Airworthiness Directives; Bombardier, Inc. Airplanes, 47543-47545 [2013-18771]
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
tkelley on DSK3SPTVN1PROD with RULES
(r) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2010–0192
(corrected), dated October 11, 2010; and
EASA Airworthiness Directive 2010–0193
(corrected), dated October 11, 2010; for
related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the addresses specified in
paragraphs (s)(5), (s)(6), and (s)(7) of this AD.
(s) 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 the AD specifies otherwise.
(3) The following service information was
approved for IBR on September 10, 2013.
(i) Airbus Mandatory Service Bulletin
A330–27–3102, Revision 08, dated December
6, 2007.
(ii) Airbus Mandatory Service Bulletin
A340–27–4107, Revision 08, dated December
6, 2007.
(iii) Task 27.40.00/02, Lubrication of
Trimmable Horizontal Stabilizer (THS)
Actuator Ball Screw Nut, of Airbus A330
Maintenance Review Board Report (MRBR),
Revision 12, dated July 1, 2010.
(iv) Task 27.40.00/02, Lubrication of THS
Actuator Ball Screw Nut, of Airbus A340
MRBR, Revision 12, dated July 1, 2010.
(v) A330 Airworthiness Limitations
Section (ALS) Part 4—Ageing Systems
Maintenance, Revision 02, dated December
16, 2009. Only the title page and Record of
Revision of this document contain the
revision level; no other page of the document
contains this information. The title page of
this document does not contain an issue date.
(vi) Airbus A330 ALS Part 4—Ageing
Systems Maintenance, Revision 03, dated
September 9, 2011. Only the title page and
Record of Revision of this document contain
the revision level; no other page of the
document contains this information. The title
page of this document does not contain an
issue date.
(vii) Airbus A340 ALS Part 4—Ageing
Systems Maintenance, Revision 01, dated
VerDate Mar<15>2010
17:14 Aug 05, 2013
Jkt 229001
December 15, 2009. Only the title page and
Record of Revision of this document contains
the revision level; no other page of this
document contains this information. The title
page of this document does not contain an
issue date.
(viii) Airbus A340 ALS Part 4—Ageing
Systems Maintenance, Revision 02, dated
October 12, 2011. Only the title page and
Record of Revision of this document contain
the revision level; no other page of the
document contains this information. The title
page of this document does not contain an
issue date.
(ix) Airbus A340 ALS Part 4—Ageing
Systems Maintenance, Revision 03, dated
November 15, 2012. Only the title page and
Record of Revision of this document contain
the revision level; no other page of the
document contains this information. The title
page of this document does not contain an
issue date.
(4) The following service information was
approved for IBR on May 4, 2005 (60 FR
16104, March 30, 2005).
(i) Airbus Service Bulletin A330–27–3007,
Revision 01, dated September 18, 1996.
(ii) Airbus Service Bulletin A330–27–3015,
dated June 7, 1995.
(iii) Airbus Service Bulletin A330–27–
3047, Revision 01, dated November 26, 1997.
(iv) Airbus Service Bulletin A330–27–
3050, dated November 15, 1996.
(v) Airbus Service Bulletin A330–27–3052,
Revision 03, dated December 5, 2001.
(vi) Airbus Service Bulletin A330–27–
3085, Revision 02, dated September 5, 2002.
(vii) Airbus Service Bulletin A330–27–
3093, Revision 01, dated September 5, 2002.
(viii) Airbus Service Bulletin A330–55–
3020, Revision 01, dated October 21, 1998.
(ix) Airbus Service Bulletin A340–27–
4007, dated April 7, 1994.
(x) Airbus Service Bulletin A340–27–4025,
dated June 7, 1995.
(xi) Airbus Service Bulletin A340–27–
4054, Revision 01, dated November 26, 1997.
(xii) Airbus Service Bulletin A340–27–
4057, dated November 15, 1996.
(xiii) Airbus Service Bulletin A340–27–
4059, Revision 03, dated December 5, 2001.
(xiv) Airbus Service Bulletin A340–27–
4089, Revision 02, dated September 5, 2002.
(xv) Airbus Service Bulletin A340–27–
4099, Revision 01, dated September 5, 2002.
(xvi) Airbus Service Bulletin A340–55–
4021, Revision 01, October 21, 1998.
(5) For Airbus service information
identified in this AD, contact Airbus SAS—
Airworthiness Office—EAL, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet: https://
www.airbus.com.
(6) For TRW Aeronautical Systems, SAMM
Avionique, and Lucas Aerospace service
information identified in this AD, contact
Goodrich Corporation, Actuation Systems,
Stafford Road, Fordhouses, Wolverhampton
WV10 7EH, England; telephone +44 (0) 1902
624938; fax +44 (0) 1902 788100; email
techpubs.wolverhampton@goodrich.com;
Internet https://www.goodrich.com/TechPubs.
(7) You may review copies of the service
information at the FAA, Transport Airplane
PO 00000
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47543
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(8) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on June 21,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–18774 Filed 8–5–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0209; Directorate
Identifier 2012–NM–127–AD; Amendment
39–17514; AD 2013–14–09]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2012–14–
04 for certain Bombardier, Inc. Model
DHC–8–100, –200, and –300 series
airplanes. AD 2012–14–04 required
replacing certain parking brake
accumulators. This new AD retains this
requirement. This new AD also requires
installing restraint devices around the
parking brake accumulator end caps. We
are issuing this AD to prevent failure of
a parking brake accumulator screw cap
or end cap resulting in loss of the
number 2 hydraulic system and damage
to airplane structures, which could
adversely affect the controllability of the
airplane.
DATES: This AD becomes effective
September 10, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 10, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of August 27, 2012 (77 FR
42956, July 23, 2012).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
SUMMARY:
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47544
Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7318; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
tkelley on DSK3SPTVN1PROD with RULES
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–14–04,
which applies to the specified products.
The NPRM was published in the
Federal Register on March 26, 2013 (78
FR 18257), and proposed to correct an
unsafe condition for the specified
products. Transport Canada Civil
Aviation (TCCA), which is the aviation
authority for Canada, issued Canadian
Airworthiness Directive CF–2011–29R1,
dated May 24, 2012 (the Mandatory
Continuing Airworthiness Information,
referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Seven cases of on-ground hydraulic
accumulator screw cap or end cap failure
have been experienced on CL–600–2B19
* * * aeroplanes, 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 DHC–8 aeroplanes, similar
accumulators to those installed on the CL–
600–2B19, Part Numbers (P/N)08–60162–001
and 08–60162–002 (Parking Brake
Accumulator), are installed on the aeroplanes
listed in the Applicability section of this
[TCCA] directive.
A detailed analysis of the systems and
structure in the potential line of trajectory of
a failed screw cap/end cap for the
accumulator has been conducted. It has
identified that the worst-case scenarios
would be the loss of number 2 hydraulic
system, and damage to aeroplane structures.
This [original TCCA] directive [which
corresponds to FAA AD 2012–14–04,
Amendment 39–17118 (77 FR 42956, July 23,
2012)] gives instructions to determine the
part number and serial number of the
existing parking brake accumulator, and
where applicable, replace the accumulator.
Revision 1 of this [TCCA] AD mandates the
installation of restraint devices around [all]
the parking brake accumulator end caps to
hold them in place in the event of an end cap
failure.
Uncontained failure of the parking brake
accumulator screw caps and/or end caps
VerDate Mar<15>2010
17:14 Aug 05, 2013
Jkt 229001
could result in loss of the number 2
hydraulic system, and damage to
airplane structures, and could adversely
affect the controllability of the airplane.
You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (78
FR 18257 March 26, 2013) or on the
determination of the cost to the public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
as proposed–except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
18257 March 26, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 18257
March 26, 2013).
Costs of Compliance
We estimate that this AD will affect
about 129 products of U.S. registry.
The actions that were required by AD
2012–14–04, Amendment 39–17118 (77
FR 42956, July 23, 2012), and retained
in this AD take about 2 work-hours per
product, at an average labor rate of $85
per work-hour. Based on these figures,
the estimated cost of the currently
required actions is $170 per product.
We estimate that it will take about 15
work-hours per product to comply with
the new basic requirements of this AD.
The average labor rate is $85 per workhour. Required parts will cost about
$5,302 per product. Where the service
information lists required parts costs
that are covered under warranty, we
have assumed that there will be no
charge for these parts. As we do not
control warranty coverage for affected
parties, some parties may incur costs
higher than estimated here. Based on
these figures, we estimate the cost of
this AD to the U.S. operators to be
$848,433, or $6,577 per product.
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,
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section.
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:
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2012–14–04, Amendment 39–17118 (77
FR 42956, July 23, 2012), and adding the
following new AD:
■
2013–14–09 Bombardier, Inc.: Amendment
39–17514. Docket No. FAA–2013–0209;
Directorate Identifier 2012–NM–127–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective September 10, 2013.
(b) Affected ADs
This AD supersedes AD 2012–14–04,
Amendment 39–17118 (77 FR 42956, July 23,
2012).
(c) Applicability
This AD applies to Bombardier, Inc. Model
DHC–8–101, –102, –103, –106, –201, –202,
–301, –311, and –315 airplanes, certificated
in any category, serial numbers 003 and
subsequent.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing gear.
(e) Reason
This AD was prompted by reports of
hydraulic accumulator screw cap or end cap
failure. We are issuing this AD to prevent
failure of a parking brake accumulator screw
cap or end cap resulting in loss of the
number 2 hydraulic system and damage to
airplane structures, which could adversely
affect the controllability of the airplane.
tkelley on DSK3SPTVN1PROD with RULES
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Inspection and Replacement
This paragraph restates the requirements of
paragraph (g) of AD 2012–14–04,
Amendment 39–17118 (77 FR 42956, July 23,
2012), with no changes. Within 2,000 flight
hours or 12 months after August 27, 2012
(the effective date of AD 2012–14–04),
whichever occurs first: Inspect to determine
the part number (P/N) and serial number of
the parking brake hydraulic accumulator, in
accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
8–32–170, dated February 25, 2011. A review
of airplane maintenance records is acceptable
in lieu of this inspection if the part number
and serial number of the parking brake
hydraulic accumulator can be conclusively
determined from that review.
(1) For accumulators not having P/N
0860162001 or 0860162002: No further
action is required by this paragraph.
(2) For accumulators having P/N
0860162001 or 0860162002: Before further
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17:14 Aug 05, 2013
Jkt 229001
flight, do the applicable actions specified in
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) If the serial number is listed in the table
in paragraph 3.B.(2) of Bombardier Service
Bulletin 8–32–170, dated February 25, 2011:
No further action is required by this
paragraph.
(ii) If the serial number is not listed in the
table in paragraph 3.B.(2) of Bombardier
Service Bulletin 8–32–170, dated February
25, 2011: Within 2,000 flight hours or 12
months after August 27, 2012 (the effective
date of AD 2012–14–04, Amendment 39–
17118 (77 FR 42956, July 23, 2012)),
whichever occurs first, replace the
accumulator with a new non-suspect
accumulator, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–32–172, dated March 15,
2011.
(h) Retained Parts Installation Prohibition
This paragraph restates the requirements of
paragraph (h) of AD 2012–14–04,
Amendment 39–17118 (77 FR 42956, July 23,
2012), with no changes. As of August 27,
2012 (the effective date of AD 2012–14–04),
no person may install a parking brake
accumulator, P/N 0860162001 or 0860162002
with a serial number that is not listed in the
table in paragraph 3.B.(2) of Bombardier
Service Bulletin 8–32–170, dated February
25, 2011, on any airplane.
(i) New Requirement of This AD: Install
Restraint Devices on All Airplanes
Within 6,000 flight hours or 36 months
after the effective date of this AD, whichever
occurs first: Install restraint devices around
the parking brake hydraulic accumulator end
caps by incorporating Bombardier ModSum
8Q101901, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 8–32–169, Revision A, dated
December 16, 2011.
(j) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (i) of this AD, if those
actions were performed before the effective
date of this AD using Bombardier Service
Bulletin 8–32–169, dated November 25, 2011,
which is not incorporated by reference in this
AD.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7300; fax 516–794–5531.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
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47545
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2011–29R1,
dated May 24, 2012, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov.
(2) Service information identified in this
AD that is not incorporated by reference may
be obtained at the address specified in
paragraph (m)(5) of this AD.
(m) 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 the AD specifies otherwise.
(3) The following service information was
approved for IBR on September 10, 2013.
(i) Bombardier Service Bulletin 8–32–169,
Revision A, dated December 16, 2011.
(ii) Reserved.
(4) The following service information was
approved for IBR on August 27, 2012 (77 FR
42956, July 23, 2012).
(i) Bombardier Service Bulletin 8–32–170,
dated February 25, 2011.
(ii) Bombardier Service Bulletin 8–32–172,
dated March 15, 2011.
(5) For service information identified in
this AD, contact Bombardier, Inc., Q-Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
email thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com.
(6) You may review copies of the 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.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 5,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–18771 Filed 8–5–13; 8:45 am]
BILLING CODE 4910–13–P
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]]>Agencies
[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Rules and Regulations]
[Pages 47543-47545]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18771]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0209; Directorate Identifier 2012-NM-127-AD;
Amendment 39-17514; AD 2013-14-09]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding airworthiness directive (AD) 2012-14-04 for
certain Bombardier, Inc. Model DHC-8-100, -200, and -300 series
airplanes. AD 2012-14-04 required replacing certain parking brake
accumulators. This new AD retains this requirement. This new AD also
requires installing restraint devices around the parking brake
accumulator end caps. We are issuing this AD to prevent failure of a
parking brake accumulator screw cap or end cap resulting in loss of the
number 2 hydraulic system and damage to airplane structures, which
could adversely affect the controllability of the airplane.
DATES: This AD becomes effective September 10, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
10, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of August
27, 2012 (77 FR 42956, July 23, 2012).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the
[[Page 47544]]
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 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 2012-14-04, which applies to the specified
products. The NPRM was published in the Federal Register on March 26,
2013 (78 FR 18257), and proposed to correct an unsafe condition for the
specified products. Transport Canada Civil Aviation (TCCA), which is
the aviation authority for Canada, issued Canadian Airworthiness
Directive CF-2011-29R1, dated May 24, 2012 (the Mandatory Continuing
Airworthiness Information, referred to after this as ``the MCAI''), to
correct an unsafe condition for the specified products. The MCAI
states:
Seven cases of on-ground hydraulic accumulator screw cap or end
cap failure have been experienced on CL-600-2B19 * * * aeroplanes,
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 DHC-8
aeroplanes, similar accumulators to those installed on the CL-600-
2B19, Part Numbers (P/N)08-60162-001 and 08-60162-002 (Parking Brake
Accumulator), are installed on the aeroplanes listed in the
Applicability section of this [TCCA] directive.
A detailed analysis of the systems and structure in the
potential line of trajectory of a failed screw cap/end cap for the
accumulator has been conducted. It has identified that the worst-
case scenarios would be the loss of number 2 hydraulic system, and
damage to aeroplane structures.
This [original TCCA] directive [which corresponds to FAA AD
2012-14-04, Amendment 39-17118 (77 FR 42956, July 23, 2012)] gives
instructions to determine the part number and serial number of the
existing parking brake accumulator, and where applicable, replace
the accumulator.
Revision 1 of this [TCCA] AD mandates the installation of
restraint devices around [all] the parking brake accumulator end
caps to hold them in place in the event of an end cap failure.
Uncontained failure of the parking brake accumulator screw caps and/or
end caps could result in loss of the number 2 hydraulic system, and
damage to airplane structures, and could adversely affect the
controllability of the airplane. You may obtain further information by
examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (78 FR 18257 March 26,
2013) or on the determination of the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD as proposed-except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 18257 March 26, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 18257 March 26, 2013).
Costs of Compliance
We estimate that this AD will affect about 129 products of U.S.
registry.
The actions that were required by AD 2012-14-04, Amendment 39-17118
(77 FR 42956, July 23, 2012), and retained in this AD take about 2
work-hours per product, at an average labor rate of $85 per work-hour.
Based on these figures, the estimated cost of the currently required
actions is $170 per product.
We estimate that it will take about 15 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $5,302 per
product. Where the service information lists required parts costs that
are covered under warranty, we have assumed that there will be no
charge for these parts. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of this AD to the
U.S. operators to be $848,433, or $6,577 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section.
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:
[[Page 47545]]
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)
2012-14-04, Amendment 39-17118 (77 FR 42956, July 23, 2012), and adding
the following new AD:
2013-14-09 Bombardier, Inc.: Amendment 39-17514. Docket No. FAA-
2013-0209; Directorate Identifier 2012-NM-127-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective September
10, 2013.
(b) Affected ADs
This AD supersedes AD 2012-14-04, Amendment 39-17118 (77 FR
42956, July 23, 2012).
(c) Applicability
This AD applies to Bombardier, Inc. Model DHC-8-101, -102, -103,
-106, -201, -202, -301, -311, and -315 airplanes, certificated in
any category, serial numbers 003 and subsequent.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
gear.
(e) Reason
This AD was prompted by reports of hydraulic accumulator screw
cap or end cap failure. We are issuing this AD to prevent failure of
a parking brake accumulator screw cap or end cap resulting in loss
of the number 2 hydraulic system and damage to airplane structures,
which could adversely affect the controllability of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Inspection and Replacement
This paragraph restates the requirements of paragraph (g) of AD
2012-14-04, Amendment 39-17118 (77 FR 42956, July 23, 2012), with no
changes. Within 2,000 flight hours or 12 months after August 27,
2012 (the effective date of AD 2012-14-04), whichever occurs first:
Inspect to determine the part number (P/N) and serial number of the
parking brake hydraulic accumulator, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 8-32-170,
dated February 25, 2011. A review of airplane maintenance records is
acceptable in lieu of this inspection if the part number and serial
number of the parking brake hydraulic accumulator can be
conclusively determined from that review.
(1) For accumulators not having P/N 0860162001 or 0860162002: No
further action is required by this paragraph.
(2) For accumulators having P/N 0860162001 or 0860162002: Before
further flight, do the applicable actions specified in paragraphs
(g)(2)(i) and (g)(2)(ii) of this AD.
(i) If the serial number is listed in the table in paragraph
3.B.(2) of Bombardier Service Bulletin 8-32-170, dated February 25,
2011: No further action is required by this paragraph.
(ii) If the serial number is not listed in the table in
paragraph 3.B.(2) of Bombardier Service Bulletin 8-32-170, dated
February 25, 2011: Within 2,000 flight hours or 12 months after
August 27, 2012 (the effective date of AD 2012-14-04, Amendment 39-
17118 (77 FR 42956, July 23, 2012)), whichever occurs first, replace
the accumulator with a new non-suspect accumulator, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
8-32-172, dated March 15, 2011.
(h) Retained Parts Installation Prohibition
This paragraph restates the requirements of paragraph (h) of AD
2012-14-04, Amendment 39-17118 (77 FR 42956, July 23, 2012), with no
changes. As of August 27, 2012 (the effective date of AD 2012-14-
04), no person may install a parking brake accumulator, P/N
0860162001 or 0860162002 with a serial number that is not listed in
the table in paragraph 3.B.(2) of Bombardier Service Bulletin 8-32-
170, dated February 25, 2011, on any airplane.
(i) New Requirement of This AD: Install Restraint Devices on All
Airplanes
Within 6,000 flight hours or 36 months after the effective date
of this AD, whichever occurs first: Install restraint devices around
the parking brake hydraulic accumulator end caps by incorporating
Bombardier ModSum 8Q101901, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 8-32-169, Revision A,
dated December 16, 2011.
(j) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(i) of this AD, if those actions were performed before the effective
date of this AD using Bombardier Service Bulletin 8-32-169, dated
November 25, 2011, which is not incorporated by reference in this
AD.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), ANE-170, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the ACO, send it to ATTN: Program Manager, Continuing
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531.
Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the
local flight standards district office/certificate holding district
office. The AMOC approval letter must specifically reference this
AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Canadian Airworthiness Directive CF-2011-29R1, dated May 24,
2012, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov.
(2) Service information identified in this AD that is not
incorporated by reference may be obtained at the address specified
in paragraph (m)(5) of this AD.
(m) 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 the AD specifies otherwise.
(3) The following service information was approved for IBR on
September 10, 2013.
(i) Bombardier Service Bulletin 8-32-169, Revision A, dated
December 16, 2011.
(ii) Reserved.
(4) The following service information was approved for IBR on
August 27, 2012 (77 FR 42956, July 23, 2012).
(i) Bombardier Service Bulletin 8-32-170, dated February 25,
2011.
(ii) Bombardier Service Bulletin 8-32-172, dated March 15, 2011.
(5) For service information identified in this AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000;
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet
https://www.bombardier.com.
(6) You may review copies of the 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.
(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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on July 5, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-18771 Filed 8-5-13; 8:45 am]
BILLING CODE 4910-13-P
