Airworthiness Directives; Bombardier, Inc. Airplanes, 5730-5733 [2012-2619]
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Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules
(e) Reason
This AD was prompted by reports of an
inoperative fire shut-off valve (FSOV) as a
result of damage due to over-length of the
bonding lead. We are issuing this AD to
detect and correct contact or chafing of wires
and bonding leads which, if not detected,
could be a source of sparks in the wing
trailing edge, and could lead to an
uncontrolled engine fire.
(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 FSOV Bonding Leads
Within 4,500 flight hours or 30 months
after the effective date of this AD, whichever
occurs first: Do a one-time detailed
inspection for length of the FSOV bonding
leads, and for contact or chafing of the wires
located on left hand (LH) side and right-hand
(RH) side of the wing rear spar, in accordance
with Accomplishment Instructions of the
Airbus Mandatory Service Bulletin A300–24–
0106, dated July 9, 2010 (for Model A300
series airplanes); or Airbus Mandatory
Service Bulletin A300–24–6108, dated July 9,
2010 (for Model A300–600 series airplanes).
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–2125; fax (425)
227–1149.
(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
Refer to MCAI European Aviation Safety
Agency (EASA) Airworthiness Directive
2011–0084, dated May 24, 2011; and the
service information identified in paragraphs
(l)(1), and (l)(2) of this AD; for related
information.
(1) Airbus Mandatory Service Bulletin
A300–24–0106, dated July 9, 2010.
(2) Airbus Mandatory Service Bulletin
A300–24–6108, dated July 9, 2010.
(h) Corrective Action for FSOV Bonding
Leads
If, during the inspection required by
paragraph (g) of this AD, the length of the
bonding lead(s) is more than 80 mm (3.15
inches), before further flight, replace the
bonding lead(s) with a new bonding lead
having a length equal to 80 mm (3.15 inches),
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A300–24–0106, dated July 9, 2010
(for Model A300 series airplanes); or Airbus
Mandatory Service Bulletin A300–24–6108,
dated July 9, 2010 (for Model A300–600
series airplanes).
Issued in Renton, Washington, on January
12, 2012.
Michael J. Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
(i) Repair of the Wires of the LH and RH
Sides
If, during the inspection required by
paragraph (g) of this AD, contact(s) or
chafing(s) of the wires is found, repair the
wires in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300–24–0106,
dated July 9, 2010 (for Model A300 series
airplanes); or Airbus Mandatory Service
Bulletin A300–24–6108, dated July 9, 2010
(for Model A300–600 series airplanes).
[Docket No. FAA–2012–0042; Directorate
Identifier 2011–NM–154–AD]
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(j) Parts Installation
As of the effective date of this AD, no
person may install any bonding lead longer
than 80 mm (3.15 inches), located between
LH/RH engine hydraulic FSOV and wing rear
spar in the zones 575/675 on any airplane.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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
VerDate Mar<15>2010
18:22 Feb 03, 2012
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[FR Doc. 2012–2625 Filed 2–3–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain Bombardier, Inc.
Model CL–600–2C10 (Regional Jet
Series 700, 701 & 702), CL–600–2D15
(Regional Jet Series 705), and CL–600–
2D24 (Regional Jet Series 900) airplanes.
The existing AD currently requires a
one-time inspection of the main landing
gear (MLG) shock strut assemblies for
part and serial numbers; for certain
MLG shock strut assemblies, a one-time
inspection of the torque link apex joint,
and corrective actions if necessary; and,
SUMMARY:
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for certain MLG shock strut assemblies,
replacement or rework of the apex nut.
Since we issued that AD, we have
determined that part and serial numbers
for MLG shock strut assemblies for
Model CL–600–2D15 and CL–600–2D24
airplanes were inadvertently omitted
from certain requirements of the
existing AD. This proposed AD would
continue to require the actions in the
existing AD, and would add the
previously omitted part and serial
numbers. We are proposing this AD to
detect and correct improper assembly
and damage of the MLG torque link
apex joint, which could cause heavy
vibration during landing, consequent
damage to MLG components, and
subsequent collapse of the MLG.
DATES: We must receive comments on
this proposed AD by March 22, 2012.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Bombardier,
Inc., 400 Cote-Vertu Road West, Dorval,
Quebec H4S 1Y9, Canada; phone: 514–
855–5000; fax: 514–855–7401; email:
thd.crj@aero.bombardier.com; Internet:
https://www.bombardier.com. You may
review copies of the referenced 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.
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
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Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules
FOR FURTHER INFORMATION CONTACT:
Stephen Kowalski, Aerospace Engineer,
Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; phone: (516) 228–
7327; fax: (516) 794–5531; email:
Stephen.Kowalski@faa.gov.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2012–0042; Directorate Identifier
2011–NM–154–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On March 23, 2011, we issued AD
2011–08–04, Amendment 39–16654 (76
FR 20498, April 13, 2011). That AD
required actions intended to address an
unsafe condition on Bombardier, Inc.
Model CL–600–2C10 (Regional Jet
Series 700, 701 & 702), CL–600–2D15
(Regional Jet Series 705), and CL–600–
2D24 (Regional Jet Series 900) airplanes.
Since we issued AD 2011–08–04,
Amendment 39–16654 (76 FR 20498,
April 13, 2011), we have determined
that part and serial numbers for main
landing gear (MLG) shock strut
assemblies for Model CL–600–2D15
(Regional Jet Series 705) airplanes and
Model CL–600–2D24 (Regional Jet
Series 900) airplanes were inadvertently
omitted from paragraphs (g) and (h) of
that AD. As a result, operators could be
inspecting for part and serial numbers
which they do not have, and would,
therefore, not be required to accomplish
the actions intended to correct the
identified unsafe condition on those
airplanes. Therefore, we have removed
airplanes identified in paragraph (c)(2)
of this AD from the requirements of
paragraphs (g), (h), and (i) of this AD.
We have added new requirements for
those airplanes to inspect for the
appropriate part numbers and serial
numbers, and to do all applicable
inspections and corrective actions.
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15:45 Feb 03, 2012
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AD 2011–08–04, Amendment 39–
16654 (76 FR 20498, April 13, 2011),
referred to Transport Canada Civil
Aviation (TCCA) (the aviation authority
for Canada) Airworthiness Directive CF–
2009–20, dated May 1, 2009 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
There have been four reports of loose or
detached main landing gear torque link apex
pin locking plate and the locking plate
retainer bolt. This condition could result in
torque link apex pin disengagement, heavy
vibration during landing, damage to main
landing gear components and subsequent
main landing gear collapse.
Investigation has determined that incorrect
stack-up tolerances of the apex joint or
improper installation of the locking plate and
apex nut could result in torque link apex pin
disengagement. This [TCCA] directive
mandates [a one-time detailed] inspection of
the torque link apex joint [for correct
installation and damage, and corrective
actions if necessary] and replacement of the
torque link apex nut.
The corrective actions include reinstalling parts that are not correctly
installed and replacing damaged parts.
You may obtain further information by
examining the MCAI in the AD docket.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between This AD and the
MCAI or Service Information
The MCAI specifies to inspect only
airplanes having certain serial numbers
that are part of the MCAI applicability.
Because the affected part could be
rotated onto any of the airplanes listed
in the applicability, this proposed AD
would continue to require that the
inspection be done on all airplanes. We
have coordinated this with the TCCA.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 361 products of U.S.
registry.
The actions required by AD 2011–08–
04, Amendment 39–16654 (76 FR
20498, April 13, 2011), and retained in
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5731
this proposed AD that about 5 workhours 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 $153,425,
or $425 per product.
We estimate that it would take about
5 work-hours per product to comply
with the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Based on these
figures, we estimate the cost of the
proposed AD on U.S. operators to be
$153,425, or $425 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 proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
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 proposed AD and placed it in the
AD docket.
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Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–16654 (76 FR
20498, April 13, 2011) and adding the
following new AD:
Bombardier, Inc.: Docket No. FAA–2012–
0042; Directorate Identifier 2011–NM–
154–AD.
(a) Comments Due Date
We must receive comments by March 22,
2012.
(b) Affected ADs
This AD supersedes AD 2011–08–04,
Amendment 39–16654 (76 FR 20498, April
13, 2011).
(c) Applicability
This AD applies to the Bombardier
airplanes identified in paragraphs (c)(1) and
(c)(2) of this AD, certificated in any category.
(1) Model CL–600–2C10 (Regional Jet
Series 700, 701 & 702) airplanes, serial
numbers (S/Ns) 10003 and subsequent.
(2) Model CL–600–2D15 (Regional Jet
Series 705) airplanes and Model CL–600–
2D24 (Regional Jet Series 900) airplanes,
S/Ns 15001 and subsequent.
(d) Subject
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(e) Reason
This AD was prompted by reports of loose
or detached main landing gear (MLG) torque
link apex pin locking plate and the locking
plate retainer bolt in the torque link apex
joint. We are issuing this AD to detect and
correct improper assembly and damage of the
MLG torque link apex joint, which could
cause heavy vibration during landing,
consequent damage to MLG components, and
subsequent collapse of the MLG.
(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.
15:45 Feb 03, 2012
Jkt 226001
(g) Inspection for Part Number (P/N) and
Serial Number (S/N) for Model CL–600–2C10
Airplanes
For airplanes identified in paragraph (c)(1)
of this AD: Within 900 flight hours after May
18, 2011 (the effective date of AD 2011–08–
04, Amendment 39–16654 (76 FR 20498,
April 13, 2011)), inspect the main landing
gear (MLG) shock strut assemblies to
determine whether an MLG shock strut
assembly having P/Ns 49000–11 through
49000–22 inclusive and a S/N 0001 through
0284 inclusive is installed. A review of
airplane maintenance records is acceptable in
lieu of this inspection if the part and serial
numbers of the MLG shock strut assembly
can be conclusively determined from that
review.
(h) Inspection of the Torque Link Apex Joint
for Model CL–600–2C10 Airplanes
For any MLG shock strut assembly having
P/Ns 49000–11 through 49000–22 inclusive
and a S/N 0001 through 0284 inclusive found
installed during the inspection or records
check required by paragraph (g) of this AD:
Within 900 flight hours after May 18, 2011,
perform a one-time detailed inspection and
all applicable corrective actions on the torque
link apex joint, in accordance with Part A of
the Accomplishment Instructions of
Bombardier Service Bulletin 670BA–32–019,
Revision A, dated September 18, 2008,
except as provided by paragraph (o) of this
AD. Do all applicable corrective actions
before further flight.
(i) Replacement or Rework of the Apex Nut
for Model CL–600–2C10 Airplanes
For any MLG shock strut assembly
identified during the inspection or records
check required by paragraph (g) of this AD:
Within 4,500 flight hours after May 18, 2011,
replace or rework the apex nut, in accordance
with Part B of the Accomplishment
Instructions of Bombardier Service Bulletin
670BA–32–019, Revision A, dated September
18, 2008.
(j) Parts Installation
Air Transport Association (ATA) of
America Code 32: Landing gear.
VerDate Mar<15>2010
Restatement of Requirements of AD 2011–
08–04, Amendment 39–16654 (76 FR 20498,
April 13, 2011)
For all airplanes: As of May 18, 2011, no
person may install, on any airplane, a
replacement MLG shock strut assembly
identified in paragraph (j)(1) or (j)(2) of this
AD, unless it has been reworked in
accordance with paragraph B. of Part B of the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–32–019, Revision A,
dated September 18, 2008.
(1) Part numbers 49000–11 through 49000–
22 inclusive, and with a serial number in the
range of S/Ns 0001 through 0284 inclusive
(the serial number can start with ‘‘MA,’’
‘‘MAL,’’ or ‘‘MA–’’).
(2) Part numbers 49050–5 through 49050–
10 inclusive, and with a serial number in the
range of S/Ns 1001 through 1114 inclusive
(the serial number can start with ‘‘MA,’’
‘‘MAL,’’ or ‘‘MA–’’).
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New Requirements of This AD
(k) Inspection for Part Number and Serial
Number for Model CL–600–2D15 and CL–
600–2D24 Airplanes
For airplanes identified in paragraph (c)(2)
of this AD: Within 900 flight hours after the
effective date of this AD, inspect the MLG
shock strut assemblies to determine whether
an MLG shock strut assembly having P/Ns
49050–5 through 49050–10 inclusive and a
S/N 0001 through 1114 inclusive is installed.
A review of airplane maintenance records is
acceptable in lieu of this inspection if the
part and serial numbers of the MLG shock
strut assembly can be conclusively
determined from that review.
(l) Inspection of the Torque Link Apex Joint
for Model CL–600–2D15 and CL–600–2D24
Airplanes
For any MLG shock strut assembly having
P/Ns 49050–5 through 49050–10 inclusive
and a S/N 0001 through 1114 inclusive found
installed during the inspection or records
check required by paragraph (k) of this AD:
Within 900 flight hours after the effective
date of this AD, perform a one-time detailed
inspection and all applicable corrective
actions on the torque link apex joint, in
accordance with Part A of the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–32–019, Revision A,
dated September 18, 2008, except as
provided by paragraph (o) of this AD. Do all
applicable corrective actions before further
flight.
(m) Replacement or Rework of the Apex Nut
for Model CL–600–2D15 and CL–600–2D24
Airplanes
For any MLG shock strut assembly
identified during the inspection or records
check required by paragraph (k) of this AD:
Within 900 flight hours after the effective
date of this AD, replace or rework the apex
nut, in accordance with Part B of the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–32–019, Revision A,
dated September 18, 2008.
(n) Credit for Actions Accomplished in
Accordance With Previous Service
Information
Inspections, corrective actions,
replacements, and rework accomplished
before the effective date of this AD, in
accordance with Bombardier Service Bulletin
670BA–32–019, dated March 16, 2006, are
considered acceptable for compliance with
the corresponding actions specified in this
AD.
(o) Inspections Not Required Under Certain
Conditions
The inspections specified in paragraph (h)
or (l) of this AD are not required if the actions
specified in paragraph (i) or (m) of this AD,
as applicable, have already been
accomplished; or if Bombardier Repair
Engineering Order 670–32–11–0022, dated
October 22, 2005, or Goodrich Service
Concession Request SCR 0056–05, dated
October 22, 2005; has been incorporated.
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Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules
(p) 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.
(q) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(r) Related Information
Refer to MCAI Canadian Airworthiness
Directive CF–2009–20, dated May 1, 2009;
and Bombardier Service Bulletin 670BA–32–
019, Revision A, dated September 18, 2008;
for related information.
Issued in Renton, Washington, on January
24, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–2619 Filed 2–3–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
Docket No. FAA–2011–1407; Airspace
Docket No. 11–AGL–25
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RIN 2120–AA66
Proposed Modification of Area
Navigation (RNAV) Route Q–62;
Northeast United States
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
VerDate Mar<15>2010
15:45 Feb 03, 2012
Jkt 226001
This action proposes to
modify area navigation (RNAV) route
Q–62 by extending it further west and
incorporating two additional navigation
fixes. The route extension is proposed to
link two RNAV Standard Terminal
Arrival Routes (STARs) serving the
Chicago O’Hare International Airport,
IL, terminal area with the high altitude
route. The FAA is taking this action to
increase National Airspace System
(NAS) efficiency and enhance flight
safety as aircraft transition from the en
route airway structure to the terminal
area airspace phase of flight.
DATES: Comments must be received on
or before March 22, 2012.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, M–
30, 1200 New Jersey Avenue SE., West
Building Ground Floor, Room W12–140,
Washington, DC 20590–0001; telephone:
(202) 366–9826. You must identify FAA
Docket No. FAA–2011–1407 and
Airspace Docket No. 11–AGL–25 at the
beginning of your comments. You may
also submit comments through the
Internet at https://www.regulations.gov.
FOR FURTHER INFORMATION CONTACT:
Colby Abbott, Airspace, Regulations and
ATC Procedures Group, Office of
Airspace Services, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket numbers (FAA Docket No. FAA–
2011–1407 and Airspace Docket No. 11–
AGL–25) and be submitted in triplicate
to the Docket Management Facility (see
ADDRESSES section for address and
phone number). You may also submit
comments through the Internet at
https://www.regulations.gov.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this action must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to FAA
Docket No. FAA–2011–1407 and
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
5733
Airspace Docket No. 11–AGL–25.’’ The
postcard will be date/time stamped and
returned to the commenter.
All communications received on or
before the specified closing date for
comments will be considered before
taking action on the proposed rule. The
proposal contained in this action may
be changed in light of comments
received. All comments submitted will
be available for examination in the
public docket both before and after the
closing date for comments. A report
summarizing each substantive public
contact with FAA personnel concerned
with this rulemaking will be filed in the
docket.
Availability of NPRMs
An electronic copy of this document
may be downloaded through the
Internet at https://www.regulations.gov.
Recently published rulemaking
documents can also be accessed through
the FAA’s Web page at https://
www.faa.gov/airports_airtraffic/
air_traffic/publications/
airspace_amendments/.
You may review the public docket
containing the proposal, any comments
received and any final disposition in
person in the Dockets Office (see
ADDRESSES section for address and
phone number) between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. An informal docket
may also be examined during normal
business hours at the office of the
Central Service Center, Operations
Support Group, Federal Aviation
Administration, 2601 Meacham Blvd.,
Fort Worth, TX 76137.
Persons interested in being placed on
a mailing list for future NPRMs should
contact the FAA’s Office of Rulemaking,
(202) 267–9677, for a copy of Advisory
Circular No. 11–2A, Notice of Proposed
Rulemaking Distribution System, which
describes the application procedure.
The Proposal
The FAA is proposing an amendment
to Title 14, Code of Federal Regulations
(14 CFR) part 71 by extending high
altitude RNAV route Q–62 to the west
to include the WATSN and DAIFE fixes.
The proposed change would facilitate
linking the WATSN and HALIE RNAV
STARs serving Chicago O’Hare
International Airport, IL, with the high
altitude route and establish a seamless
transition for westbound air traffic from
the New York metropolitan area into the
Chicago O’Hare International Airport,
IL, terminal area. This proposed route
extension would also reduce ATC
system complexity, air traffic controller
and pilot workload, and voice
communication requirements, as well as
E:\FR\FM\06FEP1.SGM
06FEP1
]]>Agencies
[Federal Register Volume 77, Number 24 (Monday, February 6, 2012)]
[Proposed Rules]
[Pages 5730-5733]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-2619]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0042; Directorate Identifier 2011-NM-154-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain Bombardier, Inc. Model CL-600-2C10
(Regional Jet Series 700, 701 & 702), CL-600-2D15 (Regional Jet Series
705), and CL-600-2D24 (Regional Jet Series 900) airplanes. The existing
AD currently requires a one-time inspection of the main landing gear
(MLG) shock strut assemblies for part and serial numbers; for certain
MLG shock strut assemblies, a one-time inspection of the torque link
apex joint, and corrective actions if necessary; and, for certain MLG
shock strut assemblies, replacement or rework of the apex nut. Since we
issued that AD, we have determined that part and serial numbers for MLG
shock strut assemblies for Model CL-600-2D15 and CL-600-2D24 airplanes
were inadvertently omitted from certain requirements of the existing
AD. This proposed AD would continue to require the actions in the
existing AD, and would add the previously omitted part and serial
numbers. We are proposing this AD to detect and correct improper
assembly and damage of the MLG torque link apex joint, which could
cause heavy vibration during landing, consequent damage to MLG
components, and subsequent collapse of the MLG.
DATES: We must receive comments on this proposed AD by March 22, 2012.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Bombardier, Inc., 400 Cote-Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; phone: 514-855-5000; fax: 514-855-7401; email:
thd.crj@aero.bombardier.com; Internet: https://www.bombardier.com. You
may review copies of the referenced 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.
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
[[Page 5731]]
FOR FURTHER INFORMATION CONTACT: Stephen Kowalski, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; phone: (516) 228-7327; fax: (516) 794-5531; email:
Stephen.Kowalski@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0042;
Directorate Identifier 2011-NM-154-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 23, 2011, we issued AD 2011-08-04, Amendment 39-16654 (76
FR 20498, April 13, 2011). That AD required actions intended to address
an unsafe condition on Bombardier, Inc. Model CL-600-2C10 (Regional Jet
Series 700, 701 & 702), CL-600-2D15 (Regional Jet Series 705), and CL-
600-2D24 (Regional Jet Series 900) airplanes.
Since we issued AD 2011-08-04, Amendment 39-16654 (76 FR 20498,
April 13, 2011), we have determined that part and serial numbers for
main landing gear (MLG) shock strut assemblies for Model CL-600-2D15
(Regional Jet Series 705) airplanes and Model CL-600-2D24 (Regional Jet
Series 900) airplanes were inadvertently omitted from paragraphs (g)
and (h) of that AD. As a result, operators could be inspecting for part
and serial numbers which they do not have, and would, therefore, not be
required to accomplish the actions intended to correct the identified
unsafe condition on those airplanes. Therefore, we have removed
airplanes identified in paragraph (c)(2) of this AD from the
requirements of paragraphs (g), (h), and (i) of this AD. We have added
new requirements for those airplanes to inspect for the appropriate
part numbers and serial numbers, and to do all applicable inspections
and corrective actions.
AD 2011-08-04, Amendment 39-16654 (76 FR 20498, April 13, 2011),
referred to Transport Canada Civil Aviation (TCCA) (the aviation
authority for Canada) Airworthiness Directive CF-2009-20, dated May 1,
2009 (referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
There have been four reports of loose or detached main landing
gear torque link apex pin locking plate and the locking plate
retainer bolt. This condition could result in torque link apex pin
disengagement, heavy vibration during landing, damage to main
landing gear components and subsequent main landing gear collapse.
Investigation has determined that incorrect stack-up tolerances
of the apex joint or improper installation of the locking plate and
apex nut could result in torque link apex pin disengagement. This
[TCCA] directive mandates [a one-time detailed] inspection of the
torque link apex joint [for correct installation and damage, and
corrective actions if necessary] and replacement of the torque link
apex nut.
The corrective actions include re-installing parts that are not
correctly installed and replacing damaged parts. You may obtain further
information by examining the MCAI in the AD docket.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
The MCAI specifies to inspect only airplanes having certain serial
numbers that are part of the MCAI applicability. Because the affected
part could be rotated onto any of the airplanes listed in the
applicability, this proposed AD would continue to require that the
inspection be done on all airplanes. We have coordinated this with the
TCCA.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 361 products of U.S. registry.
The actions required by AD 2011-08-04, Amendment 39-16654 (76 FR
20498, April 13, 2011), and retained in this proposed AD that about 5
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 $153,425, or $425 per product.
We estimate that it would take about 5 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the proposed AD on U.S. operators to be $153,425, or $425
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
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 proposed AD and placed it in the AD docket.
[[Page 5732]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 39-16654 (76 FR
20498, April 13, 2011) and adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2012-0042; Directorate Identifier
2011-NM-154-AD.
(a) Comments Due Date
We must receive comments by March 22, 2012.
(b) Affected ADs
This AD supersedes AD 2011-08-04, Amendment 39-16654 (76 FR
20498, April 13, 2011).
(c) Applicability
This AD applies to the Bombardier airplanes identified in
paragraphs (c)(1) and (c)(2) of this AD, certificated in any
category.
(1) Model CL-600-2C10 (Regional Jet Series 700, 701 & 702)
airplanes, serial numbers (S/Ns) 10003 and subsequent.
(2) Model CL-600-2D15 (Regional Jet Series 705) airplanes and
Model CL-600-2D24 (Regional Jet Series 900) airplanes, S/Ns 15001
and subsequent.
(d) Subject
Air Transport Association (ATA) of America Code 32: Landing
gear.
(e) Reason
This AD was prompted by reports of loose or detached main
landing gear (MLG) torque link apex pin locking plate and the
locking plate retainer bolt in the torque link apex joint. We are
issuing this AD to detect and correct improper assembly and damage
of the MLG torque link apex joint, which could cause heavy vibration
during landing, consequent damage to MLG components, and subsequent
collapse of the MLG.
(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.
Restatement of Requirements of AD 2011-08-04, Amendment 39-16654 (76 FR
20498, April 13, 2011)
(g) Inspection for Part Number (P/N) and Serial Number (S/N) for Model
CL-600-2C10 Airplanes
For airplanes identified in paragraph (c)(1) of this AD: Within
900 flight hours after May 18, 2011 (the effective date of AD 2011-
08-04, Amendment 39-16654 (76 FR 20498, April 13, 2011)), inspect
the main landing gear (MLG) shock strut assemblies to determine
whether an MLG shock strut assembly having P/Ns 49000-11 through
49000-22 inclusive and a S/N 0001 through 0284 inclusive is
installed. A review of airplane maintenance records is acceptable in
lieu of this inspection if the part and serial numbers of the MLG
shock strut assembly can be conclusively determined from that
review.
(h) Inspection of the Torque Link Apex Joint for Model CL-600-2C10
Airplanes
For any MLG shock strut assembly having P/Ns 49000-11 through
49000-22 inclusive and a S/N 0001 through 0284 inclusive found
installed during the inspection or records check required by
paragraph (g) of this AD: Within 900 flight hours after May 18,
2011, perform a one-time detailed inspection and all applicable
corrective actions on the torque link apex joint, in accordance with
Part A of the Accomplishment Instructions of Bombardier Service
Bulletin 670BA-32-019, Revision A, dated September 18, 2008, except
as provided by paragraph (o) of this AD. Do all applicable
corrective actions before further flight.
(i) Replacement or Rework of the Apex Nut for Model CL-600-2C10
Airplanes
For any MLG shock strut assembly identified during the
inspection or records check required by paragraph (g) of this AD:
Within 4,500 flight hours after May 18, 2011, replace or rework the
apex nut, in accordance with Part B of the Accomplishment
Instructions of Bombardier Service Bulletin 670BA-32-019, Revision
A, dated September 18, 2008.
(j) Parts Installation
For all airplanes: As of May 18, 2011, no person may install, on
any airplane, a replacement MLG shock strut assembly identified in
paragraph (j)(1) or (j)(2) of this AD, unless it has been reworked
in accordance with paragraph B. of Part B of the Accomplishment
Instructions of Bombardier Service Bulletin 670BA-32-019, Revision
A, dated September 18, 2008.
(1) Part numbers 49000-11 through 49000-22 inclusive, and with a
serial number in the range of S/Ns 0001 through 0284 inclusive (the
serial number can start with ``MA,'' ``MAL,'' or ``MA-'').
(2) Part numbers 49050-5 through 49050-10 inclusive, and with a
serial number in the range of S/Ns 1001 through 1114 inclusive (the
serial number can start with ``MA,'' ``MAL,'' or ``MA-'').
New Requirements of This AD
(k) Inspection for Part Number and Serial Number for Model CL-600-2D15
and CL-600-2D24 Airplanes
For airplanes identified in paragraph (c)(2) of this AD: Within
900 flight hours after the effective date of this AD, inspect the
MLG shock strut assemblies to determine whether an MLG shock strut
assembly having P/Ns 49050-5 through 49050-10 inclusive and a S/N
0001 through 1114 inclusive is installed. A review of airplane
maintenance records is acceptable in lieu of this inspection if the
part and serial numbers of the MLG shock strut assembly can be
conclusively determined from that review.
(l) Inspection of the Torque Link Apex Joint for Model CL-600-2D15 and
CL-600-2D24 Airplanes
For any MLG shock strut assembly having P/Ns 49050-5 through
49050-10 inclusive and a S/N 0001 through 1114 inclusive found
installed during the inspection or records check required by
paragraph (k) of this AD: Within 900 flight hours after the
effective date of this AD, perform a one-time detailed inspection
and all applicable corrective actions on the torque link apex joint,
in accordance with Part A of the Accomplishment Instructions of
Bombardier Service Bulletin 670BA-32-019, Revision A, dated
September 18, 2008, except as provided by paragraph (o) of this AD.
Do all applicable corrective actions before further flight.
(m) Replacement or Rework of the Apex Nut for Model CL-600-2D15 and CL-
600-2D24 Airplanes
For any MLG shock strut assembly identified during the
inspection or records check required by paragraph (k) of this AD:
Within 900 flight hours after the effective date of this AD, replace
or rework the apex nut, in accordance with Part B of the
Accomplishment Instructions of Bombardier Service Bulletin 670BA-32-
019, Revision A, dated September 18, 2008.
(n) Credit for Actions Accomplished in Accordance With Previous
Service Information
Inspections, corrective actions, replacements, and rework
accomplished before the effective date of this AD, in accordance
with Bombardier Service Bulletin 670BA-32-019, dated March 16, 2006,
are considered acceptable for compliance with the corresponding
actions specified in this AD.
(o) Inspections Not Required Under Certain Conditions
The inspections specified in paragraph (h) or (l) of this AD are
not required if the actions specified in paragraph (i) or (m) of
this AD, as applicable, have already been accomplished; or if
Bombardier Repair Engineering Order 670-32-11-0022, dated October
22, 2005, or Goodrich Service Concession Request SCR 0056-05, dated
October 22, 2005; has been incorporated.
[[Page 5733]]
(p) 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.
(q) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(r) Related Information
Refer to MCAI Canadian Airworthiness Directive CF-2009-20, dated
May 1, 2009; and Bombardier Service Bulletin 670BA-32-019, Revision
A, dated September 18, 2008; for related information.
Issued in Renton, Washington, on January 24, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-2619 Filed 2-3-12; 8:45 am]
BILLING CODE 4910-13-P
