Airworthiness Directives; Bombardier, Inc. (Type Certificate Previously Held by Canadair Limited) Airplanes, 22766-22771 [2017-10030]
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been authorized by the Manager, Los Angeles
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (j)(2)
of this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (m)(4)(i) and (m)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0474; Directorate
Identifier 2016–NM–096–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. (Type Certificate Previously Held
by Canadair Limited) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2011–03–
08, for certain Bombardier, Inc., Model
CL–215–1A10 (CL–215), CL–215–6B11
(CL–215T Variant), and CL–215–6B11
(CL–415 Variant) airplanes. AD 2011–
03–08 currently requires an inspection
to determine the number of flight cycles
accumulated by certain accumulators
installed on the airplane, and repetitive
inspections of the accumulators for
(n) Related Information
cracks and replacement if necessary.
Since we issued AD 2011–03–08, we
(1) For more information about this AD,
contact Lu Lu, Aerospace Engineer, Airframe determined that a terminating action is
Branch, ANM–120S, FAA, Seattle ACO, 1601 necessary to address the identified
unsafe condition. This proposed AD
Lind Avenue SW., Renton, WA 98057–3356;
would add a requirement for the
phone: 425–917–6478; fax: 425–917–6590;
terminating action. We are proposing
email: lu.lu@faa.gov.
this AD to address the unsafe condition
(2) For information about AMOCs, contact
on these products.
George Garrido, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
DATES: We must receive comments on
Angeles ACO, 3960 Paramount Boulevard,
this proposed AD by July 3, 2017.
Lakewood, CA 90712–4137; phone: 562–627– ADDRESSES: You may send comments,
5357; fax: 562–627–5210; email:
using the procedures found in 14 CFR
george.garrido@faa.gov.
11.43 and 11.45, by any of the following
(3) For service information identified in
methods:
this AD, contact Boeing Commercial
• Federal eRulemaking Portal: Go to
Airplanes, Attention: Contractual & Data
https://www.regulations.gov. Follow the
Services (C&DS), 2600 Westminster Blvd.,
instructions for submitting comments.
MC 110–SK57, Seal Beach, CA 90740–5600;
• Fax: 202–493–2251.
telephone 562–797–1717; Internet https://
• Mail: U.S. Department of
www.myboeingfleet.com. You may view this
Transportation, Docket Operations, M–
referenced service information at the FAA,
30, West Building Ground Floor, Room
Transport Airplane Directorate, 1601 Lind
W12–140, 1200 New Jersey Avenue SE.,
Avenue SW., Renton, WA. For information
Washington, DC 20590.
on the availability of this material at the
• Hand Delivery: U.S. Department of
FAA, call 425–227–1221.
Transportation, Docket Operations, M–
Issued in Renton, Washington, on May 10,
30, West Building Ground Floor, Room
2017.
W12–140, 1200 New Jersey Avenue SE.,
Jeffrey E. Duven,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Manager, Transport Airplane Directorate,
Federal holidays.
Aircraft Certification Service.
For service information identified in
[FR Doc. 2017–10031 Filed 5–17–17; 8:45 am]
this NPRM, contact Bombardier, Inc.,
BILLING CODE 4910–13–P
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
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SUMMARY:
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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–2017–
0474; 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:
Cesar A. Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office (ACO), 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516–228–7318; fax
516–794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2017–0474; Directorate Identifier
2016–NM–096–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 26, 2011, we issued AD
2011–03–08, Amendment 39–16592 (76
FR 6536, February 7, 2011) (‘‘AD 2011–
03–08’’), for certain Bombardier, Inc.,
Model CL–215–1A10 (CL–215), CL–
215–6B11 (CL–215T Variant), and CL–
215–6B11 (CL–415 Variant) airplanes.
AD 2011–03–08 was prompted by
reports of seven cases of on-ground
hydraulic accumulator screw cap or end
cap failure, which have resulted in loss
of the associated hydraulic system and
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high-energy impact damage to adjacent
systems and structure. AD 2011–03–08
requires an inspection to determine the
number of flight cycles accumulated by
applicable accumulators (i.e., brake,
aileron, elevator, and rudder
accumulators) installed on the airplane.
AD 2011–03–08 also requires repetitive
ultrasonic inspections of the
accumulators for cracks and
replacement of any accumulator in
which a crack is detected. We issued AD
2011–03–08 to detect and correct
cracking of the accumulator, which
could result in loss of the associated
hydraulic system and high-energy
impact damage to adjacent systems and
structure, potentially resulting in fuel
spillage, uncommanded flap movement,
or loss of aileron control.
Since we issued AD 2011–03–08,
terminating action for the repetitive
inspections has been developed. We
have determined that a terminating
action (relocation of the affected
accumulators, and incorporation of new
airworthiness limitations) is necessary
to address the identified unsafe
condition.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2009–42R2,
dated June 13, 2016 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc., Model CL–
215–1A10 (CL–215), CL–215–6B11 (CL–
215T Variant), and CL–215–6B11 (CL–
415 Variant) airplanes. The MCAI states:
Seven cases of on-ground hydraulic
accumulator screw cap or end cap failure
have been experienced on CL–600–2B19
(CRJ) aeroplane, resulting in loss of the
associated hydraulic system and high-energy
impact damage to adjacent systems and
structure. To date, the lowest number of
flight cycles accumulated at the time of
failure has been 6991.
Although there have been no failures to
date on any CL–215–1A10 (CL–215) or CL–
215–6B11 (CL–215T and CL–415) aeroplane,
similar accumulators, Part Number (P/N) 08–
8423–010 (MS28700–3), to those installed on
the CL–600–2B19, are installed on the
aeroplane models listed in the Applicability
section of this [Canadian] AD.
A detailed analysis of the systems and
structure in the potential line of trajectory of
a failed screw cap/end cap for each
accumulator has been conducted. It has
identified that the worst-case scenarios
would be impact damage to various
components, potentially resulting in fuel
spillage, uncommanded flap movement, or
loss of aileron control.
This [Canadian] AD mandates repetitive
[ultrasonic] inspections of the accumulators
for cracks and replacement of any
accumulator in which a crack is detected.
Revision 1 of this [Canadian] AD clarified
the text of the [Canadian] AD, including the
P/N of the affected accumulators.
This revision provides the terminating
action [relocation of the affected
accumulators, and incorporating new
airworthiness limitations] to this [Canadian]
AD. It also modifies the applicability range
for the CL–215–1A10 (CL–215); the CL–215
is out of production and the last aeroplane
produced was serial number 1125.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0474.
Related Service Information Under 1
CFR Part 51
We reviewed the following
Bombardier, Inc., service information:
• Bombardier Canadair 215 Service
Bulletin 215–552, Revision 2, dated
June 18, 2015. This service information
describes procedures to relocate the
aileron hydraulic accumulator aft of its
current location.
• Bombardier Canadair 215T Service
Bulletin 215–3158, Revision 2, dated
April 15, 2014; and Bombardier 415
Service Bulletin 215–4423, Revision 5,
dated March 17, 2016. These documents
are distinct since they apply to different
airplane models. This service
information describes procedures to
relocate the aileron, elevator, and
rudder hydraulic accumulators aft and
outboard of their current locations.
• Bombardier Canadair 215 Service
Bulletin 215–557, Revision 1, dated
June 27, 2014; Bombardier Canadair
215T Service Bulletin 215–3182,
Revision 1, dated June 27, 2014; and
Bombardier 415 Service Bulletin 215–
4470, Revision 1, dated June 27, 2014.
These documents are distinct since they
apply to different airplane models. This
service information provides procedures
to establish the number of flight hours
for each accumulator and determine if it
has been used on another type of
aircraft.
• Bombardier Model CL–215–1A10
(CL–215), Time Limits/Maintenance
Checks (TLMC) Manual PSP 295, TR
295–7, dated December 13, 2013;
Bombardier Model CL–215–6B11 (CL–
215T), TLMC Manual PSP 395, TR LLC–
3, dated December 13, 2013; Bombardier
Model CL–215–6B11 (CL–215T), TLMC
Manual PSP 395–1, TR LLC–1, dated
December 13, 2013; and Bombardier
Model CL–600–6B11 (CL–415), TLMC
Manual PSP 495, TR 5–56, dated
December 13, 2013. These documents
are distinct since they apply to different
airplane models. This service
information provides a 10,000-hour
accumulator life limitation for certain
accumulators.
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.
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 these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 7 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
jstallworth on DSK7TPTVN1PROD with PROPOSALS
Action
Labor cost
Ultrasonic inspection [retained action from AD 2011–03–08]
7 work-hours × $85 per hour
= $595.
56 work-hours × $85 per hour
= $4,760.
Relocation, determination of accumulator hours and usage,
and maintenance or inspection program revision [new proposed action].
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Cost per
product
Parts cost
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Cost on U.S.
operators
$0
$595
$4,165
0
4,760
33,320
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We estimate the following costs to do
any necessary replacement that would
be required based on the results of the
proposed inspection. We have no way of
determining the number of airplanes
that might need this replacement.
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Replacement of cracked part [retained actions from AD 2011–03–08] ....
6 work-hours × $85 per hour =
$510.
$4,055
$4,565
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
jstallworth on DSK7TPTVN1PROD with PROPOSALS
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
(3) Model CL–215–6B11 (CL–415)
airplanes, serial numbers 2001 through 2990
inclusive.
(d) Subject
Air Transport Association (ATA) of
America Code 29, Hydraulic power.
(e) Reason
This AD was prompted by reports of onground hydraulic accumulator screw cap or
end cap failure resulting in a loss of the
associated hydraulic system and high-energy
impact damage to adjacent systems and
structure. We are issuing this AD to prevent
failure of the screw cap or end cap, which
could result in impact damage to various
components, potentially resulting in fuel
spillage, uncommanded flap movement, or
loss of aileron control.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
■
(g) Retained Inspection To Determine Flight
Cycles, With No Changes
Bombardier, Inc. (Type Certificate
Previously Held by Canadair Limited):
Docket No. FAA–2017–0474; Directorate
Identifier 2016–NM–096–AD.
This paragraph restates the requirements of
paragraph (g) of AD 2011–03–08, with no
changes. Within 50 flight hours after March
14, 2011 (the effective date of AD 2011–03–
08), inspect to determine the number of flight
cycles accumulated by each of the applicable
accumulators (i.e., brake, aileron, elevator,
and rudder accumulators) having part
number 08–8423–010 (MS28700–3) installed
on the airplane. A review of airplane
maintenance records is acceptable in lieu of
this inspection if the number of flight cycles
accumulated can be conclusively determined
from that review.
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2011–03–08, Amendment 39–16592 (76
FR 6536, February 7, 2011) (‘‘AD 2011–
03–08’’), and adding the following new
AD:
(a) Comments Due Date
We must receive comments by July 3, 2017.
(b) Affected ADs
This AD replaces AD 2011–03–08,
Amendment 39–16592 (76 FR 6536, February
7, 2011) (‘‘AD 2011–03–08’’).
(c) Applicability
This AD applies to Bombardier, Inc. (Type
Certificate previously held by Canadair
Limited) airplanes, certificated in any
category, identified in paragraphs (c)(1)
through (c)(3) of this AD.
(1) Model CL–215–1A10 (CL–215)
airplanes, serial numbers 1001 through 1125
inclusive.
(2) Model CL–215–6B11 (CL–215T)
airplanes, serial numbers 1056 through 1125
inclusive.
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(h) Retained Initial Ultrasonic Inspection for
Model CL–215–1A10 (CL–215) and CL–215–
6B11 (CL–215T) Airplanes, With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2011–03–08, with no
changes. For Model CL–215–1A10 (CL–215)
and CL–215–6B11 (CL–215T) airplanes: Do
an ultrasonic inspection for cracking of the
accumulator at the applicable time specified
in paragraph (h)(1) or (h)(2) of this AD, in
accordance with Part B of the
Accomplishment Instructions of the
applicable service bulletin listed in table 1 to
paragraphs (h), (i), and (k) of this AD.
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TABLE 1 TO PARAGRAPHS (h), (i), AND (k) OF THIS AD—SERVICE BULLETINS
For model—
Use Bombardier service bulletin—
CL–215–1A10 (CL–215) ....................................................
CL–215–6B11 (CL–215T) ..................................................
CL–215–6B11 (CL–415) ....................................................
215–541, Revision 1, dated March 12, 2010.
215–3155, Revision 1, dated March 12, 2010.
215–4414, Revision 1, dated March 12, 2010.
(1) For any accumulator on which the
inspection required by paragraph (g) of this
AD shows an accumulation of more than 875
total flight cycles, or on which it is not
possible to determine the number of total
accumulated flight cycles, do the inspection
within 125 flight cycles after March 14, 2011
(the effective date of AD 2011–03–08).
(2) For any accumulator on which the
inspection required by paragraph (g) of this
AD shows an accumulation of 875 total flight
cycles, or fewer, do the inspection before the
accumulation of 1,000 flight cycles on the
accumulator.
(i) Retained Initial Ultrasonic Inspection for
Model CL–215–6B11 (CL–415) Airplanes,
With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2011–03–08, with no
changes. For Model CL–215–6B11 (CL–415)
airplanes, do an ultrasonic inspection for
cracking of the accumulator at the applicable
time specified in paragraph (i)(1) or (i)(2) of
this AD, in accordance with Part B of the
Accomplishment Instructions of the
applicable service bulletin listed in table 1 to
paragraphs (h), (i), and (k) of this AD.
(1) For any accumulator on which the
inspection required by paragraph (g) of this
AD shows an accumulation of more than 750
flight cycles, or on which it is not possible
to determine the number of total
accumulated flight cycles, do the inspection
within 250 flight cycles after March 14, 2011
(the effective date of AD 2011–03–08).
(2) For any accumulator on which the
inspection required by paragraph (g) of this
AD shows an accumulation of 750 total flight
cycles, or fewer, do the inspection before the
accumulation of 1,000 total flight cycles on
the accumulator.
(j) Retained Repetitive Inspections, With
New Terminating Action
This paragraph restates the requirements of
paragraph (j) of AD 2011–03–08, with new
terminating action. If no cracking is found
during any inspection required by paragraph
(h) or (i) of this AD, repeat the inspection
thereafter at intervals not to exceed 750 flight
cycles until the actions required by
paragraphs (n), (o), and (p) of this AD have
been done.
(k) Retained Replacement of Cracked
Accumulators and Repetitive Inspections,
With New Terminating Action
If any cracking is found during any
inspection required by paragraph (h) or (i) of
this AD, before further flight, replace the
accumulator with a serviceable accumulator,
in accordance with Part B of the
Accomplishment Instructions of the
applicable Bombardier service bulletin listed
in table 1 to paragraphs (h), (i), and (k) of this
AD. Doing the replacement does not end the
inspection requirements of paragraphs (h)
and (i) of this AD. Repeat the inspections
required by paragraph (h) or (i) of this AD,
as applicable, at intervals not to exceed 750
flight cycles until the actions required by
paragraphs (n), (o), and (p) of this AD have
been done.
(l) Retained Parts Installation Limitation,
With Revised Compliance Language
This paragraph restates the parts
installation limitation in paragraph (l) of AD
2011–03–08, with revised compliance
language. As of March 14, 2011 (the effective
date of AD 2011–03–08), no person may
install an accumulator, part number 08–
8423–010 (MS28700–3), on any airplane
unless the accumulator has been inspected in
accordance with the requirements of
paragraph (h) or (i) of this AD.
(m) Retained Credit for Previous Actions,
With No Changes
This paragraph restates the credit provided
in paragraph (m) of AD 2011–03–08, with no
changes. Inspections accomplished before
March 14, 2011 (the effective date of AD
2011–03–08), in accordance with the
applicable service bulletin listed in table 2 to
paragraph (m) of this AD are considered
acceptable for compliance with the
corresponding action specified in paragraph
(h), (i), (j), or (k) of this AD.
TABLE 2 TO PARAGRAPH (m) OF THIS AD—CREDIT SERVICE BULLETINS
For model—
Use Bombardier service bulletin—
CL–215–1A10 (CL–215) ...........................................................................
CL–215–6B11 (CL–215T) ........................................................................
CL–600–6B11 (CL–415) ...........................................................................
215–541, dated July 9, 2009.
215–3155, July 9, 2009.
215–4414, July 9, 2009.
(n) New Relocation of Affected
Accumulators
Within 12 months after the effective date
of this AD, relocate affected hydraulic
accumulators, in accordance with the
Accomplishment Instructions of the
applicable Bombardier service bulletin
specified in table 3 to paragraph (n) of this
AD.
TABLE 3 TO PARAGRAPH (n) OF THIS AD—SERVICE INFORMATION FOR RELOCATING ACCUMULATORS
Affected accumulators—
Use service bulletin—
CL–215–1A10 (CL–215) ....................................
Aileron, if installed ............................................
CL–215–6B11 (CL–215T) ..................................
jstallworth on DSK7TPTVN1PROD with PROPOSALS
For model—
Aileron, Rudder, and Elevator .........................
CL–215–6B11 (CL–415) ....................................
Aileron, Rudder, and Elevator .........................
Bombardier Canadair 215 Service Bulletin
215–552, Revision 2, dated June 18, 2015.
Bombardier Canadair 215T Service Bulletin
215–3158, Revision 2, dated April 15, 2014.
Bombardier 415 Service Bulletin 215–4423,
Revision 5, dated March 17, 2016.
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(o) New Establishment of Accumulator
Number of Flight Hours and Determination
of Previous Use of the Accumulator
Within 12 months after the effective date
of this AD, establish the number of flight
hours for each accumulator, and determine
whether any accumulator has been used in
service on another type of airplane other than
Model CL–215–1A10 (CL–215), CL–215–
6B11 (CL–215T Variant), and CL–215–6B11
(CL–415 Variant), in accordance with the
Accomplishment Instructions in the
applicable Bombardier service bulletin
specified in table 4 to paragraph (o) of this
AD. If any accumulator is found that has
been in service on another type of airplane
other than Model CL–215–1A10 (CL–215),
CL–215–6B11 (CL–215T Variant), or CL–215–
6B11 (CL–415 Variant), replace the
accumulator within 50 flight hours after
determining an affected accumulator is
installed.
TABLE 4 TO PARAGRAPH (o) OF THIS AD—ESTABLISHMENT OF ACCUMULATOR NUMBER OF FLIGHT HOURS
For model—
Use service bulletin—
CL–215–1A10 (CL–215) .....................................
Bombardier Canadair 215 Service Bulletin 215–557, Revision 1, dated June 27, 2014 (Applicable to MS28700–3 accumulator).
Bombardier Canadair 215T Service Bulletin 215–3182, Revision 1, dated June 27, 2014.
Bombardier 415 Service Bulletin 215–4470, Revision 1, dated December 13, 2013.
CL–215–6B11 (CL–215T) ...................................
CL–215–6B11 (CL–415) .....................................
(p) New Airworthiness Limitations
Within 30 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate the
10,000-hour accumulator life limitation
specified in the applicable Time Limits/
Maintenance Checks (TLMC) Manual
Temporary Revisions (TRs) listed in table 5
to paragraph (p) of this AD. The initial
compliance time for accomplishing the
replacement of the accumulator is within the
limitation specified in the applicable TR
specified in Table 5 to paragraph (p) of this
AD, or within 30 days after the effective date
of this AD, whichever occurs later.
TABLE 5 TO PARAGRAPH (p) OF THIS AD—AIRWORTHINESS LIMITATIONS
Comply with TLMC manual—
For model—
CL–215–1A10
CL–215–6B11
CL–215–6B11
CL–215–6B11
(CL–215) .....................................................
(CL–215T) ...................................................
(CL–215T) ...................................................
(CL–415) .....................................................
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(q) No Alternative Actions and Intervals
After accomplishment of the revision
required by paragraph (p) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions and
intervals are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (s)(1) of this AD.
(r) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (n) of this AD,
if those actions were performed before the
effective date of this AD using any applicable
service information specified in paragraphs
(r)(1)(i) through (r)(1)(ix) of this AD.
(i) Bombardier Canadair 215 Service
Bulletin 215–552, dated December 16, 2013.
(ii) Bombardier Canadair 215 Service
Bulletin 215–552, Revision 1, dated
September 12, 2014.
(iii) Bombardier Canadair 215T Service
Bulletin 215–3158, dated March 28, 2012.
(iv) Bombardier Canadair 215T Service
Bulletin 215–3158, Revision 1, dated
December 16, 2013.
(v) Bombardier 415 Service Bulletin 215–
4423, dated April 4, 2011.
(vi) Bombardier 415 Service Bulletin 215–
4423, Revision 1, dated September 28, 2011.
(vii) Bombardier 415 Service Bulletin 215–
4423, Revision 2, dated May 30, 2012.
(viii) Bombardier 415 Service Bulletin 215–
4423, Revision 3, dated December 16, 2013.
(ix) Bombardier 415 Service Bulletin 215–
4423, Revision 4, dated December 3, 2015.
(2) This paragraph provides credit for
actions required by paragraph (o) of this AD,
VerDate Sep<11>2014
12:41 May 17, 2017
Jkt 241001
Temporary revision (TR)
number—
Dated—
PSP
PSP
PSP
PSP
295–7 ...................................
LLC–3 ..................................
LLC–1 ..................................
5–56 .....................................
December
December
December
December
295 ..............................
395 ..............................
395–1 ..........................
495 ..............................
if those actions were performed before the
effective date of this AD using any applicable
service information specified in paragraphs
(r)(2)(i) through (r)(2)(iii) of this AD.
(i) Bombardier Canadair 215 Service
Bulletin 215–557, dated December 13, 2013.
(ii) Bombardier Canadair 215T Service
Bulletin 215–3182, dated December 13, 2013.
(iii) Bombardier 415 Service Bulletin 215–
4470, dated December 13, 2013.
(s) 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 manager of 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, New York ACO, ANE–170,
FAA; or Transport Canada Civil Aviation
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
13,
13,
13,
13,
2013.
2013.
2013.
2013.
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(t) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2009–42R2,
dated June 13, 2016, 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–2017–0474.
(2) For more information about this AD,
contact Cesar A. Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch,
ANE–171, FAA, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7318; fax 516–
794–5531; email: Cesar.Gomez.faa.gov.
(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. 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.
E:\FR\FM\18MYP1.SGM
18MYP1
Federal Register / Vol. 82, No. 95 / Thursday, May 18, 2017 / Proposed Rules
Issued in Renton, Washington, on May 10,
2017.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–10030 Filed 5–17–17; 8:45 am]
BILLING CODE 4910–13–P
LIBRARY OF CONGRESS
Copyright Office
37 CFR Part 201
[Docket No. 2017–7]
Modernizing Copyright Recordation
U.S. Copyright Office, Library
of Congress.
ACTION: Notice of proposed rulemaking.
AGENCY:
The United States Copyright
Office is proposing to amend its
regulations governing recordation of
transfers of copyright ownership,
notices of termination, and other
documents pertaining to a copyright.
These amendments are being proposed
in conjunction with the anticipated
commencement of development effort
for a modernized electronic recordation
system.
DATES: Written comments must be
received no later than 11:59 p.m.
Eastern Time on July 17, 2017.
ADDRESSES: For reasons of government
efficiency, the Copyright Office is using
the regulations.gov system for the
submission and posting of public
comments in this proceeding. All
comments are therefore to be submitted
electronically through regulations.gov.
Specific instructions for submitting
comments are available on the
Copyright Office Web site at https://
www.copyright.gov/rulemaking/
recordation-modernization. If electronic
submission of comments is not feasible
due to lack of access to a computer and/
or the internet, please contact the Office
using the contact information below for
special instructions.
FOR FURTHER INFORMATION CONTACT:
Sarang V. Damle, General Counsel and
Associate Register of Copyrights, by
email at sdam@loc.gov, or Jason E.
Sloan, Attorney-Advisor, by email at
jslo@loc.gov. Each can be contacted by
telephone by calling (202) 707–8350.
SUPPLEMENTARY INFORMATION:
jstallworth on DSK7TPTVN1PROD with PROPOSALS
SUMMARY:
I. Background
Since 1870, the U.S. Copyright Office
has recorded documents pertaining to
works under copyright, such as
assignments, licenses, and grants of
security interests. Relevant here are the
VerDate Sep<11>2014
12:41 May 17, 2017
Jkt 241001
three primary types of documents
submitted to the Copyright Office for
recordation: Transfers of copyright
ownership,1 other documents pertaining
to a copyright,2 and notices of
termination.3 Pursuant to 17 U.S.C.
205(a), ‘‘[a]ny transfer of copyright
ownership or other document pertaining
to a copyright may be recorded in the
Copyright Office if’’ certain conditions
are met.4 Under the Copyright Act’s
notice of termination provisions in
sections 203(a)(4) and 304(c)(4), ‘‘[a]
copy of the notice shall be recorded in
the Copyright Office before the effective
date of termination, as a condition to its
taking effect,’’ and such ‘‘notice shall
comply, in form, content, and manner of
service, with requirements that the
Register of Copyrights shall prescribe by
regulation.’’ 5 These provisions also
apply to section 304(d)(1), another
termination provision, which
incorporates section 304(c)(4) by
reference.6 More broadly, section 702 of
the Act authorizes the Register of
Copyrights to ‘‘establish regulations . . .
for the administration of the functions
and duties made the responsibility of
the Register under [title 17],’’ and
section 705(a) requires that the Register
‘‘ensure that records of . . .
recordations . . . are maintained, and
that indexes of such records are
prepared.’’ 7
Congress has encouraged the
submission of documents for
recordation by providing certain legal
entitlements as a consequence of
1 A ‘‘transfer of copyright ownership’’ is defined
in section 101 of the Copyright Act as ‘‘an
assignment, mortgage, exclusive license, or any
other conveyance, alienation, or hypothecation of a
copyright or of any of the exclusive rights
comprised in a copyright, whether or not it is
limited in time or place of effect, but not including
a nonexclusive license.’’ 17 U.S.C. 101. Their
validity is governed by 17 U.S.C. 204.
2 A document ‘‘pertaining to a copyright’’ is
currently defined by the Office as one that ‘‘has a
direct or indirect relationship to the existence,
scope, duration, or identification of a copyright, or
to the ownership, division, allocation, licensing,
transfer, or exercise of rights under a copyright.
That relationship may be past, present, future, or
potential.’’ 37 CFR 201.4(a)(2).
3 A ‘‘notice of termination’’ is a notice that
terminates a grant to a third party of a copyright in
a work or any rights under a copyright. Only certain
grants may be terminated, and only in certain
circumstances. Termination is governed by three
separate provisions of the Copyright Act, with the
relevant one depending on a number of factors,
including when the grant was made, who executed
it, and when copyright was originally secured for
the work. See 17 U.S.C. 203, 304(c), 304(d).
4 17 U.S.C. 205(a); see also id. at 205(b) (‘‘The
Register of Copyrights shall, upon receipt of a
document as provided by subsection (a) and of the
fee provided by section 708, record the document
and return it with a certificate of recordation.’’).
5 Id. at 203(a)(4), 304(c)(4).
6 Id. at 304(d)(1).
7 Id. at 702, 705(a).
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
22771
recordation. For example, recordation
provides constructive notice of the facts
stated in the recorded document when
certain conditions are met.8 In addition,
recordation is a condition for the legal
effectiveness of notices of termination.9
Thus, the Office has an important
interest in ensuring that the public
record of copyright transactions is as
timely, complete, and accurate as
possible.
The current recordation process is a
time-consuming and labor-intensive
paper-based one, requiring remitters to
submit their documents in hard copy.
Once received, Office staff must, among
other things, digitize the paper
document, process the fee payment
including confirming that the correct fee
was submitted, examine the document
to confirm its eligibility for recordation,
search through the document for various
and often extensive indexing
information, manually input such
information into the Office’s public
catalog, and print and mail back to the
remitter a copy of the document marked
as having been recorded along with a
certificate of recordation. This process
can also involve considerable
correspondence with remitters to
remedy deficient submissions before
they can be recorded. Since late 2014,
the Office has permitted remitters to
submit some indexing information in
electronic form, limited to lists of titles
of the works associated with the
submitted document, but this too can
involve a significant amount of
correspondence with remitters and
manual input on the part of staff to
complete the recordation.10
Furthermore, electronic submission of
documents remains unavailable.
The Office is seeking to modernize
this process in coming years by
developing a fully electronic, online
system through which remitters will be
able to submit their documents and all
applicable indexing information to the
Office for recordation. The amendments
proposed today are designed to update
the Office’s current regulations to
govern the submission of documents to
the Office for recordation once the new
electronic system is developed and
launched. Though the Office cannot
currently estimate how long it will take
to complete the new system, the Office
is seeking public comments at this time
because the Office must, at present,
make a number of policy decisions
critical to the design of the to-bedeveloped system. Additionally, while
8 Id.
at 205(c).
at 203(a)(4)(A), 304(c)(4)(A), 304(d)(1).
10 See 37 CFR 201.4(c)(4); 79 FR 55633 (Sept. 17,
2014).
9 Id.
E:\FR\FM\18MYP1.SGM
18MYP1
]]>Agencies
[Federal Register Volume 82, Number 95 (Thursday, May 18, 2017)]
[Proposed Rules]
[Pages 22766-22771]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10030]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0474; Directorate Identifier 2016-NM-096-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. (Type Certificate
Previously Held by Canadair Limited) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-03-
08, for certain Bombardier, Inc., Model CL-215-1A10 (CL-215), CL-215-
6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes. AD
2011-03-08 currently requires an inspection to determine the number of
flight cycles accumulated by certain accumulators installed on the
airplane, and repetitive inspections of the accumulators for cracks and
replacement if necessary. Since we issued AD 2011-03-08, we determined
that a terminating action is necessary to address the identified unsafe
condition. This proposed AD would add a requirement for the terminating
action. We are proposing this AD to address the unsafe condition on
these products.
DATES: We must receive comments on this proposed AD by July 3, 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 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-2017-
0474; 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: Cesar A. Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury,
NY 11590; telephone 516-228-7318; fax 516-794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0474;
Directorate Identifier 2016-NM-096-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 26, 2011, we issued AD 2011-03-08, Amendment 39-16592
(76 FR 6536, February 7, 2011) (``AD 2011-03-08''), for certain
Bombardier, Inc., Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T
Variant), and CL-215-6B11 (CL-415 Variant) airplanes. AD 2011-03-08 was
prompted by reports of seven cases of on-ground hydraulic accumulator
screw cap or end cap failure, which have resulted in loss of the
associated hydraulic system and
[[Page 22767]]
high-energy impact damage to adjacent systems and structure. AD 2011-
03-08 requires an inspection to determine the number of flight cycles
accumulated by applicable accumulators (i.e., brake, aileron, elevator,
and rudder accumulators) installed on the airplane. AD 2011-03-08 also
requires repetitive ultrasonic inspections of the accumulators for
cracks and replacement of any accumulator in which a crack is detected.
We issued AD 2011-03-08 to detect and correct cracking of the
accumulator, which could result in loss of the associated hydraulic
system and high-energy impact damage to adjacent systems and structure,
potentially resulting in fuel spillage, uncommanded flap movement, or
loss of aileron control.
Since we issued AD 2011-03-08, terminating action for the
repetitive inspections has been developed. We have determined that a
terminating action (relocation of the affected accumulators, and
incorporation of new airworthiness limitations) is necessary to address
the identified unsafe condition.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2009-42R2, dated June 13, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Bombardier, Inc., Model CL-215-1A10 (CL-
215), CL-215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant)
airplanes. The MCAI states:
Seven cases of on-ground hydraulic accumulator screw cap or end
cap failure have been experienced on CL-600-2B19 (CRJ) aeroplane,
resulting in loss of the associated hydraulic system and high-energy
impact damage to adjacent systems and structure. To date, the lowest
number of flight cycles accumulated at the time of failure has been
6991.
Although there have been no failures to date on any CL-215-1A10
(CL-215) or CL-215-6B11 (CL-215T and CL-415) aeroplane, similar
accumulators, Part Number (P/N) 08-8423-010 (MS28700-3), to those
installed on the CL-600-2B19, are installed on the aeroplane models
listed in the Applicability section of this [Canadian] AD.
A detailed analysis of the systems and structure in the
potential line of trajectory of a failed screw cap/end cap for each
accumulator has been conducted. It has identified that the worst-
case scenarios would be impact damage to various components,
potentially resulting in fuel spillage, uncommanded flap movement,
or loss of aileron control.
This [Canadian] AD mandates repetitive [ultrasonic] inspections
of the accumulators for cracks and replacement of any accumulator in
which a crack is detected.
Revision 1 of this [Canadian] AD clarified the text of the
[Canadian] AD, including the P/N of the affected accumulators.
This revision provides the terminating action [relocation of the
affected accumulators, and incorporating new airworthiness
limitations] to this [Canadian] AD. It also modifies the
applicability range for the CL-215-1A10 (CL-215); the CL-215 is out
of production and the last aeroplane produced was serial number
1125.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0474.
Related Service Information Under 1 CFR Part 51
We reviewed the following Bombardier, Inc., service information:
Bombardier Canadair 215 Service Bulletin 215-552, Revision
2, dated June 18, 2015. This service information describes procedures
to relocate the aileron hydraulic accumulator aft of its current
location.
Bombardier Canadair 215T Service Bulletin 215-3158,
Revision 2, dated April 15, 2014; and Bombardier 415 Service Bulletin
215-4423, Revision 5, dated March 17, 2016. These documents are
distinct since they apply to different airplane models. This service
information describes procedures to relocate the aileron, elevator, and
rudder hydraulic accumulators aft and outboard of their current
locations.
Bombardier Canadair 215 Service Bulletin 215-557, Revision
1, dated June 27, 2014; Bombardier Canadair 215T Service Bulletin 215-
3182, Revision 1, dated June 27, 2014; and Bombardier 415 Service
Bulletin 215-4470, Revision 1, dated June 27, 2014. These documents are
distinct since they apply to different airplane models. This service
information provides procedures to establish the number of flight hours
for each accumulator and determine if it has been used on another type
of aircraft.
Bombardier Model CL-215-1A10 (CL-215), Time Limits/
Maintenance Checks (TLMC) Manual PSP 295, TR 295-7, dated December 13,
2013; Bombardier Model CL-215-6B11 (CL-215T), TLMC Manual PSP 395, TR
LLC-3, dated December 13, 2013; Bombardier Model CL-215-6B11 (CL-215T),
TLMC Manual PSP 395-1, TR LLC-1, dated December 13, 2013; and
Bombardier Model CL-600-6B11 (CL-415), TLMC Manual PSP 495, TR 5-56,
dated December 13, 2013. These documents are distinct since they apply
to different airplane models. This service information provides a
10,000-hour accumulator life limitation for certain accumulators.
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.
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 these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 7 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Ultrasonic inspection [retained action 7 work-hours x $85 per $0 $595 $4,165
from AD 2011-03-08]. hour = $595.
Relocation, determination of 56 work-hours x $85 per 0 4,760 33,320
accumulator hours and usage, and hour = $4,760.
maintenance or inspection program
revision [new proposed action].
----------------------------------------------------------------------------------------------------------------
[[Page 22768]]
We estimate the following costs to do any necessary replacement
that would be required based on the results of the proposed inspection.
We have no way of determining the number of airplanes that might need
this replacement.
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement of cracked part [retained actions 6 work-hours x $85 per hour = $4,055 $4,565
from AD 2011-03-08]. $510.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2011-03-08, Amendment 39-16592 (76 FR 6536, February 7, 2011) (``AD
2011-03-08''), and adding the following new AD:
Bombardier, Inc. (Type Certificate Previously Held by Canadair
Limited): Docket No. FAA-2017-0474; Directorate Identifier 2016-NM-
096-AD.
(a) Comments Due Date
We must receive comments by July 3, 2017.
(b) Affected ADs
This AD replaces AD 2011-03-08, Amendment 39-16592 (76 FR 6536,
February 7, 2011) (``AD 2011-03-08'').
(c) Applicability
This AD applies to Bombardier, Inc. (Type Certificate previously
held by Canadair Limited) airplanes, certificated in any category,
identified in paragraphs (c)(1) through (c)(3) of this AD.
(1) Model CL-215-1A10 (CL-215) airplanes, serial numbers 1001
through 1125 inclusive.
(2) Model CL-215-6B11 (CL-215T) airplanes, serial numbers 1056
through 1125 inclusive.
(3) Model CL-215-6B11 (CL-415) airplanes, serial numbers 2001
through 2990 inclusive.
(d) Subject
Air Transport Association (ATA) of America Code 29, Hydraulic
power.
(e) Reason
This AD was prompted by reports of on-ground hydraulic
accumulator screw cap or end cap failure resulting in a loss of the
associated hydraulic system and high-energy impact damage to
adjacent systems and structure. We are issuing this AD to prevent
failure of the screw cap or end cap, which could result in impact
damage to various components, potentially resulting in fuel
spillage, uncommanded flap movement, or loss of aileron control.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection To Determine Flight Cycles, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2011-03-08, with no changes. Within 50 flight hours after March 14,
2011 (the effective date of AD 2011-03-08), inspect to determine the
number of flight cycles accumulated by each of the applicable
accumulators (i.e., brake, aileron, elevator, and rudder
accumulators) having part number 08-8423-010 (MS28700-3) installed
on the airplane. A review of airplane maintenance records is
acceptable in lieu of this inspection if the number of flight cycles
accumulated can be conclusively determined from that review.
(h) Retained Initial Ultrasonic Inspection for Model CL-215-1A10 (CL-
215) and CL-215-6B11 (CL-215T) Airplanes, With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2011-03-08, with no changes. For Model CL-215-1A10 (CL-215) and CL-
215-6B11 (CL-215T) airplanes: Do an ultrasonic inspection for
cracking of the accumulator at the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD, in accordance with Part B of
the Accomplishment Instructions of the applicable service bulletin
listed in table 1 to paragraphs (h), (i), and (k) of this AD.
[[Page 22769]]
Table 1 to Paragraphs (h), (i), and (k) of This AD--Service Bulletins
------------------------------------------------------------------------
For model-- Use Bombardier service bulletin--
------------------------------------------------------------------------
CL-215-1A10 (CL-215).............. 215-541, Revision 1, dated March 12,
2010.
CL-215-6B11 (CL-215T)............. 215-3155, Revision 1, dated March
12, 2010.
CL-215-6B11 (CL-415).............. 215-4414, Revision 1, dated March
12, 2010.
------------------------------------------------------------------------
(1) For any accumulator on which the inspection required by
paragraph (g) of this AD shows an accumulation of more than 875
total flight cycles, or on which it is not possible to determine the
number of total accumulated flight cycles, do the inspection within
125 flight cycles after March 14, 2011 (the effective date of AD
2011-03-08).
(2) For any accumulator on which the inspection required by
paragraph (g) of this AD shows an accumulation of 875 total flight
cycles, or fewer, do the inspection before the accumulation of 1,000
flight cycles on the accumulator.
(i) Retained Initial Ultrasonic Inspection for Model CL-215-6B11 (CL-
415) Airplanes, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2011-03-08, with no changes. For Model CL-215-6B11 (CL-415)
airplanes, do an ultrasonic inspection for cracking of the
accumulator at the applicable time specified in paragraph (i)(1) or
(i)(2) of this AD, in accordance with Part B of the Accomplishment
Instructions of the applicable service bulletin listed in table 1 to
paragraphs (h), (i), and (k) of this AD.
(1) For any accumulator on which the inspection required by
paragraph (g) of this AD shows an accumulation of more than 750
flight cycles, or on which it is not possible to determine the
number of total accumulated flight cycles, do the inspection within
250 flight cycles after March 14, 2011 (the effective date of AD
2011-03-08).
(2) For any accumulator on which the inspection required by
paragraph (g) of this AD shows an accumulation of 750 total flight
cycles, or fewer, do the inspection before the accumulation of 1,000
total flight cycles on the accumulator.
(j) Retained Repetitive Inspections, With New Terminating Action
This paragraph restates the requirements of paragraph (j) of AD
2011-03-08, with new terminating action. If no cracking is found
during any inspection required by paragraph (h) or (i) of this AD,
repeat the inspection thereafter at intervals not to exceed 750
flight cycles until the actions required by paragraphs (n), (o), and
(p) of this AD have been done.
(k) Retained Replacement of Cracked Accumulators and Repetitive
Inspections, With New Terminating Action
If any cracking is found during any inspection required by
paragraph (h) or (i) of this AD, before further flight, replace the
accumulator with a serviceable accumulator, in accordance with Part
B of the Accomplishment Instructions of the applicable Bombardier
service bulletin listed in table 1 to paragraphs (h), (i), and (k)
of this AD. Doing the replacement does not end the inspection
requirements of paragraphs (h) and (i) of this AD. Repeat the
inspections required by paragraph (h) or (i) of this AD, as
applicable, at intervals not to exceed 750 flight cycles until the
actions required by paragraphs (n), (o), and (p) of this AD have
been done.
(l) Retained Parts Installation Limitation, With Revised Compliance
Language
This paragraph restates the parts installation limitation in
paragraph (l) of AD 2011-03-08, with revised compliance language. As
of March 14, 2011 (the effective date of AD 2011-03-08), no person
may install an accumulator, part number 08-8423-010 (MS28700-3), on
any airplane unless the accumulator has been inspected in accordance
with the requirements of paragraph (h) or (i) of this AD.
(m) Retained Credit for Previous Actions, With No Changes
This paragraph restates the credit provided in paragraph (m) of
AD 2011-03-08, with no changes. Inspections accomplished before
March 14, 2011 (the effective date of AD 2011-03-08), in accordance
with the applicable service bulletin listed in table 2 to paragraph
(m) of this AD are considered acceptable for compliance with the
corresponding action specified in paragraph (h), (i), (j), or (k) of
this AD.
Table 2 to Paragraph (m) of This AD--Credit Service Bulletins
------------------------------------------------------------------------
Use Bombardier service
For model-- bulletin--
------------------------------------------------------------------------
CL-215-1A10 (CL-215)................... 215-541, dated July 9, 2009.
CL-215-6B11 (CL-215T).................. 215-3155, July 9, 2009.
CL-600-6B11 (CL-415)................... 215-4414, July 9, 2009.
------------------------------------------------------------------------
(n) New Relocation of Affected Accumulators
Within 12 months after the effective date of this AD, relocate
affected hydraulic accumulators, in accordance with the
Accomplishment Instructions of the applicable Bombardier service
bulletin specified in table 3 to paragraph (n) of this AD.
Table 3 to Paragraph (n) of This AD--Service Information for Relocating
Accumulators
------------------------------------------------------------------------
Affected Use service
For model-- accumulators-- bulletin--
------------------------------------------------------------------------
CL-215-1A10 (CL-215)........ Aileron, if Bombardier Canadair
installed. 215 Service
Bulletin 215-552,
Revision 2, dated
June 18, 2015.
CL-215-6B11 (CL-215T)....... Aileron, Rudder, and Bombardier Canadair
Elevator. 215T Service
Bulletin 215-3158,
Revision 2, dated
April 15, 2014.
CL-215-6B11 (CL-415)........ Aileron, Rudder, and Bombardier 415
Elevator. Service Bulletin
215-4423, Revision
5, dated March 17,
2016.
------------------------------------------------------------------------
[[Page 22770]]
(o) New Establishment of Accumulator Number of Flight Hours and
Determination of Previous Use of the Accumulator
Within 12 months after the effective date of this AD, establish
the number of flight hours for each accumulator, and determine
whether any accumulator has been used in service on another type of
airplane other than Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T
Variant), and CL-215-6B11 (CL-415 Variant), in accordance with the
Accomplishment Instructions in the applicable Bombardier service
bulletin specified in table 4 to paragraph (o) of this AD. If any
accumulator is found that has been in service on another type of
airplane other than Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T
Variant), or CL-215-6B11 (CL-415 Variant), replace the accumulator
within 50 flight hours after determining an affected accumulator is
installed.
Table 4 to Paragraph (o) of This AD--Establishment of Accumulator Number
of Flight Hours
------------------------------------------------------------------------
For model-- Use service bulletin--
------------------------------------------------------------------------
CL-215-1A10 (CL-215)......... Bombardier Canadair 215 Service Bulletin
215-557, Revision 1, dated June 27, 2014
(Applicable to MS28700-3 accumulator).
CL-215-6B11 (CL-215T)........ Bombardier Canadair 215T Service Bulletin
215-3182, Revision 1, dated June 27,
2014.
CL-215-6B11 (CL-415)......... Bombardier 415 Service Bulletin 215-4470,
Revision 1, dated December 13, 2013.
------------------------------------------------------------------------
(p) New Airworthiness Limitations
Within 30 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate the
10,000-hour accumulator life limitation specified in the applicable
Time Limits/Maintenance Checks (TLMC) Manual Temporary Revisions
(TRs) listed in table 5 to paragraph (p) of this AD. The initial
compliance time for accomplishing the replacement of the accumulator
is within the limitation specified in the applicable TR specified in
Table 5 to paragraph (p) of this AD, or within 30 days after the
effective date of this AD, whichever occurs later.
Table 5 to Paragraph (p) of This AD--Airworthiness Limitations
----------------------------------------------------------------------------------------------------------------
Comply with TLMC Temporary revision
For model-- manual-- (TR) number-- Dated--
----------------------------------------------------------------------------------------------------------------
CL-215-1A10 (CL-215).............. PSP 295.............. 295-7............... December 13, 2013.
CL-215-6B11 (CL-215T)............. PSP 395.............. LLC-3............... December 13, 2013.
CL-215-6B11 (CL-215T)............. PSP 395-1............ LLC-1............... December 13, 2013.
CL-215-6B11 (CL-415).............. PSP 495.............. 5-56................ December 13, 2013.
----------------------------------------------------------------------------------------------------------------
(q) No Alternative Actions and Intervals
After accomplishment of the revision required by paragraph (p)
of this AD, no alternative actions (e.g., inspections) or intervals
may be used unless the actions and intervals are approved as an
alternative method of compliance (AMOC) in accordance with the
procedures specified in paragraph (s)(1) of this AD.
(r) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (n) of this AD, if those actions were performed before the
effective date of this AD using any applicable service information
specified in paragraphs (r)(1)(i) through (r)(1)(ix) of this AD.
(i) Bombardier Canadair 215 Service Bulletin 215-552, dated
December 16, 2013.
(ii) Bombardier Canadair 215 Service Bulletin 215-552, Revision
1, dated September 12, 2014.
(iii) Bombardier Canadair 215T Service Bulletin 215-3158, dated
March 28, 2012.
(iv) Bombardier Canadair 215T Service Bulletin 215-3158,
Revision 1, dated December 16, 2013.
(v) Bombardier 415 Service Bulletin 215-4423, dated April 4,
2011.
(vi) Bombardier 415 Service Bulletin 215-4423, Revision 1, dated
September 28, 2011.
(vii) Bombardier 415 Service Bulletin 215-4423, Revision 2,
dated May 30, 2012.
(viii) Bombardier 415 Service Bulletin 215-4423, Revision 3,
dated December 16, 2013.
(ix) Bombardier 415 Service Bulletin 215-4423, Revision 4, dated
December 3, 2015.
(2) This paragraph provides credit for actions required by
paragraph (o) of this AD, if those actions were performed before the
effective date of this AD using any applicable service information
specified in paragraphs (r)(2)(i) through (r)(2)(iii) of this AD.
(i) Bombardier Canadair 215 Service Bulletin 215-557, dated
December 13, 2013.
(ii) Bombardier Canadair 215T Service Bulletin 215-3182, dated
December 13, 2013.
(iii) Bombardier 415 Service Bulletin 215-4470, dated December
13, 2013.
(s) 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 manager of 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.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, New York ACO,
ANE-170, FAA; or Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.
(t) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2009-42R2, dated June 13,
2016, 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-2017-0474.
(2) For more information about this AD, contact Cesar A. Gomez,
Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE-171,
FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516-228-7318; fax 516-794-5531; email:
Cesar.Gomez.faa.gov.
(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. 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.
[[Page 22771]]
Issued in Renton, Washington, on May 10, 2017.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10030 Filed 5-17-17; 8:45 am]
BILLING CODE 4910-13-P
