(a) EFFECTIVE DATE
This AD is effective October 11, 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 Viking Air Limited (Type Certificate previously
held by Bombardier, Inc.; Canadair Limited) airplanes, certificated in
any category, as 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 Variant) airplanes, serial numbers 1056
through 1125 inclusive.
(3) Model CL-215-6B11 (CL-415 Variant) 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 al-
ready 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 VARIANT) 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 Variant) 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 Accomplish-
ment Instructions of the applicable service bulletin listed in table 1
to paragraphs (h), (i), and (k) of this AD.
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 Variant) 215-3155, Revision 1,
dated March 12, 2010
CL-215-6B11 (CL-415 Variant) 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
VARIANT) 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 Variant) air-
planes, 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 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 & REPETITIVE INSPECTIONS,
WITH NEW TERMINATING ACTION
This paragraph restates the requirements of paragraph (k) of AD 2011-
03-08, 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 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 NO CHANGES
This paragraph restates the parts installation limitation in paragraph
(l) of AD 2011-03-08, with no changes. 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) 215-541, dated July 9, 2009
CL-215-6B11 (CL-215T Variant) 215-3155, dated July 9, 2009
CL-600-6B11 (CL-415 Variant) 215-4414, dated 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 RELOCAT-
ING ACCUMULATORS
______________________________________________________________________
AFFECTED
FOR MODEL ACCUMULATORS USE SERVICE BULLETIN
______________________________________________________________________
CL-215-1A10 (CL-215) Aileron, if Bombardier Service
installed Bulletin 215-552,
Revision 2, dated
June 18, 2015
CL-215-6B11 (CL-215T Variant) Aileron, rudder, Bombardier Service
and elevator Bulletin 215-3158,
Revision 2, dated
April 15, 2014
CL-215-6B11 (CL-415 Variant) Aileron, rudder, Bombardier Service
and elevator Bulletin 215-4423,
Revision 5, dated
March 17, 2016
______________________________________________________________________
(o) NEW ESTABLISHMENT OF FLIGHT HOURS ON THE ACCUMULATOR, DETERMINATION OF
PREVIOUS USE OF THE ACCUMULATOR, AND REPLACEMENT IF NECESSARY
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), or 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 NUMBER OF FLIGHT
HOURS ON THE ACCUMULATOR
______________________________________________________________________
FOR MODEL USE SERVICE BULLETIN
______________________________________________________________________
CL-215-1A10 (CL-215) Bombardier Service Bulletin 215-557,
Revision 1, dated June 27, 2014
(applicable to MS28700-3 accumulator)
CL-215-6B11 (CL-215T Variant) Bombardier Service Bulletin 215-3182,
Revision 1, dated June 27, 2014
CL-215-6B11 (CL-415 Variant) Bombardier Service Bulletin 215-4470,
Revision 1, dated June 27, 2014
______________________________________________________________________
(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
BOMBARDIER BOMBARDIER
FOR MODEL TLMC MANUAL TR NO. DATED
______________________________________________________________________
CL-215-1A10 PSP 295 295/7 December 13, 2013
(CL-215)
CL-215-6B11 PSP 395 LLC-3 December 13, 2013
(CL-215T Variant)
CL-215-6B11 PSP 395-1 LLC-1 December 13, 2013
(CL-215T Variant)
CL-215-6B11 PSP 495 5-56 December 13, 2013
(CL-415 Variant)
______________________________________________________________________
(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 Service Bulletin 215-552, dated December 16, 2013.
(ii) Bombardier Service Bulletin 215-552, Revision 1, dated September 12,
2014.
(iii) Bombardier Service Bulletin 215-3158, dated March 21, 2012.
(iv) Bombardier Service Bulletin 215-3158, Revision 1, dated December 16,
2013.
(v) Bombardier Service Bulletin 215-4423 Revision NC, dated April 4, 2011.
(vi) Bombardier Service Bulletin 215-4423, Revision 1, dated September 28,
2011.
(vii) Bombardier Service Bulletin 215-4423 Revision 2, dated May 30, 2012.
(viii) Bombardier Service Bulletin 215-4423 Revision 3, dated December 16,
2013.
(ix) Bombardier 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 Service Bulletin 215-557, Revision NC, dated December 13,
2013.
(ii) Bombardier Service Bulletin 215-3182, Revision NC, dated December 13,
2013.
(iii) Bombardier Service Bulletin 215-4470 Revision NC, 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
Branch, 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 certification office, send
it to ATTN: Program Manager, Continuing Operational Safety, FAA, New
York ACO Branch, 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
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Viking Air
Limited'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 May 30, 2016, for
related information. This MCAI may be found in the AD docket on the
Internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2017-0474.
(2) For more information about this AD, contact Cesar A. Gomez, Aerospace
Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO
Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone
516-228-7318; fax 516-794-5531.
(3) Service information identified in this AD that is not incorporated by
reference is available at the addresses specified in paragraphs (u)(5)
and (u)(6) of this AD.
(u) MATERIAL INCORPORATED BY REFERENCE
(1) The Director of the Federal Register approved the incorporation by
reference (IBR) of the service information listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions
required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on October 11,
2017.
(i) Bombardier Service Bulletin 215-552, Revision 2, dated June 18, 2015.
(ii) Bombardier Service Bulletin 215-557, Revision 1, dated June 27, 2014.
(iii) Bombardier Service Bulletin 215-3158, Revision 2, dated April 15,
2014.
(iv) Bombardier Service Bulletin 215-3182 Revision 1, dated June 27, 2014.
(v) Bombardier Service Bulletin 215-4423 Revision 5, dated March 17, 2016.
(vi) Bombardier Service Bulletin 215-4470 Revision 1, dated June 27, 2014.
(vii) Bombardier Temporary Revision 5-56, dated December 13, 2013.
(viii) Bombardier Temporary Revision 295/7, dated December 13, 2013.
(ix) Bombardier Temporary Revision LLC-1, dated December 13, 2013.
(x) Bombardier Temporary Revision LLC-3, dated December 13, 2013.
(4) The following service information was approved for IBR on March 14,
2011 (76 FR 6536, February 7, 2011).
(i) Bombardier Service Bulletin 215-541, Revision 1, dated March 12, 2010.
(ii) Bombardier Service Bulletin 215-3155, Revision 1, dated March 12,
2010.
(iii) Bombardier Service Bulletin 215-4414, Revision 1, dated March 12,
2010.
(5) For service information identified in this AD, contact Viking Air
Limited, 1959 de Havilland Way, Sidney, British Columbia V8L 5V5,
Canada; telephone +1-250-656-7227; fax +1-250-656-0673; email acs-
technical.publications@vikingair.com; Internet http://www.vikingair.
com.
(6) You may view this service information at the FAA, Transport Standards
Branch, 1601 Lind Avenue SW., Renton, WA. For information on the
availability of this material at the FAA, call 425-227-1221.
(7) You may view this service information that is incorporated by
reference at the National Archives and Records Administration (NARA).
For information on the availability of this material at NARA, call 202
-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-
locations.html.
Issued in Renton, Washington, on August 16, 2017. Jeffrey E. Duven, Direc-
tor, System Oversight Division, Aircraft Certification Service.
FOR FURTHER INFORMATION CONTACT: Cesar A. Gomez, Aerospace Engineer, Air-
frame and Mechanical Systems Section, FAA, New York ACO Branch, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7318; fax
516-794-5531.
|
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0474; Product Identifier 2016-NM-096-AD; Amendment
39-19007; AD 2017-17-17]
RIN 2120-AA64
Airworthiness Directives; Viking Air Limited (Type Certificate
Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2011-03-08,
which applied to 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 required 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. This AD retains those inspections and the
accumulator replacement if necessary, and adds a new terminating action
to address the identified unsafe condition. This AD was prompted by the
development of a terminating action for the repetitive inspections. We
are issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective October 11, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 11,
2017.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of March
14, 2011 (76 FR 6536, February 7, 2011).
ADDRESSES: For service information identified in this final rule,
contact Viking Air Limited, 1959 de Havilland Way, Sidney, British
Columbia V8L 5V5, Canada; telephone +1-250-656-7227; fax +1-250-656-
0673; email acs-technical.publications@vikingair.com; Internet http://www.
vikingair.com. You may view this referenced service information at
the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221. It is also available on the Internet at http://www.regulations.
gov by searching for and locating Docket No. FAA-2017-0474.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.
gov by searching for and locating Docket No. FAA-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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Cesar A. Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600
Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7318;
fax 516-794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2011-03-08, Amendment 39-16592 (76 FR 6536,
February 7, 2011) (``AD 2011-03-08''). AD 2011-03-08 applied to certain
Bombardier, Inc., Model CL-215-1A10 (CL-215), CL-215-6B11 (CL-215T
Variant), and CL-215-6B11 (CL-415 Variant) airplanes. The NPRM
published in the Federal Register on May 18, 2017 (82 FR 22766). The
NPRM was prompted by the development of a terminating action
(relocation of the affected accumulators, and incorporation of new
airworthiness limitations), which addresses the unsafe condition. The
NPRM proposed to continue to require 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, repetitive ultrasonic inspections of the accumulators for
cracks, and
replacement of any accumulator in which a crack is detected. The NPRM
also proposed to require a new terminating action for the repetitive
inspections. We are issuing this AD to prevent failure of the screw cap
or end cap of certain accumulators, which could result in impact damage
to various components, potentially resulting in fuel spillage,
uncommanded flap movement, or loss of aileron control.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2009-42R2, dated May 30, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ''the MCAI''), to correct an
unsafe condition for certain Viking Air Limited 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
affected accumulators and incorporation of 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 http://www.
regulations.gov by searching for and locating Docket No. FAA-2017-0474.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Explanation of Changes Made to This Final Rule
We have revised this final rule to identify the legal name of the
manufacturer as published in the most recent type certificate data
sheet for the affected airplane models.
In the proposed AD, we inadvertently listed the wrong publication
dates for service information in two places. Table 4 to paragraph (o)
of the proposed AD referred to Bombardier Service Bulletin 215-4470,
Revision 1, dated December 13, 2013. We have corrected the publication
date for this document to June 27, 2014, in this AD. Additionally,
paragraph (r)(1)(iii) of the proposed AD referred to Bombardier Service
Bulletin 215-3158, dated March 28, 2012. We have corrected the
publication date for this document to March 21, 2012, in this AD.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD with the changes described
previously and minor editorial changes. We have determined that these
changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Bombardier, Inc., has issued the following service information:
Bombardier 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 Service Bulletin 215-3158, Revision 2, dated
April 15, 2014; and Bombardier Service Bulletin 215-4423, Revision 5,
dated March 17, 2016. This service information describes procedures to
relocate the aileron, elevator, and rudder hydraulic accumulators aft
and outboard of their current locations. These documents are distinct
since they apply to different airplane models.
Bombardier Service Bulletin 215-557, Revision 1, dated
June 27, 2014; Bombardier Service Bulletin 215-3182, Revision 1, dated
June 27, 2014; and Bombardier Service Bulletin 215-4470, Revision 1,
dated June 27, 2014. This service information describes procedures to
establish the number of flight hours for each accumulator and determine
if it has been used on another type of aircraft. These documents are
distinct since they apply to different airplane models.
Bombardier Temporary Revision 5-56, dated December 13,
2013; Bombardier Temporary Revision 295/7, dated December 13, 2013;
Bombardier Temporary Revision LLC-1, dated December 13, 2013; and
Bombardier Temporary Revision LLC-3, dated December 13, 2013. This
service information provides a 10,000-hour accumulator life limitation
for certain accumulators. These documents are distinct since they apply
to different airplane models.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 7 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
| Action |
Labor cost |
Parts cost |
Cost per product |
Cost on U.S. operators |
| Ultrasonic inspection (retained
action from AD 2011-03-08) |
7 work-hours x $85 per hour
= $595 |
$0 |
$595 |
$4,165 |
| Relocation, determination of
accumulator hours and usage, and maintenance or inspection program
revision (new action) |
56 work-hours x $85 per hour
= $4,760 |
0 |
4,760 |
33,320 |
We estimate the following costs to
do any necessary replacement
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need this
replacement.
On-Condition Costs
| Action |
Labor cost |
Parts cost |
Cost per product |
| Replacement of cracked part (retained
action from AD 2011-03-08). |
6 work-hours x $85 per hour =
$510
|
$4,055 |
$4,565 |
According to the manufacturer, some
of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2011-03-08, Amendment 39-16592 (76 FR 6536, February 7, 2011), and
adding the following new AD:
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