Airworthiness Directives; Bombardier, Inc. Airplanes, 51055-51058 [2013-20109]
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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations
on both balance weights is outside the date
range of January 1, 1996, and December 31,
2005, then no further action is required for
this AD.
(iii) For a replaced balance weight, if you
cannot positively identify the date of
purchase of a balance weight from Hawker
Beechcraft Corporation (also known as
Raytheon Aircraft Company or Beechcraft
Corporation), then you must complete all of
the actions in paragraph (h) and (i), all
subparagraphs, as applicable in this AD.
(2) For Model 58 airplanes, all serial
numbers (except TH–1768 through TH–
2110), and Models 58TC, 58P, 95–C55, E55,
and 56TC airplanes, all serial numbers,
before further flight after September 24, 2013
(the effective date of this AD) review the
airplane maintenance records to determine if
the elevator balance weights have ever been
replaced. An owner/operator (pilot) holding
at least a private pilot certificate is allowed
to do this action.
(i) If, as a result of the maintenance records
check, you positively identify that both of the
elevator balance weights have never been
replaced, then no further action is required
for this AD. An owner/operator (pilot)
holding at least a private pilot certificate is
allowed to do this action.
(ii) If, as a result of the maintenance
records check, you identify that one or both
of the balance weights have been replaced
and you can positively identify by means of
an Airworthiness Approval Tag (FAA Form
8130–3) or other positive form of parts
identification such as a shipping ticket,
invoice, or direct ship authority letter, that
the purchase date from Hawker Beechcraft
Corporation (also known as Raytheon
Aircraft Company or Beechcraft Corporation)
is outside the date range of January 1, 1996,
and December 31, 2005, then no further
action is required for this AD.
(iii) If you cannot positively identify the
date of purchase of an aircraft balance weight
from Hawker Beechcraft Corporation (also
known as Raytheon Aircraft Company or
Beechcraft Corporation), then you must
perform all of the actions in paragraph (h)
and (i), all subparagraphs, as applicable in
this AD.
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(h) Inspection of Elevator Balance Weight
Before further flight after September 24,
2013 (the effective date of this AD) and
thereafter at intervals not to exceed 100 hours
time-in-service (TIS) until the replacement
required by this AD is done, inspect the
elevator balance weights for looseness,
failure, and/or working (smoking) fasteners
and inserts following the Accomplishment
Instructions paragraph 3.A in Hawker
Beechcraft Mandatory Service Bulletin SB
55–4089, Revision 1, dated February, 2012.
(i) Replacement of Elevator Balance Weight
(1) Replace the defective elevator balance
weight with an airworthy balance weight as
specified in the Accomplishment
Instructions paragraph 3.A in Hawker
Beechcraft Mandatory Service Bulletin SB
55–4089, Revision 1, dated February, 2012, at
either paragraph (i)(1)(i) or (i)(1)(ii) of this
AD, whichever occurs first:
(i) Before further flight after any inspection
required by paragraph (h) of this AD where
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any looseness, failure, and/or working
(smoking) fasteners and inserts are found; or
(ii) Within the next 200 hours TIS after
September 24, 2013 (the effective date of this
AD).
(2) Replacement of elevator balance
weights with airworthy elevator balance
weights terminates the 100-hour inspection
requirement in paragraph (h) of this AD.
(3) As of September 24, 2013 (the effective
date of this AD), do not install P/N 96–
610022, P/N 96–61022–5, P/N 96–610022–7,
and P/N 96–610022–9 elevator balance
weight assemblies, if originally purchased
from Hawker Beechcraft Corporation (also
known as Raytheon Aircraft Company or
Beechcraft Corporation) between January 1,
1996, and December 31, 2005, on any
airplane.
(j) Special Flight Permit
Special flight is permitted with the
following limitations: Maximum structural
cruising speed (Vno) = Design Speed for
maximum gust intensity (Vb) = 195 Knots
Calibrated Airspeed (KCAS), or
Vno=Vb=195KCAS. This special flight is not
allowed into known turbulence, and the
duration of this flight should not be more
than a total of 10 hours TIS.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Wichita Aircraft
Certification Office (ACO), 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 the
attention of the person identified in the
Related Information section of this AD.
(2) 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.
(l) Related Information
For more information about this AD,
contact T. N. Baktha, Senior Aerospace
Engineer, FAA, Wichita ACO, 1801 Airport
Road, Room 100, Wichita, Kansas 67209;
telephone: (316) 946–4155; fax: (316) 946–
4107; email: t.n.baktha@faa.gov.
(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.
(i) Hawker Beechcraft Mandatory Service
Bulletin SB 55–4089, Revision 1, dated
February, 2012.
(ii) Reserved.
(3) For Beechcraft Corporation and Hawker
Beechcraft Corporation service information
identified in this AD, contact Beechcraft
Corporation, B091–A04, 10511 E. Central
Ave., Wichita, Kansas 67206; telephone: 1
(800) 429–5372 or (316) 676–3140; fax: (316)
PO 00000
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51055
676–8027; email: tmdc@beechcraft.com; or
Internet: https://www.beechcraft.com/
customer_support/technical_and_field_
support/.
(4) You may view this service information
at FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Kansas City, Missouri, on July 25,
2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2013–20098 Filed 8–19–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0367; Directorate
Identifier 2012–NM–177–AD; Amendment
39–17546; AD 2013–16–08]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model CL–600–2C10
(Regional Jet Series 700, 701, & 702)
airplanes, Model CL–600–2D15
(Regional Jet Series 705) airplanes, and
Model CL–600–2D24 (Regional Jet
Series 900) airplanes. This AD was
prompted by a report of corrosion of the
components of the main landing gear
(MLG) retraction actuator found in
service; the corrosion was found at the
interface of the rod end and the piston,
and at the bracket and related pins. This
AD requires inspection of the MLG
retraction actuator components;
corrective actions if necessary; and, for
certain retraction actuators, installation
of a new jam nut. We are issuing this
AD to prevent disconnection of the MLG
retraction actuator, which could result
in extension of the MLG without
damping, and consequent structural
damage and collapse of the MLG during
landing.
DATES: This AD is effective September
24, 2013.
SUMMARY:
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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of September 24, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov; or in person at
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 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 include an AD that would
apply to the specified products. The
NPRM published in the Federal
Register on May 10, 2013 (78 FR 27318).
The NPRM proposed to correct an
unsafe condition for the specified
products.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2011–36R1,
dated October 3, 2012, the Mandatory
Continuing Airworthiness Information
(MCAI), to correct an unsafe condition
for the specified products. The MCAI
states:
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Corrosion of the main landing gear (MLG)
retraction actuator components was found inservice, either at the interface of the rod end
and the piston or at the bracket and its
related pins. This can cause the MLG
retraction actuator to disconnect, leading to
an MLG extension without damping, and a
potential for MLG structural damage and
possible collapse during landing.
This [Canadian] AD mandates the
inspection and rectification [corrective
action] of the MLG retraction actuator
components.
This revision is to mandate [, for certain
MLG retraction actuators,] the installation of
the new retraction actuator jam nut. This
revision also corrects the background
information and updates Service Bulletin
(SB) references.
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 27318, May 10, 2013) or on the
determination of the cost to the public.
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Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
as proposed.
Costs of Compliance
Based on the service information, we
estimate that this AD affects about 391
products of U.S. registry. We also
estimate that it takes up to 16 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Required parts will cost about $1,018
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 on U.S. operators to be up to
$929,798, or up to $2,378 per product.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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:
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(1) is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
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 MCAI, 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:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2013–16–08 Bombardier, Inc.: Amendment
39–17546; Docket No. FAA–2013–0367;
Directorate Identifier 2012–NM–177–AD.
(a) Effective Date
This AD becomes effective September 24,
2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes specified
in paragraphs (c)(1) and (c)(2) of this AD,
certificated in any category.
(1) Bombardier, Inc. Model CL–600–2C10
(Regional Jet Series 700, 701, & 702)
airplanes, serial numbers 10002 and
subsequent.
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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations
(2) Bombardier, Inc. Model CL–600–2D15
(Regional Jet Series 705) and CL–600–2D24
(Regional Jet Series 900) airplanes, serial
numbers 15001 and subsequent.
(d) Subject
Air Transport Association (ATA) of
America Code 32: Landing gear.
(e) Reason
This AD was prompted by a report of
corrosion of the components of the main
landing gear (MLG) retraction actuator found
in service; the corrosion was found at the
interface of the rod end and the piston, and
at the bracket and related pins. We are
issuing this AD to prevent disconnection of
the MLG retraction actuator, which could
result in extension of the MLG without
damping, and consequent structural damage
and collapse of the MLG during landing.
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(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) Inspection of the MLG Retraction
Actuator and Corrective Actions
For any airplane with an MLG retraction
actuator assembly having any part number
and serial number identified in paragraph
1.A., Effectivity, of Bombardier Service
Bulletin 670BA–32–031, Revision C, dated
April 17, 2012, except airplanes on which
modification status ‘‘32–64’’ is marked on the
identification plate: At the applicable time
specified in paragraph (g)(1) or (g)(2) of this
AD, perform a detailed inspection of the
retraction actuator assembly for evidence of
corrosion and security of the jam nut, as
applicable, in accordance with Part A of the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–32–031, Revision C,
dated April 17, 2012; and Goodrich Service
Bulletin 49600–32–63 R1, dated May 17,
2011. If any corrosion or unsecured jam nut
is found, before further flight, replace the
retract actuator with a new or serviceable
retract actuator; and install the retract
actuator in accordance with Part A of the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–32–031, Revision C,
dated April 17, 2012. Repeat the inspection
at intervals not to exceed 1,200 flight hours
or 12 months, whichever occurs first.
(1) For MLG retraction actuator assemblies
on which, as of the effective date of this AD,
8,000 or more total flight hours have
accumulated since new or since overhaul, or
have been in service for more than 4 years
since new or since overhaul: Inspect within
1,200 flight hours or 12 months after the
effective date of this AD, whichever occurs
first.
(2) For MLG retraction actuator assemblies
on which, as of the effective date of this AD,
less than 8,000 total flight hours have
accumulated since new or since overhaul,
and have been in service for 4 years or less
since new or since overhaul: Inspect before
the accumulation of 9,200 total flight hours
on the MLG retraction actuator assembly
since new or since overhaul or within 5 years
in service since new or since overhaul,
whichever occurs first.
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(h) Inspection of MLG Retraction Actuator
Bracket and Related Pins, and Corrective
Actions
For any airplane with an MLG dressed
shock strut having any part number and
serial number identified in paragraph 1.A.,
Effectivity, of Bombardier Service Bulletin
670BA–32–033, Revision B, dated June 26,
2012: Within 4,400 flight hours or 24 months
after the effective date of this AD, whichever
occurs first, perform a detailed inspection of
the retract actuator bracket assembly,
associated pins, and the mating lugs on the
outer cylinder for evidence of corrosion, in
accordance with Bombardier Service Bulletin
670BA–32–033, Revision B, dated June 26,
2012; and Goodrich Service Bulletin 49000–
32–46 R2, dated November 11, 2011. Do all
applicable corrective actions before further
flight (i.e., replace retract actuator bracket
assembly and pins, or outer cylinder lugs, as
applicable).
dated April 17, 2012, unless that retraction
actuator assembly has been inspected as
specified in paragraph (g) of this AD, and all
applicable corrective actions (i.e.,
replacement of the retract actuator) specified
in paragraph (g) of this AD have been done.
Repeat the inspection specified in paragraph
(g) of this AD thereafter at the intervals
specified in paragraph (g) of this AD.
(2) As of the effective date of this AD, no
person may install on any airplane an MLG
retraction actuator assembly having any part
number and serial number identified in
paragraph 1.A., Effectivity, of Bombardier
Service Bulletin 670BA–32–033, Revision B,
dated June 26, 2012, unless that retraction
actuator assembly has been inspected and all
applicable corrective actions have been done,
in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin
670BA–32–033, Revision B, dated June 26,
2012.
(i) Installation of New Jam Nut
For any airplane with an MLG retraction
actuator assembly having any part number
and serial number identified in paragraph
1.A., Effectivity, of Bombardier Service
Bulletin 670BA–32–031, Revision C, dated
April 17, 2012, except airplanes on which
modification status ‘‘32–64’’ is marked on the
identification plate: Within 20,000 flight
hours or 10 years after the effective date of
this AD, whichever occurs first, install a new
jam nut having part number 49606–5, in
accordance with Part B of the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–32–031, Revision C,
dated April 17, 2012; and Goodrich Service
Bulletin 49600–32–64 R3, dated December
15, 2011.
(l) 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, New York
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.
(j) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraphs (g) and (i) of
this AD, if those actions were performed
before the effective date of this AD using the
service information specified in paragraphs
(j)(1)(i), (j)(1)(ii), or (j)(1)(iii) of this AD,
which is not incorporated by reference in this
AD.
(i) Bombardier Service Bulletin 670BA–32–
031, dated March 14, 2011.
(ii) Bombardier Service Bulletin 670BA–
32–031, Revision A, dated June 9, 2011.
(iii) Bombardier Service Bulletin 769BA–
32–031, Revision B, dated July 29, 2011.
(2) This paragraph provides credit for the
actions required by paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using the service
information specified in paragraph (j)(2)(i) or
(j)(2)(ii) of this AD, which is not incorporated
by reference in this AD.
(i) Bombardier Service Bulletin 670BA–32–
033, dated March 14, 2011.
(ii) Bombardier Service Bulletin 670BA–
32–033, Revision A, dated July 29, 2011.
(k) Parts Installation Limitations
(1) As of the effective date of this AD, no
person may install on any airplane an MLG
retraction actuator assembly having any part
number and serial number identified in
paragraph 1.A., Effectivity, of Bombardier
Service Bulletin 670BA–32–031, Revision C,
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(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information Canadian
Airworthiness Directive CF–2011–36R1,
dated October 3, 2012, for related
information, which can 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 (n)(3) of this AD.
(n) 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.
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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Rules and Regulations
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Bombardier Service Bulletin 670BA–32–
031, Revision C, dated April 17, 2012.
(ii) Bombardier Service Bulletin 670BA–
32–033, Revision B, dated June 26, 2012.
(iii) Goodrich Service Bulletin 49000–32–
46 R2, dated November 11, 2011.
(iv) Goodrich Service Bulletin 49600–32–
63 R1, dated May 17, 2011.
(v) Goodrich Service Bulletin 49600–32–64
R3, dated December 15, 2011.
(3) For Bombardier service information
identified in this AD, contact Bombardier,
ˆ
Inc., 400 Cote-Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone 514–
855–5000; fax 514–855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com.
(4) For Goodrich service information
identified in this AD, contact Goodrich
Corporation, Landing Gear, 1400 South
Service Road, West Oakville L6L 5Y7,
Ontario, Canada; telephone 905–825–1568;
email jean.breed@goodrich.com; Internet
https://www.goodrich.com/TechPubs.
(5) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(6) 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 31,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–20109 Filed 8–19–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1038; Directorate
Identifier 2011–NM–166–AD; Amendment
39–17537; AD 2013–15–21]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
We are superseding
airworthiness directive (AD) 2004–13–
06 for certain Airbus Model A319 and
A320 series airplanes. AD 2004–13–06
SUMMARY:
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required repetitive detailed inspections
to detect cracks in the keel beam side
panels, and repair if necessary. This
new AD requires repetitive eddy current
inspections for cracking in the keel
beam side panels, and corrective actions
if necessary. This AD was prompted by
reports of cracks on the side panels of
the keel beams. We are issuing this AD
to detect and correct fatigue cracks on
the side panels of the keel beams, which
could result in reduced structural
integrity of the airplane.
DATES: This AD becomes effective
September 24, 2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 24, 2013.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–1405;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. The
NPRM was published in the Federal
Register on October 4, 2012 (77 FR
60655), and proposed to supersede AD
2004–13–06, Amendment 39–13688 (69
FR 38818, June 29, 2004). The NPRM
proposed to correct an unsafe condition
for the specified products. The
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2011–0134,
dated July 15, 2011 (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
During certification structural fatigue tests,
several cases of structural damage (cracks)
have been found on keel beam side panels.
Cracks were observed on both sides of the
keel beam around the rivets below the center
wing box between frame (FR) 40 and FR 42,
and in part of the area of the upper elliptical
cut out forward of FR 41.
This type of damage, if not detected and
repaired, would adversely affect the
structural integrity of the aeroplane.
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
To address this unsafe condition, DGAC
´ ´
[Direction Generale de l’Aviation Civile]
France issued AD 2003–146 [which
corresponds to FAA AD 2004–13–06,
Amendment 39–13688 (69 FR 38818, June
29, 2004)] to require repetitive detailed
inspections of those two areas and corrective
actions, depending on findings.
Prompted by reported access difficulties
and to allow extension of the interval
between two consecutive inspections, Airbus
validated an Eddy current Non-Destructive
Test (NDT) inspection to replace the detailed
inspection.
For the reasons described above, this
[EASA] AD, which supersedes DGAC France
AD 2003–146, requires repetitive Eddycurrent NDT inspections for cracks in the
affected areas of the keel beam side panel
below the center wing box and corrective
actions [repair], depending on findings.
You may obtain further information by
examining the MCAI in the AD docket.
Revised Service Information
The NPRM (77 FR 60655, October 4,
2012) referred to Airbus Mandatory
Service Bulletin A320–53–1060,
Revision 02, dated November 30, 2010,
as the appropriate source of service
information for the proposed actions.
Airbus has revised this service
information. We have reviewed Airbus
Mandatory Service Bulletin A320–53–
1060, Revision 04, dated September 13,
2012, which includes an updated
effectivity, an added illustration,
amended job set-up and close-up
procedures, and minor changes, but
adds no accomplishment instruction
procedures.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Request To Revise Referenced Service
Information
Jetblue Airways requested that we
revise the NPRM (77 FR 60655, October
4, 2012) to reference the latest service
information.
We agree. As explained above, we
reviewed Airbus Mandatory Service
Bulletin A320–53–1060, Revision 04,
dated September 13, 2012. We have
revised this final rule to refer to Airbus
Mandatory Service Bulletin A320–53–
1060, Revision 04, dated September 13,
2012; to add new paragraph (i) to allow
credit for actions accomplished before
the effective date of this AD using
Airbus Mandatory Service Bulletin
A320–53–1060, Revision 02, dated
November 30, 2010, or Revision 03,
dated January 20, 2012; and to reidentify subsequent paragraphs.
E:\FR\FM\20AUR1.SGM
20AUR1
]]>Agencies
[Federal Register Volume 78, Number 161 (Tuesday, August 20, 2013)]
[Rules and Regulations]
[Pages 51055-51058]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-20109]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0367; Directorate Identifier 2012-NM-177-AD;
Amendment 39-17546; AD 2013-16-08]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, &
702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes,
and Model CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was
prompted by a report of corrosion of the components of the main landing
gear (MLG) retraction actuator found in service; the corrosion was
found at the interface of the rod end and the piston, and at the
bracket and related pins. This AD requires inspection of the MLG
retraction actuator components; corrective actions if necessary; and,
for certain retraction actuators, installation of a new jam nut. We are
issuing this AD to prevent disconnection of the MLG retraction
actuator, which could result in extension of the MLG without damping,
and consequent structural damage and collapse of the MLG during
landing.
DATES: This AD is effective September 24, 2013.
[[Page 51056]]
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 24,
2013.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at 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 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 include an AD that would apply to the specified products.
The NPRM published in the Federal Register on May 10, 2013 (78 FR
27318). The NPRM proposed to correct an unsafe condition for the
specified products.
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2011-36R1, dated October 3, 2012, the Mandatory Continuing
Airworthiness Information (MCAI), to correct an unsafe condition for
the specified products. The MCAI states:
Corrosion of the main landing gear (MLG) retraction actuator
components was found in-service, either at the interface of the rod
end and the piston or at the bracket and its related pins. This can
cause the MLG retraction actuator to disconnect, leading to an MLG
extension without damping, and a potential for MLG structural damage
and possible collapse during landing.
This [Canadian] AD mandates the inspection and rectification
[corrective action] of the MLG retraction actuator components.
This revision is to mandate [, for certain MLG retraction
actuators,] the installation of the new retraction actuator jam nut.
This revision also corrects the background information and updates
Service Bulletin (SB) references.
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 27318, May 10,
2013) or on the determination of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed.
Costs of Compliance
Based on the service information, we estimate that this AD affects
about 391 products of U.S. registry. We also estimate that it takes up
to 16 work-hours per product to comply with the basic requirements of
this AD. The average labor rate is $85 per work-hour. Required parts
will cost about $1,018 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 on U.S. operators to be up to $929,798, or up to $2,378
per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
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 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 MCAI, 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:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2013-16-08 Bombardier, Inc.: Amendment 39-17546; Docket No. FAA-
2013-0367; Directorate Identifier 2012-NM-177-AD.
(a) Effective Date
This AD becomes effective September 24, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes specified in paragraphs (c)(1)
and (c)(2) of this AD, certificated in any category.
(1) Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700,
701, & 702) airplanes, serial numbers 10002 and subsequent.
[[Page 51057]]
(2) Bombardier, Inc. Model CL-600-2D15 (Regional Jet Series 705)
and CL-600-2D24 (Regional Jet Series 900) airplanes, serial numbers
15001 and subsequent.
(d) Subject
Air Transport Association (ATA) of America Code 32: Landing
gear.
(e) Reason
This AD was prompted by a report of corrosion of the components
of the main landing gear (MLG) retraction actuator found in service;
the corrosion was found at the interface of the rod end and the
piston, and at the bracket and related pins. We are issuing this AD
to prevent disconnection of the MLG retraction actuator, which could
result in extension of the MLG without damping, and consequent
structural damage and collapse of the MLG during landing.
(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) Inspection of the MLG Retraction Actuator and Corrective Actions
For any airplane with an MLG retraction actuator assembly having
any part number and serial number identified in paragraph 1.A.,
Effectivity, of Bombardier Service Bulletin 670BA-32-031, Revision
C, dated April 17, 2012, except airplanes on which modification
status ``32-64'' is marked on the identification plate: At the
applicable time specified in paragraph (g)(1) or (g)(2) of this AD,
perform a detailed inspection of the retraction actuator assembly
for evidence of corrosion and security of the jam nut, as
applicable, in accordance with Part A of the Accomplishment
Instructions of Bombardier Service Bulletin 670BA-32-031, Revision
C, dated April 17, 2012; and Goodrich Service Bulletin 49600-32-63
R1, dated May 17, 2011. If any corrosion or unsecured jam nut is
found, before further flight, replace the retract actuator with a
new or serviceable retract actuator; and install the retract
actuator in accordance with Part A of the Accomplishment
Instructions of Bombardier Service Bulletin 670BA-32-031, Revision
C, dated April 17, 2012. Repeat the inspection at intervals not to
exceed 1,200 flight hours or 12 months, whichever occurs first.
(1) For MLG retraction actuator assemblies on which, as of the
effective date of this AD, 8,000 or more total flight hours have
accumulated since new or since overhaul, or have been in service for
more than 4 years since new or since overhaul: Inspect within 1,200
flight hours or 12 months after the effective date of this AD,
whichever occurs first.
(2) For MLG retraction actuator assemblies on which, as of the
effective date of this AD, less than 8,000 total flight hours have
accumulated since new or since overhaul, and have been in service
for 4 years or less since new or since overhaul: Inspect before the
accumulation of 9,200 total flight hours on the MLG retraction
actuator assembly since new or since overhaul or within 5 years in
service since new or since overhaul, whichever occurs first.
(h) Inspection of MLG Retraction Actuator Bracket and Related Pins, and
Corrective Actions
For any airplane with an MLG dressed shock strut having any part
number and serial number identified in paragraph 1.A., Effectivity,
of Bombardier Service Bulletin 670BA-32-033, Revision B, dated June
26, 2012: Within 4,400 flight hours or 24 months after the effective
date of this AD, whichever occurs first, perform a detailed
inspection of the retract actuator bracket assembly, associated
pins, and the mating lugs on the outer cylinder for evidence of
corrosion, in accordance with Bombardier Service Bulletin 670BA-32-
033, Revision B, dated June 26, 2012; and Goodrich Service Bulletin
49000-32-46 R2, dated November 11, 2011. Do all applicable
corrective actions before further flight (i.e., replace retract
actuator bracket assembly and pins, or outer cylinder lugs, as
applicable).
(i) Installation of New Jam Nut
For any airplane with an MLG retraction actuator assembly having
any part number and serial number identified in paragraph 1.A.,
Effectivity, of Bombardier Service Bulletin 670BA-32-031, Revision
C, dated April 17, 2012, except airplanes on which modification
status ``32-64'' is marked on the identification plate: Within
20,000 flight hours or 10 years after the effective date of this AD,
whichever occurs first, install a new jam nut having part number
49606-5, in accordance with Part B of the Accomplishment
Instructions of Bombardier Service Bulletin 670BA-32-031, Revision
C, dated April 17, 2012; and Goodrich Service Bulletin 49600-32-64
R3, dated December 15, 2011.
(j) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraphs (g) and (i) of this AD, if those actions were performed
before the effective date of this AD using the service information
specified in paragraphs (j)(1)(i), (j)(1)(ii), or (j)(1)(iii) of
this AD, which is not incorporated by reference in this AD.
(i) Bombardier Service Bulletin 670BA-32-031, dated March 14,
2011.
(ii) Bombardier Service Bulletin 670BA-32-031, Revision A, dated
June 9, 2011.
(iii) Bombardier Service Bulletin 769BA-32-031, Revision B,
dated July 29, 2011.
(2) This paragraph provides credit for the actions required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using the service information specified in
paragraph (j)(2)(i) or (j)(2)(ii) of this AD, which is not
incorporated by reference in this AD.
(i) Bombardier Service Bulletin 670BA-32-033, dated March 14,
2011.
(ii) Bombardier Service Bulletin 670BA-32-033, Revision A, dated
July 29, 2011.
(k) Parts Installation Limitations
(1) As of the effective date of this AD, no person may install
on any airplane an MLG retraction actuator assembly having any part
number and serial number identified in paragraph 1.A., Effectivity,
of Bombardier Service Bulletin 670BA-32-031, Revision C, dated April
17, 2012, unless that retraction actuator assembly has been
inspected as specified in paragraph (g) of this AD, and all
applicable corrective actions (i.e., replacement of the retract
actuator) specified in paragraph (g) of this AD have been done.
Repeat the inspection specified in paragraph (g) of this AD
thereafter at the intervals specified in paragraph (g) of this AD.
(2) As of the effective date of this AD, no person may install
on any airplane an MLG retraction actuator assembly having any part
number and serial number identified in paragraph 1.A., Effectivity,
of Bombardier Service Bulletin 670BA-32-033, Revision B, dated June
26, 2012, unless that retraction actuator assembly has been
inspected and all applicable corrective actions have been done, in
accordance with the Accomplishment Instructions of Bombardier
Service Bulletin 670BA-32-033, Revision B, dated June 26, 2012.
(l) 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, New York 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.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
Canadian Airworthiness Directive CF-2011-36R1, dated October 3,
2012, for related information, which can 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 (n)(3) of this AD.
(n) 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.
[[Page 51058]]
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Bombardier Service Bulletin 670BA-32-031, Revision C, dated
April 17, 2012.
(ii) Bombardier Service Bulletin 670BA-32-033, Revision B, dated
June 26, 2012.
(iii) Goodrich Service Bulletin 49000-32-46 R2, dated November
11, 2011.
(iv) Goodrich Service Bulletin 49600-32-63 R1, dated May 17,
2011.
(v) Goodrich Service Bulletin 49600-32-64 R3, dated December 15,
2011.
(3) For Bombardier service information identified in this AD,
contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet https://www.bombardier.com.
(4) For Goodrich service information identified in this AD,
contact Goodrich Corporation, Landing Gear, 1400 South Service Road,
West Oakville L6L 5Y7, Ontario, Canada; telephone 905-825-1568;
email jean.breed@goodrich.com; Internet https://www.goodrich.com/TechPubs.
(5) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221.
(6) 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 31, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-20109 Filed 8-19-13; 8:45 am]
BILLING CODE 4910-13-P
