Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes, 13080-13082 [2011-5085]
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13080
Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations
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.
Federal Aviation Administration
This AD becomes effective
March 25, 2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 25, 2011.
We must receive comments on this
AD by April 25, 2011.
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 W12–40, 1200 New Jersey
Avenue, SE., Washington, DC, between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays.
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2011–0154; Directorate
Identifier 2011–NM–016–AD; Amendment
39–16624; AD 2011–05–14]
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Fabio Buttitta, 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–
7303; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Related Information
(i) For more information about this AD,
contact Eric Kinney, Aerospace Engineer, Ft.
Worth Aircraft Certification Office, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone: (817) 222–5459; fax: (817)
222–5960; e-mail: eric.kinney@faa.gov.
Issued in Kansas City, Missouri, on March
3, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2011–5296 Filed 3–9–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Model DHC–8–400 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
jdjones on DSK8KYBLC1PROD with RULES
SUMMARY:
Two cases of the main landing gear (MLG)
alternate extension system (AES) cam
mechanism failure were found during line
checks. The cam mechanism operates the
cable to open the MLG door and releases the
MLG uplock in sequence. In the case where
it is necessary to deploy the MLG using the
AES, the failure of the MLG AES cam
mechanism on one side will lead to an unsafe
asymmetrical landing configuration.
*
*
*
*
*
The unsafe condition is possible loss of
control during landing. This AD
requires actions that are intended to
address the unsafe condition described
in the MCAI.
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14:45 Mar 09, 2011
Jkt 223001
DATES:
Discussion
The Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Emergency Airworthiness Directive CF–
2011–01, dated January 17, 2011
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
Two cases of the main landing gear (MLG)
alternate extension system (AES) cam
mechanism failure were found during line
checks. The cam mechanism operates the
cable to open the MLG door and releases the
MLG uplock in sequence. In the case where
it is necessary to deploy the MLG using the
AES, the failure of the MLG AES cam
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Sfmt 4700
mechanism on one side will lead to an unsafe
asymmetrical landing configuration.
Preliminary investigation indicates that the
cam mechanism failure may have occurred
and remained dormant after a previous AES
operation. The cam mechanism may not have
fully returned to the normal rested position.
With the cam mechanism out of normal
rested position, normal powered landing gear
door operation could introduce sufficient
loads to fracture the cam mechanism or
rupture the door release cable.
This directive mandates the initial and
subsequent [detailed] inspections for proper
operation of the MLG AES cam mechanism,
and rectify [repair or replace cam assembly
with new or serviceable cam assembly] as
necessary.
The unsafe condition is possible loss of
control during landing. You may obtain
further information by examining the
MCAI in the AD docket.
Relevant Service Information
Bombardier has issued Repair
Drawing 8/4–32–0160, Issue 2, dated
January 18, 2011. The actions described
in this service information are intended
to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This 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 issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between the AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a Note within the AD.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
E:\FR\FM\10MRR1.SGM
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Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because two cases of the main
landing gear (MLG) alternate extension
system (AES) cam mechanism failure
were found during line checks. The cam
mechanism operates the cable to open
the MLG door and releases the MLG
uplock in sequence. In the case where
it is necessary to deploy the MLG using
the AES, the failure of the MLG AES
cam mechanism on one side will lead to
an unsafe asymmetrical landing
configuration. Therefore, we determined
that notice and opportunity for public
comment before issuing this AD are
impracticable and that good cause exists
for making this amendment effective in
fewer than 30 days.
jdjones on DSK8KYBLC1PROD with RULES
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2011–0154;
Directorate Identifier 2011–NM–016–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of 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 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
VerDate Mar<15>2010
14:45 Mar 09, 2011
Jkt 223001
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 this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. 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.
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 AD:
■
2011–05–14 Bombardier, Inc.: Amendment
39–16624. Docket No. FAA–2011–0154;
Directorate Identifier 2011–NM–016–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective March 25, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier, Inc.
Model DHC–8–400, -401, and -402 airplanes,
certificated in any category, serial numbers
4001 and subsequent.
Subject
(d) Air Transport Association (ATA) of
America Code 32: Landing Gear.
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Fmt 4700
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13081
Reason
(e) The mandatory continued airworthiness
information (MCAI) states:
Two cases of the main landing gear (MLG)
alternate extension system (AES) cam
mechanism failure were found during line
checks. The cam mechanism operates the
cable to open the MLG door and releases the
MLG uplock in sequence. In the case where
it is necessary to deploy the MLG using the
AES, the failure of the MLG AES cam
mechanism on one side will lead to an unsafe
asymmetrical landing configuration.
*
*
*
*
*
The unsafe condition is possible loss of
control during landing.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Actions
(g) Within 50 flight hours or 10 days after
the effective date of this AD, whichever
occurs first, do a detailed inspection for
proper operation of the MLG AES cam
mechanism, in accordance with paragraph A)
of Bombardier Repair Drawing 8/4–32–0160,
Issue 2, dated January 18, 2011. Repeat the
inspection thereafter at intervals not to
exceed 50 flight hours or 10 days, whichever
occurs first.
(1) If the cam mechanism is found to reset
to the normal rested position without any
sticking or binding, it is operating properly.
(2) If the cam mechanism has not reset to
its normal rested position, or if any sticking
or binding is observed, before further flight,
remove the cam assembly, in accordance
with paragraph A) of Bombardier Repair
Drawing 8/4–32–0160, Issue 2, dated January
18, 2011, and do the actions in paragraph
(g)(2)(i) or (g)(2)(ii) of this AD.
(i) Repair the cam mechanism assembly,
including doing detailed inspections for
discrepancies (including an inspection to
determine proper operation, an inspection for
damage, an inspection for corrosion and
cadmium coating degradation, and
inspections to determine dimensions are
within the limits specified in paragraph B) of
Bombardier Repair Drawing 8/4–32–0160,
Issue 2, dated January 18, 2011), in
accordance with paragraph B) of Bombardier
Repair Drawing 8/4–32–0160, Issue 2, dated
January 18, 2011, and install the repaired
cam assembly in accordance with paragraph
C) of Bombardier Repair Drawing 8/4–32–
0160, Issue 2, dated January 18, 2011.
(ii) Install a new or serviceable cam
assembly, in accordance with paragraph C) of
Bombardier Repair Drawing 8/4–32–0160,
Issue 2, dated January 18, 2011.
(3) If the cam mechanism is found
damaged or inoperative during the repair
specified in paragraph (g)(2)(i) of this AD, or
if any discrepancies are found and
Bombardier Repair Drawing 8/4–32–0160,
Issue 2, dated January 18, 2011, does not
specify repairs for those discrepancies, or
repairs specified in paragraph (g)(2)(i) of this
AD cannot be accomplished: Before further
flight, repair and reinstall using a method
approved by the Manager, ANE–170, New
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10MRR1
13082
Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations
York Aircraft Certification Office (ACO),
FAA, or Transport Canada Civil Aviation
(TCCA) (or its delegated agent), or install new
or serviceable cam assembly in accordance
with paragraph C) of Bombardier Repair
Drawing 8/4–32–0160, Issue 2, dated January
18, 2011.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(h) Actions done before the effective date
of this AD in accordance with Bombardier 8/
4–32–0160, Issue 1, dated January 14, 2011,
are acceptable for compliance with the
corresponding requirements of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: No
difference.
Other FAA AD Provisions
(i) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, ANE–170, New York
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 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.
Related Information
(j) Refer to MCAI Canadian Emergency
Airworthiness Directive CF–2011–01, dated
January 17, 2011; and Bombardier Repair
Drawing 8/4–32–0160, Issue 2, dated January
18, 2011; for related information.
Material Incorporated by Reference
(k) You must use Bombardier Repair
Drawing 8/4–32–0160, Issue 2, dated January
18, 2011, to do the actions required by this
AD, unless the AD specifies otherwise.
Bombardier Repair Drawing 8/4–32–0160,
Issue 2, dated January 18, 2011, contains the
following effective pages:
Issue level
shown on page
Sheet number shown on page
1 .............................................................................................................................................................
2, 3, 11 ...................................................................................................................................................
4–10 .......................................................................................................................................................
Date shown on page
2
2
1
January 18, 2011
None shown *
None shown *
(* The issue date of this document is found only on the first page of the document; no other page of this document contains this information.)
jdjones on DSK8KYBLC1PROD with RULES
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Bombardier, Inc., Q–Series
Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada;
telephone 416–375–4000; fax 416–375–4539;
e-mail thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com.
(3) 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.
(4) You may also review copies of the
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/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
22, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–5085 Filed 3–9–11; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
14:45 Mar 09, 2011
Jkt 223001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
Support Services, Federal Aviation
Administration, 800 Independence
Avenue, SW., Washington, DC 20591;
telephone: (202) 267–8783.
SUPPLEMENTARY INFORMATION:
[Docket No. FAA–2011–0009; Airspace
Docket No. 10–AWP–20]
Background
RIN 2120–AA66
The FAA has relocated the Kona
VORTAC current location 3.92 nautical
miles north northwest to the Kona
International Airport property. As a part
of this effort, the FAA realigned V– 1,
V–7, V–11 and V–20, and changed the
VORTAC identification from IAI to
KOA.
Amendment of VOR Federal Airways
V–1, V–7, V–11 and V–20; Kona, HI
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action amends four VHF
Omnidirectional Range (VOR) Federal
airways in the vicinity of Kona, HI; V–
1, V–7, V–11 and V–20 to bring them in
concert with the FAA’s Aeronautical
Products. These VOR Federal airways
are being impacted due to the relocation
of the Kona VHF Omnidirectional Radio
Range and Tactical Air Navigation Aids
(VORTAC).
DATES: Effective date 0901 UTC, May 5,
2011. The Director of the Federal
Register approves this incorporation by
reference action under 1 CFR part 51,
subject to the annual revision of FAA
Order 7400.9 and publication of
conforming amendments.
FOR FURTHER INFORMATION CONTACT: Ken
McElroy, Airspace Regulation and ATC
Procedures Group, Office of Mission
SUMMARY:
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The Rule
This action amends Title 14 Code of
Federal Regulations (14 CFR) part 71 by
modifying Hawaiian VOR Federal
Airways V–1, V–7, V–11 and V–20.
Specifically, this action realigns the
airways north northwest of the current
VORTAC site to reflect the new radials
of the relocated Kona VORTAC (KOA)
onto Kona International Keahole Airport
property Kailua-Kona, HI. This will
enhance the management of aircraft
operations over Hawaii. This action
does not affect the boundaries, altitudes,
or operating requirements of the
airspace. The FAA’s Aeronautical
Products has correctly charted the
airspace, therefore, notice and public
comment under 5 U.S.C. 553(b) are
unnecessary.
E:\FR\FM\10MRR1.SGM
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]]>Agencies
[Federal Register Volume 76, Number 47 (Thursday, March 10, 2011)]
[Rules and Regulations]
[Pages 13080-13082]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-5085]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0154; Directorate Identifier 2011-NM-016-AD;
Amendment 39-16624; AD 2011-05-14]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
Two cases of the main landing gear (MLG) alternate extension
system (AES) cam mechanism failure were found during line checks.
The cam mechanism operates the cable to open the MLG door and
releases the MLG uplock in sequence. In the case where it is
necessary to deploy the MLG using the AES, the failure of the MLG
AES cam mechanism on one side will lead to an unsafe asymmetrical
landing configuration.
* * * * *
The unsafe condition is possible loss of control during landing. This
AD requires actions that are intended to address the unsafe condition
described in the MCAI.
DATES: This AD becomes effective March 25, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of March 25,
2011.
We must receive comments on this AD by April 25, 2011.
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 W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Fabio Buttitta, 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) 228-7303; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
The Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Emergency Airworthiness
Directive CF-2011-01, dated January 17, 2011 (referred to after this as
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
Two cases of the main landing gear (MLG) alternate extension
system (AES) cam mechanism failure were found during line checks.
The cam mechanism operates the cable to open the MLG door and
releases the MLG uplock in sequence. In the case where it is
necessary to deploy the MLG using the AES, the failure of the MLG
AES cam mechanism on one side will lead to an unsafe asymmetrical
landing configuration.
Preliminary investigation indicates that the cam mechanism
failure may have occurred and remained dormant after a previous AES
operation. The cam mechanism may not have fully returned to the
normal rested position. With the cam mechanism out of normal rested
position, normal powered landing gear door operation could introduce
sufficient loads to fracture the cam mechanism or rupture the door
release cable.
This directive mandates the initial and subsequent [detailed]
inspections for proper operation of the MLG AES cam mechanism, and
rectify [repair or replace cam assembly with new or serviceable cam
assembly] as necessary.
The unsafe condition is possible loss of control during landing. You
may obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
Bombardier has issued Repair Drawing 8/4-32-0160, Issue 2, dated
January 18, 2011. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This 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 issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between the AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the AD.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this
[[Page 13081]]
AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because two
cases of the main landing gear (MLG) alternate extension system (AES)
cam mechanism failure were found during line checks. The cam mechanism
operates the cable to open the MLG door and releases the MLG uplock in
sequence. In the case where it is necessary to deploy the MLG using the
AES, the failure of the MLG AES cam mechanism on one side will lead to
an unsafe asymmetrical landing configuration. Therefore, we determined
that notice and opportunity for public comment before issuing this AD
are impracticable and that good cause exists for making this amendment
effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2011-0154; Directorate
Identifier 2011-NM-016-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
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 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 this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. 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.
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 AD:
2011-05-14 Bombardier, Inc.: Amendment 39-16624. Docket No. FAA-
2011-0154; Directorate Identifier 2011-NM-016-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
25, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier, Inc. Model DHC-8-400, -401,
and -402 airplanes, certificated in any category, serial numbers
4001 and subsequent.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
Gear.
Reason
(e) The mandatory continued airworthiness information (MCAI)
states:
Two cases of the main landing gear (MLG) alternate extension
system (AES) cam mechanism failure were found during line checks.
The cam mechanism operates the cable to open the MLG door and
releases the MLG uplock in sequence. In the case where it is
necessary to deploy the MLG using the AES, the failure of the MLG
AES cam mechanism on one side will lead to an unsafe asymmetrical
landing configuration.
* * * * *
The unsafe condition is possible loss of control during landing.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Actions
(g) Within 50 flight hours or 10 days after the effective date
of this AD, whichever occurs first, do a detailed inspection for
proper operation of the MLG AES cam mechanism, in accordance with
paragraph A) of Bombardier Repair Drawing 8/4-32-0160, Issue 2,
dated January 18, 2011. Repeat the inspection thereafter at
intervals not to exceed 50 flight hours or 10 days, whichever occurs
first.
(1) If the cam mechanism is found to reset to the normal rested
position without any sticking or binding, it is operating properly.
(2) If the cam mechanism has not reset to its normal rested
position, or if any sticking or binding is observed, before further
flight, remove the cam assembly, in accordance with paragraph A) of
Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18,
2011, and do the actions in paragraph (g)(2)(i) or (g)(2)(ii) of
this AD.
(i) Repair the cam mechanism assembly, including doing detailed
inspections for discrepancies (including an inspection to determine
proper operation, an inspection for damage, an inspection for
corrosion and cadmium coating degradation, and inspections to
determine dimensions are within the limits specified in paragraph B)
of Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18,
2011), in accordance with paragraph B) of Bombardier Repair Drawing
8/4-32-0160, Issue 2, dated January 18, 2011, and install the
repaired cam assembly in accordance with paragraph C) of Bombardier
Repair Drawing 8/4-32-0160, Issue 2, dated January 18, 2011.
(ii) Install a new or serviceable cam assembly, in accordance
with paragraph C) of Bombardier Repair Drawing 8/4-32-0160, Issue 2,
dated January 18, 2011.
(3) If the cam mechanism is found damaged or inoperative during
the repair specified in paragraph (g)(2)(i) of this AD, or if any
discrepancies are found and Bombardier Repair Drawing 8/4-32-0160,
Issue 2, dated January 18, 2011, does not specify repairs for those
discrepancies, or repairs specified in paragraph (g)(2)(i) of this
AD cannot be accomplished: Before further flight, repair and
reinstall using a method approved by the Manager, ANE-170, New
[[Page 13082]]
York Aircraft Certification Office (ACO), FAA, or Transport Canada
Civil Aviation (TCCA) (or its delegated agent), or install new or
serviceable cam assembly in accordance with paragraph C) of
Bombardier Repair Drawing 8/4-32-0160, Issue 2, dated January 18,
2011.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(h) Actions done before the effective date of this AD in
accordance with Bombardier 8/4-32-0160, Issue 1, dated January 14,
2011, are acceptable for compliance with the corresponding
requirements of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service
information as follows: No difference.
Other FAA AD Provisions
(i) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANE-
170, New York 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 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.
Related Information
(j) Refer to MCAI Canadian Emergency Airworthiness Directive CF-
2011-01, dated January 17, 2011; and Bombardier Repair Drawing 8/4-
32-0160, Issue 2, dated January 18, 2011; for related information.
Material Incorporated by Reference
(k) You must use Bombardier Repair Drawing 8/4-32-0160, Issue 2,
dated January 18, 2011, to do the actions required by this AD,
unless the AD specifies otherwise. Bombardier Repair Drawing 8/4-32-
0160, Issue 2, dated January 18, 2011, contains the following
effective pages:
----------------------------------------------------------------------------------------------------------------
Issue level shown
Sheet number shown on page on page Date shown on page
----------------------------------------------------------------------------------------------------------------
1.............................................. 2 January 18, 2011
2, 3, 11....................................... 2 None shown *
4-10........................................... 1 None shown *
----------------------------------------------------------------------------------------------------------------
(* The issue date of this document is found only on the first page of the document; no other page of this
document contains this information.)
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000;
fax 416-375-4539; e-mail thd.qseries@aero.bombardier.com; Internet
https://www.bombardier.com.
(3) 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.
(4) You may also review copies of the 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/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on February 22, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-5085 Filed 3-9-11; 8:45 am]
BILLING CODE 4910-13-P
