 4,
dated February 2, 2015, of the Dassault
Falcon 7X Maintenance Manual, which
introduces new and more restrictive
maintenance requirements and
airworthiness limitations.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive AD 2015–0095, dated May 29,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Dassault
Aviation FALCON 7X airplanes. The
MCAI states:
The airworthiness limitations and
maintenance requirements for the FALCON
7X type design are included in Dassault
Aviation FALCON 7X Aircraft Maintenance
Manual (AMM) chapter 5–40 and are
approved by EASA. To ensure
accomplishment of the maintenance tasks,
and implementation of the airworthiness
limitations, as specified in Dassault Aviation
FALCON 7X AMM chapter 5–40 original
issue, including temporary revision (TR) TR–
01, EASA issued AD 2008–0221 [https://
ad.easa.europa.eu/ad/2008-0221].
Since that [EASA] AD was issued, Dassault
Aviation issued revision 4 of the FALCON 7X
AMM chapter 5–40, which introduces new
and more restrictive maintenance
requirements and/or airworthiness
limitations.
Dassault Aviation AMM chapter 5–40
revision 4 contains, among others, the
following changes:
—Fatigue and Damage tolerance
airworthiness limitations,
—Miscellaneous Certification Maintenance
Requirements and Airworthiness
Limitation Items,
—Periodic restoration of the DC generators
(this action was required by EASA AD
2009–0254) [https://ad.easa.europa.eu/ad/
2009-0254],
—Functional test of the Ram Air Turbine
heater (this action was required by EASA
AD 2010–0033) [https://ad.easa.europa.eu/
ad/2010-0233] [which corresponds to FAA
AD 2011–10–01, Amendment 39–16682
(76 FR 25535, May 5, 2011)],
E:\FR\FM\20APP1.SGM
20APP1
]]>Agencies
[Federal Register Volume 81, Number 76 (Wednesday, April 20, 2016)]
[Proposed Rules]
[Pages 23202-23206]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08960]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-5593; Directorate Identifier 2015-NM-184-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2015-02-
23, for certain Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-
2A12 (CL-601), and CL-600-2B16 (CL-601-3A, and CL-601-3R Variants)
airplanes. AD 2015-02-23 currently requires repetitive inspections for
fractured or incorrectly oriented fasteners on the inboard flap hinge-
box forward fittings on both wings, and replacement of all fasteners if
necessary. The preamble to AD 2015-02-23 explains that we consider the
requirements interim action and are considering further rulemaking. We
now have determined that further rulemaking is indeed necessary, and
that replacement of the fasteners is necessary. This proposed AD would
require terminating action to replace the fasteners on the inboard flap
hinge-box forward fittings on both wings. We are proposing this AD to
detect and correct incorrectly oriented or fractured fasteners, which
could result in detachment of the flap hinge-box and the flap surface,
and consequent reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by June 6, 2016.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this NPRM, 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.
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-
5593; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7329; fax 516-794-5531.
SUPPLEMENTARY INFORMATION:
[[Page 23203]]
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-5593;
Directorate Identifier 2015-NM-184-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On January 20, 2015, we issued AD 2015-02-23, Amendment 39-18092
(80 FR 5670, February 3, 2015) (``AD 2015-02-23''). AD 2015-02-23
requires actions intended to address an unsafe condition on certain
Bombardier, Inc. Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and
CL-600-2B16 (CL-601-3A, and CL-601-3R Variants) airplanes. AD 2015-02-
23 corresponds to Canadian Emergency Airworthiness Directive CF-2013-
39R2, dated December 12, 2014 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''). The MCAI was
issued by Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada.
The preamble to AD 2015-02-23 explains that we consider the
requirements interim action and are considering further rulemaking. We
have now determined that further rulemaking is indeed necessary and
that, instead of continuing repetitive inspections, replacement of the
incorrectly oriented fasteners is necessary. This proposed AD follows
from that determination. This proposed AD would require terminating
action to replace the fasteners on the inboard flap hinge-box forward
fittings on affected wings.
The repetitive inspections can only detect if a fastener head has
fractured and sheared off. For incorrectly oriented fasteners, it is
not possible to detect whether a crack has already initiated and
propagated. The fastener fracture speed is unpredictable due to the
variability in the quality of the hole preparation prior to fastener
installation and whether there was any misalignment in the installation
of the fasteners. The failure of two fasteners could result in the loss
of the flap attachment, causing flap asymmetry and consequent reduced
controllability of the airplane.
We are proposing this AD to detect and correct incorrectly oriented
or fractured fasteners, which could result in detachment of the flap
hinge-box and the flap surface, and consequent reduced controllability
of the airplane.
Related Service Information Under 1 CFR Part 51
Bombardier has issued Alert Service Bulletins A600-0763, Revision
02, dated December 9, 2014, including Appendices 1 and 2, dated
September 26, 2013; and A601-0627, Revision 02, dated December 9, 2014,
including Appendices 1 and 2, dated September 26, 2013. The service
information describes procedures for repetitive inspections of the
fasteners on the inboard flap hinge-box forward fittings on both wings,
and replacement of 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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type designs.
Clarification of Intent of the MCAI
Paragraph C. of Canadian Emergency AD CF-2013-39R2, dated December
12, 2014, specifies to do the replacement on ``both'' wings. We have
clarified with TCCA that the intent of paragraph C. of Canadian
Emergency AD CF-2013-39R2, dated December 12, 2014, is that for
airplanes on which any incorrectly oriented fastener, and no fractured
or missing fastener, was detected, the replacement only needs to be
done on the affected wing on which incorrectly oriented fasteners were
found but none were found to be fractured.
The replacement of all forward and aft fasteners, regardless of
condition or orientation, at wing station (WS) 76.50 and WS 127.25, on
the affected wings, constitutes terminating action. Fasteners that have
cracks or fractures were already addressed by the requirements of AD
2015-02-13, which is restated in this proposed AD.
Costs of Compliance
We estimate that this proposed AD affects 120 airplanes of U.S.
registry.
The actions required by AD 2015-02-23, and retained in this
proposed AD, take about 1 work-hour per product, at an average labor
rate of $85 per work-hour. Based on these figures, the estimated cost
of the actions that are required by AD 2015-02-23 is $85 per product.
We also estimate that it would take about 59 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. We have received no definitive data
that would enable us to provide cost estimates for the parts cost.
Based on these figures, we estimate the cost of this proposed AD on
U.S. operators to be $601,800, or $5,015 per product.
In addition, we estimate that any necessary follow-on actions will
take about 58 work-hours and require parts costing $753, for a cost of
$5,683 per product. We have no way of determining the number of
aircraft that might need this action.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all available costs in our
cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
[[Page 23204]]
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2015-02-23, Amendment 39-18092 (80 FR 5670, February 3, 2015), and
adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2016-5593; Directorate Identifier
2015-NM-184-AD.
(a) Comments Due Date
We must receive comments by June 6, 2016.
(b) Affected ADs
This AD replaces AD 2015-02-23, Amendment 39-18092 (80 FR 5670,
February 3, 2015) (``AD 2015-02-23''). This AD affects AD 2014-03-
17, Amendment 39-17754 (79 FR 9389, February 19, 2014) (``AD 2014-
03-17'').
(c) Applicability
This AD applies to the Bombardier, Inc. airplanes identified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in
any category.
(1) Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes,
having serial numbers (S/Ns) 1004 through 1085 inclusive.
(2) Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes,
having S/Ns 3001 through 3066 inclusive.
(3) Bombardier, Inc. Model CL-600-2B16 (CL-601-3A and CL-601-3R
Variants) airplanes, having S/Ns 5001 through 5194 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of incorrectly oriented
fasteners. We are issuing this AD to detect and correct incorrectly
oriented or fractured fasteners, which could result in detachment of
the flap hinge-box and the flap surface, and consequent reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection on Airplanes Not Previously Inspected, With No
Changes
This paragraph restates the requirements of paragraph (g) of AD
2015-02-23, with no changes. For airplanes that have not been
inspected as required by paragraph (g) of AD 2014-03-17, as of
February 18, 2015 (the effective date of AD 2015-02-23): Within 10
flight cycles after February 18, 2015, or 100 flight cycles after
March 6, 2014 (the effective date of AD 2014-03-17), whichever
occurs first, do a detailed visual inspection for incorrect
orientation and any fractured or missing fastener heads of each
inboard flap fastener of the hinge-box forward fitting at wing
station (WS) 76.50 and WS 127.25, on both wings, in accordance with
the Accomplishment Instructions of the applicable service
information specified in paragraphs (g)(1) and (g)(2) of this AD.
Accomplishing the inspection required by this paragraph terminates
the requirements of paragraph (g) of AD 2014-03-17 for the inspected
airplane only.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014, including Appendices 1 and 2, dated September 26,
2013.
(h) Retained Corrective Actions for Paragraph (g) of This AD, With
Revised Paragraph (h)(2) of This AD
(1) This paragraph restates the requirements of paragraph (h)(1)
of AD 2015-02-23, with no changes. If, during any inspection
required by paragraph (g) of this AD, all fasteners are found
correctly oriented and not fractured, and no fastener heads are
missing (fasteners found intact): No further action is required by
this AD.
(2) This paragraph restates the requirements of paragraph (h)(2)
of AD 2015-02-23, with revised references to replacement paragraphs.
If, during any inspection required by paragraph (g) of this AD, any
fastener is found incorrectly oriented but no fasteners are
fractured or are missing a fastener head (fasteners found intact),
repeat the inspection required by paragraph (g) of this AD
thereafter at intervals not to exceed 10 flight cycles until the
replacements specified in paragraph (h)(3), (k), or (n) of this AD
is accomplished.
(3) This paragraph restates the requirements of paragraph (h)(3)
of AD 2015-02-23, with no changes. If, during any inspection
required by paragraph (g) of this AD, any fastener is found
fractured or has a missing fastener head: Before further flight,
remove and replace all forward and aft fasteners (regardless of
orientation or condition) at WS 76.50 and WS 127.25, on both wings,
in accordance with the Accomplishment Instructions of the applicable
service information specified in paragraphs (h)(3)(i) and (h)(3)(ii)
of this AD, except as required by paragraph (m) of this AD. After
accomplishing the replacements required by this paragraph, no
further action is required by this AD.
(i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014, including Appendices 1 and 2, dated September 26,
2013.
(i) Retained Inspection for Airplanes Previously Inspected and Found To
Have Incorrectly Oriented Fastener(s), With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2015-02-23, with no changes. For airplanes on which an inspection
required by paragraph (g) or (j) of AD 2014-03-17, has been done as
of the effective date of this AD, and on which any incorrectly
oriented fastener was found but no fasteners were fractured
(fasteners found intact): Except as provided by paragraph (l) of
this AD, within 10 flight cycles after February 18, 2015 (the
effective date of AD 2015-02-23), or within 100 flight cycles after
accomplishing the most recent inspection required by AD 2014-03-17,
whichever occurs first, do a detailed visual inspection for any
fractured or missing fastener heads of each inboard flap fastener of
the hinge-box forward fitting at WS 76.50 and WS 127.25, on both
wings. Do the inspection in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraphs (i)(1) and (i)(2) of this AD. Accomplishing the
[[Page 23205]]
inspection required by this paragraph terminates the requirements of
paragraphs (g) and (j) of AD 2014-03-17 for the inspected airplane
only.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014, including Appendices 1 and 2, dated September 26,
2013.
(j) Retained Corrective Actions for Paragraph (i) of This AD, With
Revised Reference to Additional, New Requirements
(1) This paragraph restates the requirements of paragraph (j)(1)
of AD 2015-02-23, with revised reference to additional, new
requirements. If, during any inspection required by paragraph (i) of
this AD, no fasteners are found fractured or have missing fastener
heads (fasteners are intact), repeat the inspection required by
paragraph (i) of this AD thereafter at intervals not to exceed 10
flight cycles until the replacement specified in paragraph (j)(2),
(k), or (n) of this AD is accomplished.
(2) This paragraph restates the requirements of paragraph (j)(2)
of AD 2015-02-23, with no changes. If, during any inspection
required by paragraph (i) of this AD, any fastener is found
fractured or has a missing fastener head: Before further flight,
remove and replace all forward and aft fasteners (regardless of
orientation or condition) at WS 76.50 and WS 127.25, on both wings,
in accordance with the Accomplishment Instructions of the applicable
service information specified in paragraphs (j)(2)(i) and (j)(2)(ii)
of this AD, except as required by paragraph (m) of this AD. After
accomplishing the replacements required by this paragraph, no
further action is required by this AD.
(i) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(ii) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014, including Appendices 1 and 2, dated September 26,
2013.
(k) Retained Optional Terminating Action for Incorrectly Oriented
Fasteners, With No Changes
This paragraph restates the provisions of paragraph (k) of AD
2015-02-23, with no changes. Replacement of all forward and aft
fasteners (regardless of orientation or condition) at WS 76.50 and
WS 127.25, on both wings, terminates the requirements of this AD.
The replacement must be done in accordance with the Accomplishment
Instructions of the applicable service information specified in
paragraphs (k)(1) and (k)(2) of this AD, except as provided by
paragraph (m) of this AD. Doing the replacements specified in this
paragraph terminates the requirements of paragraphs (g) and (j) of
AD 2014-03-17, only for the airplane on which the replacement was
done.
(1) For Model CL-600-1A11 (CL-600) airplanes having S/Ns 1004
through 1085 inclusive: Bombardier Alert Service Bulletin A600-0763,
Revision 02, dated December 9, 2014, including Appendices 1 and 2,
dated September 26, 2013.
(2) For Model CL-600-2A12 (CL-601) airplanes having S/Ns 3001
through 3066 inclusive, and Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variants) airplanes having S/Ns 5001 through 5194 inclusive:
Bombardier Alert Service Bulletin A601-0627, Revision 02, dated
December 9, 2014, including Appendices 1 and 2, dated September 26,
2013.
(l) Retained Exception for Previously Replaced Fasteners, With No
Changes
This paragraph restates the provisions of paragraph (l) of AD
2015-02-23, with no changes. Replacement of all fractured and
incorrectly oriented forward and aft fasteners, as specified in
paragraph (i) or (k) of AD 2014-03-17, if done before the effective
date of this AD, is considered acceptable for compliance with the
requirements of this AD.
(m) Retained Exception to the Service Information, With No Changes
This paragraph restates the requirements of paragraph (m) of AD
2015-02-23, with no changes. Where Bombardier Alert Service Bulletin
A600-0763, Revision 02, dated December 9, 2014, including Appendices
1 and 2, dated September 26, 2013; and Bombardier Alert Service
Bulletin A601-0627, Revision 02, dated December 9, 2014, including
Appendices 1 and 2, dated September 26, 2013; specify to contact
Bombardier for repair instructions, 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 Bombardier's TCCA Design Approval Organization (DAO).
(n) New Requirement of This AD: Terminating Action
For airplanes on which any incorrectly oriented fastener, and no
fractured or missing fastener, was detected during any inspection
required by paragraph (g), (h)(2), (i), and (j)(1) of this AD:
Within 24 months after the effective date of this AD, replace all
forward and aft fasteners, regardless of condition or orientation,
at WS 76.50 and WS 127.25, on affected wings, in accordance with the
Accomplishment Instructions of the applicable service information
specified in paragraphs (k)(1) and (k)(2) of this AD, except as
provided by paragraph (m) of this AD. Doing the replacements
specified in this paragraph terminates the requirements of this AD.
Doing the replacements specified in this paragraph terminates the
requirements of paragraphs (g) and (j) of AD 2014-03-17, only for
the airplane on which the replacement was done.
(o) Credit for Previous Actions
This paragraph restates the provisions of paragraph (n) of AD
2015-02-23, with new credit for paragraph (n) of this AD. This
paragraph provides credit for actions required by paragraphs (g),
(h), (i), and (n) of this AD, if those actions were performed before
the effective date of this AD using the applicable service
information identified in paragraphs (o)(1) through (o)(4) of this
AD.
(1) Bombardier Alert Service Bulletin A600-0763, including
Appendices 1 and 2, dated September 26, 2013, which was previously
incorporated by reference on March 6, 2014 (79 FR 9389, February 19,
2014).
(2) Bombardier Alert Service Bulletin A600-0763, Revision 01,
dated February 26, 2014, including Appendices 1 and 2, dated
September 26, 2013, which is not incorporated by reference in this
AD.
(3) Bombardier Alert Service Bulletin A601-0627, including
Appendices 1 and 2, dated September 26, 2013, which was previously
incorporated by reference on March 6, 2014 (79 FR 9389, February 19,
2014).
(4) Bombardier Alert Service Bulletin A601-0627, Revision 01,
dated February 26, 2014, including Appendices 1 and 2, dated
September 26, 2013, which is not incorporated by reference in this
AD.
(p) 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, Engine and Propeller Directorate, FAA; or TCCA; or
Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval
must include the DAO-authorized signature.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Emergency Airworthiness Directive CF-2013-39R2,
dated December 12, 2014, for related information. This MCAI may be
[[Page 23206]]
found in the AD docket on the Internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2016-5593.
(2) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com. You may view this service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on April 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-08960 Filed 4-19-16; 8:45 am]
BILLING CODE 4910-13-P
