Airworthiness Directives; Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701 & 702), Model CL-600-2D15 (Regional Jet Series 705), and Model CL-600-2D24 (Regional Jet Series 900) Airplanes, 52222-52225 [2011-20673]
Download as PDF
<![CDATA[
52222
Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
4090; e-mail: jim.rutherford@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(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.
(3) Reporting Requirements: For any
reporting requirement in this AD, a Federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
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Related Information
ˆ
(h) Refer to AGENCIA NACIONAL DE
AVIACAO CIVIL—BRAZIL (ANAC), NPR/AD
¸˜
2011–500–02, dated March 31, 2011; MCAI
ˆ
AGENCIA NACIONAL DE AVIACAO
¸˜
CIVIL—BRAZIL (ANAC), AD No.: 2010–11–
01, dated December 20, 2010; and PHENOM
Service Bulletin SB No.: 500–27–0006,
Revision No.: 02, dated January 14, 2011; for
related information.
Material Incorporated by Reference
(i) You must use PHENOM Service Bulletin
SB No.: 500–27–0006, Revision No.: 02,
dated January 14, 2011, to do the actions
required by this AD, unless the AD specifies
otherwise.
(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 EMBRAER Empresa
´
Brasileira de Aeronautica S.A., Phenom
Maintenance Support, Av. Brig. Farina Lima,
2170, Sao Jose dos Campos–SP, CEP: 12227–
901—P.O. Box: 36/2, BRASIL; telephone:
++55 12 3927–5383; fax: ++55 12 3927–2619;
e-mail: phenom.reliability@embraer.com.br;
Internet: https://www.embraer.com.br.
(3) You may review copies of the
referenced service information at the 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.
VerDate Mar<15>2010
17:10 Aug 19, 2011
Jkt 223001
(4) You may also review copies of the
service information incorporated by reference
for this AD 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 Kansas City, Missouri on August
9, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2011–20775 Filed 8–19–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0515; Directorate
Identifier 2009–NM–196–AD; Amendment
39–16776; AD 2011–17–12]
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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:
SUMMARY:
Several cases have been reported of cracks
in the joint extrusions securing the outer
bondment to the acoustic panel of the nacelle
transcowl assemblies. Although there is no
effect on flight safety (thrust reverser
stowed), thrust reverser deployment under
rejected take-off or emergency landing load
conditions could potentially result in
acoustic panel failure and possible runway
debris.
*
*
*
*
*
The loss of an acoustic panel during
rejected take-off or emergency landing
load conditions could leave debris on
the runway. This debris, if not removed,
creates an unsafe condition for other
airplanes during take-off or landing, as
those airplanes could impact debris on
the runway and sustain damage. We are
issuing this AD to require actions to
Frm 00010
Fmt 4700
This AD becomes effective
September 26, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 26, 2011.
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:
Craig Yates, 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–
7355; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
DATES:
Discussion
Airworthiness Directives; Bombardier,
Inc. Model CL–600–2C10 (Regional Jet
Series 700, 701 & 702), Model CL–600–
2D15 (Regional Jet Series 705), and
Model CL–600–2D24 (Regional Jet
Series 900) Airplanes
PO 00000
correct the unsafe condition on these
products.
Sfmt 4700
We issued a supplemental notice of
proposed rulemaking (NPRM) to amend
14 CFR part 39 to include an AD that
would apply to the specified products.
That supplemental NPRM was
published in the Federal Register on
April 6, 2011 (76 FR 18957). That
supplemental NPRM proposed to
correct an unsafe condition for the
specified products. The MCAI states:
Several cases have been reported of cracks
in the joint extrusions securing the outer
bondment to the acoustic panel of the nacelle
transcowl assemblies. Although there is no
effect on flight safety (thrust reverser
stowed), thrust reverser deployment under
rejected take-off or emergency landing load
conditions could potentially result in
acoustic panel failure and possible runway
debris.
This [Canadian] directive mandates
inspection, repair (if necessary) and
reinforcement of the transcowl assemblies.
The loss of an acoustic panel during
rejected take-off or emergency landing
load conditions could leave debris on
the runway. This debris, if not removed,
creates an unsafe condition for other
airplanes during take-off or landing, as
those airplanes could impact debris on
the runway and sustain damage. The
inspection is a detailed visual
inspection of the outboard edge of the
transcowl joint extrusion for evidence of
cracking. The repair consists of doing an
eddy current or liquid penetrant
inspection for cracking, and depending
on the results, either removing the
affected joint extrusion area and
replacing with packers, or contacting
Bombardier for repair instructions and
E:\FR\FM\22AUR1.SGM
22AUR1
Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
doing the repair. The reinforcement of
the transcowl assemblies includes
installing new support channels. 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
considered the comments received.
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Request To Allow for Records Review
American Eagle Airlines (AEA)
requested that we revise the
supplemental NPRM to allow operators
to perform a records review in lieu of
the inspection for part number, serial
number, and repair status of each
transcowl assembly, as required by
paragraph (g) of the supplemental
NPRM. AEA did not provide reasoning
for this request.
We agree to allow operators to
perform a records review in lieu of the
inspection for part number, serial
number, and repair status of each
transcowl assembly. We have
determined that a review of airplane
maintenance records is acceptable in
lieu of the inspection, if the part
number, serial number, and repair status
of each transcowl assembly can be
conclusively determined from that
review. We have revised paragraph (g)
of the final rule accordingly.
Request To Revise Paragraph (g)(1) of
the Supplemental NPRM
AEA requested that we revise
paragraph (g)(1) of the supplemental
NPRM to remove the reference to
paragraph (h) of the supplemental
NPRM. AEA explained that the
transcowls specified in paragraph (g)(1)
of the supplemental NPRM are postmodified transcowls and do not need
the inspections required by paragraph
(h) of the supplemental NPRM. AEA
reasoned that paragraph (h) of the
supplemental NPRM should not apply
to airplanes that have met the
conditions specified in paragraph
(g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of the
supplemental NPRM.
We agree to revise paragraph (g)(1) of
the final rule to remove reference to
paragraph (h) of the final rule. We have
determined that only paragraph (k) of
the final rule applies to postmodification transcowls. We have
revised paragraph (g)(1) of the final rule
accordingly.
Conclusion
We reviewed the available data,
including the comment received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
VerDate Mar<15>2010
17:10 Aug 19, 2011
Jkt 223001
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
Differences Between This 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 our FAA
policies. Any such differences are
highlighted in a Note within the AD.
Costs of Compliance
We estimate that this AD will affect
361 products of U.S. registry. We also
estimate that it will take about 8 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 $0 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of this AD
to the U.S. operators to be $245,480, or
$680 per product.
In addition, we estimate that any
necessary follow-on actions would take
between 4 and 8 work-hours and require
parts costing $0, for a cost between $340
and $680 per product. We have no way
of determining the number of products
that may need these actions.
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
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
52223
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.
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 the NPRM, 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.
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:
■
E:\FR\FM\22AUR1.SGM
22AUR1
52224
Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
2011–17–12 Bombardier, Inc.: Amendment
39–16776. Docket No. FAA–2010–0515;
Directorate Identifier 2009–NM–196–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective September 26, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes
identified 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 10003 through
10265 inclusive.
(2) Bombardier, Inc. Model CL–600–2D15
(Regional Jet Series 705) and Model CL–600–
2D24 (Regional Jet Series 900) airplanes,
serial numbers 15001 through 15192
inclusive.
Subject
(d) Air Transport Association (ATA) of
America Code 78: Engine exhaust.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Several cases have been reported of cracks
in the joint extrusions securing the outer
bondment to the acoustic panel of the nacelle
transcowl assemblies. Although there is no
effect on flight safety (thrust reverser
stowed), thrust reverser deployment under
rejected take-off or emergency landing load
conditions could potentially result in
acoustic panel failure and possible runway
debris.
*
*
*
*
*
The loss of an acoustic panel during rejected
take-off or emergency landing load
conditions could leave debris on the runway.
This debris, if not removed, creates an unsafe
condition for other airplanes during take-off
or landing, as those airplanes could impact
debris on the runway and sustain damage.
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.
Inspection, Repair, and Reinforcement
(g) Within 5,000 flight hours or 24 months
after the effective date of this AD, whichever
occurs first, inspect for the part number and
serial number of each transcowl assembly,
and, as applicable, the repair status of each
transcowl assembly. A review of airplane
maintenance records is acceptable in lieu of
this inspection if the part number and serial
number of each transcowl assembly, and, as
applicable, the repair status of each
transcowl assembly can be conclusively
determined from that review.
(1) If all transcowl assemblies installed on
any airplane meet one of the conditions
listed in paragraph (g)(1)(i), (g)(1)(ii), or
(g)(1)(iii) of this AD, no further action is
required by this AD, except paragraph (k) of
this AD must be complied with.
(i) Having part number (P/N) KCN624–
2003–3, –4, –5, –6, –7, or –8, as listed in
Bombardier Service Bulletin 670SH–78–029,
Revision C, dated November 10, 2010.
(ii) Having P/Ns CN624–2001–XXX or
KCN624–2001–X (XXX and X mean various
dash numbers), with serial number (S/N)
SB0965 or higher.
(iii) Having P/Ns CN624–2001–XXX or
KCN624–2001–X (XXX and X mean various
dash numbers), and repaired in accordance
with one of the Bombardier repair
engineering orders (REOs) listed in paragraph
1.D. of Bombardier Service Bulletin 670BA–
78–008, Revision B, dated December 22,
2010; or paragraph 1.A. of Bombardier
Service Bulletin 670SH–78–029, Revision C,
dated November 10, 2010.
(2) If one or more of the transcowl
assemblies have P/N CN624–2001–XXX or
KCN624–2001–X (XXX and X mean various
dash numbers), with S/N SB0964 or lower,
and have not been repaired in accordance
with one of the Bombardier REOs listed in
paragraph 1.D. of Bombardier Service
Bulletin 670BA–78–008, Revision B, dated
December 22, 2010; or paragraph 1.A. of
Bombardier Service Bulletin 670SH–78–029,
Revision C, dated November 10, 2010; do the
actions specified in paragraph (i) of this AD.
(h) As of the effective date of this AD, if
any high-energy stop occurs and the thrust
reversers are deployed above 68% N1, or if
a rejected take-off (RTO) occurs and the
thrust reversers are deployed above 68% N1:
Perform a detailed inspection for cracks of
each transcowl assembly (left, right, upper,
and lower) before further flight, by doing the
actions specified in paragraphs (h)(1), (h)(2),
and (h)(3) of this AD. Doing the requirements
of paragraph (i) of this AD terminates the
requirements of paragraph (h) of this AD.
(1) Open the cowling on the left and right
engines.
(2) Do a detailed inspection for cracks of
the joint extrusion of the upper and lower
transcowl assembly on the left and right
engines at the location of the joint piece. If
no cracks are found, close the cowlings on
the left and right engines.
(3) If any crack is found on one or more
transcowl assemblies during the inspection
required by paragraph (h)(2) of this AD,
before further flight, repair and reinforce the
cracked part(s) in accordance with paragraph
(i)(1) of this AD.
Note 1: Procedure—Part 3 of Task 05–51–
27–210–801 of Chapter 05, Part 2, Volume 1,
of the Bombardier CRJ Series Regional Jet
Aircraft Maintenance Manual (AMM), CSP
B–001, Revision 34, dated November 20,
2010, provides guidance for opening and
closing the cowling on the left and right
engines.
(i) For transcowl assemblies identified in
paragraph (g)(2) of this AD: Except as
required by paragraph (h) of this AD, within
5,000 flight hours or 24 months after the
effective date of this AD, whichever comes
first, do a detailed inspection for cracking on
each transcowl assembly, in accordance with
the Accomplishment Instructions of
Bombardier Service Bulletin 670BA–78–008,
Revision B, dated December 22, 2010; or
Bombardier Service Bulletin 670SH–78–029,
Revision C, dated November 10, 2010.
Accomplishment of the actions specified in
paragraph (i)(1) or (i)(2) of this AD for all
transcowl assemblies identified in paragraph
(g)(2) of this AD terminates the requirements
of paragraph (h) of this AD.
(1) If any cracking of the joint extrusion is
found, before further flight, repair and
reinforce the joint extrusion on each
transcowl assembly, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–78–008, Revision B,
dated December 22, 2010; or Bombardier
Service Bulletin 670SH–78–029, Revision C,
dated November 10, 2010.
(2) If no cracking is found, before further
flight, reinforce the joint extrusion on each
transcowl assembly, in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 670BA–78–008, Revision B,
dated December 22, 2010; or Bombardier
Service Bulletin 670SH–78–029, Revision C,
dated November 10, 2010.
Credit for Actions Accomplished in
Accordance With Previous Service
Information
(j) Inspections, repairs, and reinforcement
of the joint extrusion on each transcowl is
also acceptable for compliance with the
corresponding requirements of paragraph (i)
of this AD if done before the effective date
of this AD in accordance with the service
information listed in table 1 of this AD.
TABLE 1—CREDIT SERVICE INFORMATION
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Document
Bombardier
Bombardier
Bombardier
Bombardier
Bombardier
Service
Service
Service
Service
Service
VerDate Mar<15>2010
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Revision
670BA–78–008
670BA–78–008
670SH–78–029
670SH–78–029
670SH–78–029
17:10 Aug 19, 2011
Jkt 223001
................................
................................
................................
................................
................................
PO 00000
Frm 00012
Date
Original ........................................................................
A ..................................................................................
Original ........................................................................
A ..................................................................................
B ..................................................................................
September 19, 2008.
July 10, 2009.
July 3, 2008.
June 30, 2009.
November 25, 2009.
Fmt 4700
Sfmt 4700
E:\FR\FM\22AUR1.SGM
22AUR1
Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations
Parts Installation
(k) As of the effective date of this AD, no
replacement or spare transcowl assembly
having P/N CN624–2001–XXX or KCN624–
2001–X (XXX and X mean various dash
numbers), with S/N SB0964 or lower, may be
installed on any airplane, except for a
transcowl assembly on which any repair
listed in paragraph 1.D. of Bombardier
Service Bulletin 670BA–78–008, Revision B,
dated December 22, 2010, or paragraph 1.A.
of Bombardier Service Bulletin 670SH–78–
029, Revision C, dated November 10, 2010,
has been done; and except for a transcowl
that has been inspected as specified in
paragraph (i) of this AD and all applicable
actions specified in paragraph (i)(1) or (i)(2)
of this AD, as applicable, have been done.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(l) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office, 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 NYACO, send it to ATTN: Program
Manager, Continuing Operational Safety,
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.
mstockstill on DSK4VPTVN1PROD with RULES
Related Information
(m) Refer to MCAI Canadian Airworthiness
Directive CF–2009–33, dated July 28, 2009;
Bombardier Service Bulletin 670BA–78–008,
Revision B, dated December 22, 2010; and
Bombardier Service Bulletin 670SH–78–029,
Revision C, dated November 10, 2010; for
related information.
Material Incorporated by Reference
(n) You must use Bombardier Service
Bulletin 670BA–78–008, Revision B, dated
December 22, 2010; and Bombardier Service
Bulletin 670SH–78–029, Revision C, dated
November 10, 2010; as applicable; to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
VerDate Mar<15>2010
17:10 Aug 19, 2011
Jkt 223001
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.crj@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 August
8, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–20673 Filed 8–19–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–1213; Directorate
Identifier 2009–NM–097–AD; Amendment
39–16775; AD 2011–17–11]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model DC–9–81 (MD–81),
DC–9–82 (MD–82), DC–9–83 (MD–83),
DC–9–87 (MD–87), and MD–88
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD requires
repetitive inspections for cracking of the
lower rear spar caps of the wings, and
related investigative and corrective
actions if necessary. This AD also
requires repetitive inspections of certain
repaired areas. This AD was prompted
by reports of cracking of the wing rear
spar lower cap at the outboard flap and
inboard drive hinge at station
Xrs=164.000; the cracking is due to
material fatigue from normal flap
operating loads. We are issuing this AD
to detect and correct such fatigue
cracking, which could result in fuel
leaks, damage to the wing skin or other
SUMMARY:
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
52225
structure, and consequent reduced
structural integrity of the wing.
DATES: This AD is effective September
26, 2011.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of September 26, 2011.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, California 90846–0001;
telephone 206–544–5000, extension 2;
fax 206–766–5683; e-mail
dse.boecom@boeing.com; Internet
https://www.myboeingfleet.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 Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Roger Durbin, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood,
California 90712–4137; phone: (562)
627–5233; fax: (562) 627–5210; e-mail:
roger.durbin@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to the
specified products. That NPRM
published in the Federal Register on
February 8, 2010 (75 FR 6162). That
NPRM proposed to require repetitive
inspections for cracking of the lower
rear spar caps of the wings, and related
investigative and corrective actions if
necessary. That NPRM also proposed to
require repetitive inspections of certain
repaired areas.
E:\FR\FM\22AUR1.SGM
22AUR1
]]>Agencies
[Federal Register Volume 76, Number 162 (Monday, August 22, 2011)]
[Rules and Regulations]
[Pages 52222-52225]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-20673]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0515; Directorate Identifier 2009-NM-196-AD;
Amendment 39-16776; AD 2011-17-12]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model CL-600-2C10
(Regional Jet Series 700, 701 & 702), Model CL-600-2D15 (Regional Jet
Series 705), and Model CL-600-2D24 (Regional Jet Series 900) Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
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:
Several cases have been reported of cracks in the joint
extrusions securing the outer bondment to the acoustic panel of the
nacelle transcowl assemblies. Although there is no effect on flight
safety (thrust reverser stowed), thrust reverser deployment under
rejected take-off or emergency landing load conditions could
potentially result in acoustic panel failure and possible runway
debris.
* * * * *
The loss of an acoustic panel during rejected take-off or emergency
landing load conditions could leave debris on the runway. This debris,
if not removed, creates an unsafe condition for other airplanes during
take-off or landing, as those airplanes could impact debris on the
runway and sustain damage. We are issuing this AD to require actions to
correct the unsafe condition on these products.
DATES: This AD becomes effective September 26, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 26,
2011.
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: Craig Yates, 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) 228-7355; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (NPRM) to
amend 14 CFR part 39 to include an AD that would apply to the specified
products. That supplemental NPRM was published in the Federal Register
on April 6, 2011 (76 FR 18957). That supplemental NPRM proposed to
correct an unsafe condition for the specified products. The MCAI
states:
Several cases have been reported of cracks in the joint
extrusions securing the outer bondment to the acoustic panel of the
nacelle transcowl assemblies. Although there is no effect on flight
safety (thrust reverser stowed), thrust reverser deployment under
rejected take-off or emergency landing load conditions could
potentially result in acoustic panel failure and possible runway
debris.
This [Canadian] directive mandates inspection, repair (if
necessary) and reinforcement of the transcowl assemblies.
The loss of an acoustic panel during rejected take-off or emergency
landing load conditions could leave debris on the runway. This debris,
if not removed, creates an unsafe condition for other airplanes during
take-off or landing, as those airplanes could impact debris on the
runway and sustain damage. The inspection is a detailed visual
inspection of the outboard edge of the transcowl joint extrusion for
evidence of cracking. The repair consists of doing an eddy current or
liquid penetrant inspection for cracking, and depending on the results,
either removing the affected joint extrusion area and replacing with
packers, or contacting Bombardier for repair instructions and
[[Page 52223]]
doing the repair. The reinforcement of the transcowl assemblies
includes installing new support channels. 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 considered the comments received.
Request To Allow for Records Review
American Eagle Airlines (AEA) requested that we revise the
supplemental NPRM to allow operators to perform a records review in
lieu of the inspection for part number, serial number, and repair
status of each transcowl assembly, as required by paragraph (g) of the
supplemental NPRM. AEA did not provide reasoning for this request.
We agree to allow operators to perform a records review in lieu of
the inspection for part number, serial number, and repair status of
each transcowl assembly. We have determined that a review of airplane
maintenance records is acceptable in lieu of the inspection, if the
part number, serial number, and repair status of each transcowl
assembly can be conclusively determined from that review. We have
revised paragraph (g) of the final rule accordingly.
Request To Revise Paragraph (g)(1) of the Supplemental NPRM
AEA requested that we revise paragraph (g)(1) of the supplemental
NPRM to remove the reference to paragraph (h) of the supplemental NPRM.
AEA explained that the transcowls specified in paragraph (g)(1) of the
supplemental NPRM are post-modified transcowls and do not need the
inspections required by paragraph (h) of the supplemental NPRM. AEA
reasoned that paragraph (h) of the supplemental NPRM should not apply
to airplanes that have met the conditions specified in paragraph
(g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of the supplemental NPRM.
We agree to revise paragraph (g)(1) of the final rule to remove
reference to paragraph (h) of the final rule. We have determined that
only paragraph (k) of the final rule applies to post-modification
transcowls. We have revised paragraph (g)(1) of the final rule
accordingly.
Conclusion
We reviewed the available data, including the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This 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 our FAA policies. Any such differences
are highlighted in a Note within the AD.
Costs of Compliance
We estimate that this AD will affect 361 products of U.S. registry.
We also estimate that it will take about 8 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 $0 per product.
Where the service information lists required parts costs that are
covered under warranty, we have assumed that there will be no charge
for these parts. As we do not control warranty coverage for affected
parties, some parties may incur costs higher than estimated here. Based
on these figures, we estimate the cost of this AD to the U.S. operators
to be $245,480, or $680 per product.
In addition, we estimate that any necessary follow-on actions would
take between 4 and 8 work-hours and require parts costing $0, for a
cost between $340 and $680 per product. We have no way of determining
the number of products that may need these actions.
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.
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 the NPRM, 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.
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:
[[Page 52224]]
2011-17-12 Bombardier, Inc.: Amendment 39-16776. Docket No. FAA-
2010-0515; Directorate Identifier 2009-NM-196-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 26, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the airplanes identified 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 10003 through 10265 inclusive.
(2) Bombardier, Inc. Model CL-600-2D15 (Regional Jet Series 705)
and Model CL-600-2D24 (Regional Jet Series 900) airplanes, serial
numbers 15001 through 15192 inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 78: Engine
exhaust.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Several cases have been reported of cracks in the joint
extrusions securing the outer bondment to the acoustic panel of the
nacelle transcowl assemblies. Although there is no effect on flight
safety (thrust reverser stowed), thrust reverser deployment under
rejected take-off or emergency landing load conditions could
potentially result in acoustic panel failure and possible runway
debris.
* * * * *
The loss of an acoustic panel during rejected take-off or emergency
landing load conditions could leave debris on the runway. This
debris, if not removed, creates an unsafe condition for other
airplanes during take-off or landing, as those airplanes could
impact debris on the runway and sustain damage.
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.
Inspection, Repair, and Reinforcement
(g) Within 5,000 flight hours or 24 months after the effective
date of this AD, whichever occurs first, inspect for the part number
and serial number of each transcowl assembly, and, as applicable,
the repair status of each transcowl assembly. A review of airplane
maintenance records is acceptable in lieu of this inspection if the
part number and serial number of each transcowl assembly, and, as
applicable, the repair status of each transcowl assembly can be
conclusively determined from that review.
(1) If all transcowl assemblies installed on any airplane meet
one of the conditions listed in paragraph (g)(1)(i), (g)(1)(ii), or
(g)(1)(iii) of this AD, no further action is required by this AD,
except paragraph (k) of this AD must be complied with.
(i) Having part number (P/N) KCN624-2003-3, -4, -5, -6, -7, or -
8, as listed in Bombardier Service Bulletin 670SH-78-029, Revision
C, dated November 10, 2010.
(ii) Having P/Ns CN624-2001-XXX or KCN624-2001-X (XXX and X mean
various dash numbers), with serial number (S/N) SB0965 or higher.
(iii) Having P/Ns CN624-2001-XXX or KCN624-2001-X (XXX and X
mean various dash numbers), and repaired in accordance with one of
the Bombardier repair engineering orders (REOs) listed in paragraph
1.D. of Bombardier Service Bulletin 670BA-78-008, Revision B, dated
December 22, 2010; or paragraph 1.A. of Bombardier Service Bulletin
670SH-78-029, Revision C, dated November 10, 2010.
(2) If one or more of the transcowl assemblies have P/N CN624-
2001-XXX or KCN624-2001-X (XXX and X mean various dash numbers),
with S/N SB0964 or lower, and have not been repaired in accordance
with one of the Bombardier REOs listed in paragraph 1.D. of
Bombardier Service Bulletin 670BA-78-008, Revision B, dated December
22, 2010; or paragraph 1.A. of Bombardier Service Bulletin 670SH-78-
029, Revision C, dated November 10, 2010; do the actions specified
in paragraph (i) of this AD.
(h) As of the effective date of this AD, if any high-energy stop
occurs and the thrust reversers are deployed above 68% N1, or if a
rejected take-off (RTO) occurs and the thrust reversers are deployed
above 68% N1: Perform a detailed inspection for cracks of each
transcowl assembly (left, right, upper, and lower) before further
flight, by doing the actions specified in paragraphs (h)(1), (h)(2),
and (h)(3) of this AD. Doing the requirements of paragraph (i) of
this AD terminates the requirements of paragraph (h) of this AD.
(1) Open the cowling on the left and right engines.
(2) Do a detailed inspection for cracks of the joint extrusion
of the upper and lower transcowl assembly on the left and right
engines at the location of the joint piece. If no cracks are found,
close the cowlings on the left and right engines.
(3) If any crack is found on one or more transcowl assemblies
during the inspection required by paragraph (h)(2) of this AD,
before further flight, repair and reinforce the cracked part(s) in
accordance with paragraph (i)(1) of this AD.
Note 1: Procedure--Part 3 of Task 05-51-27-210-801 of Chapter
05, Part 2, Volume 1, of the Bombardier CRJ Series Regional Jet
Aircraft Maintenance Manual (AMM), CSP B-001, Revision 34, dated
November 20, 2010, provides guidance for opening and closing the
cowling on the left and right engines.
(i) For transcowl assemblies identified in paragraph (g)(2) of
this AD: Except as required by paragraph (h) of this AD, within
5,000 flight hours or 24 months after the effective date of this AD,
whichever comes first, do a detailed inspection for cracking on each
transcowl assembly, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 670BA-78-008, Revision
B, dated December 22, 2010; or Bombardier Service Bulletin 670SH-78-
029, Revision C, dated November 10, 2010. Accomplishment of the
actions specified in paragraph (i)(1) or (i)(2) of this AD for all
transcowl assemblies identified in paragraph (g)(2) of this AD
terminates the requirements of paragraph (h) of this AD.
(1) If any cracking of the joint extrusion is found, before
further flight, repair and reinforce the joint extrusion on each
transcowl assembly, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 670BA-78-008, Revision
B, dated December 22, 2010; or Bombardier Service Bulletin 670SH-78-
029, Revision C, dated November 10, 2010.
(2) If no cracking is found, before further flight, reinforce
the joint extrusion on each transcowl assembly, in accordance with
the Accomplishment Instructions of Bombardier Service Bulletin
670BA-78-008, Revision B, dated December 22, 2010; or Bombardier
Service Bulletin 670SH-78-029, Revision C, dated November 10, 2010.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(j) Inspections, repairs, and reinforcement of the joint
extrusion on each transcowl is also acceptable for compliance with
the corresponding requirements of paragraph (i) of this AD if done
before the effective date of this AD in accordance with the service
information listed in table 1 of this AD.
Table 1--Credit Service Information
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Bombardier Service Bulletin 670BA-78-008. Original.................... September 19, 2008.
Bombardier Service Bulletin 670BA-78-008. A........................... July 10, 2009.
Bombardier Service Bulletin 670SH-78-029. Original.................... July 3, 2008.
Bombardier Service Bulletin 670SH-78-029. A........................... June 30, 2009.
Bombardier Service Bulletin 670SH-78-029. B........................... November 25, 2009.
----------------------------------------------------------------------------------------------------------------
[[Page 52225]]
Parts Installation
(k) As of the effective date of this AD, no replacement or spare
transcowl assembly having P/N CN624-2001-XXX or KCN624-2001-X (XXX
and X mean various dash numbers), with S/N SB0964 or lower, may be
installed on any airplane, except for a transcowl assembly on which
any repair listed in paragraph 1.D. of Bombardier Service Bulletin
670BA-78-008, Revision B, dated December 22, 2010, or paragraph 1.A.
of Bombardier Service Bulletin 670SH-78-029, Revision C, dated
November 10, 2010, has been done; and except for a transcowl that
has been inspected as specified in paragraph (i) of this AD and all
applicable actions specified in paragraph (i)(1) or (i)(2) of this
AD, as applicable, have been done.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(l) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office, 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 NYACO, send it to ATTN: Program Manager, Continuing Operational
Safety, 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
(m) Refer to MCAI Canadian Airworthiness Directive CF-2009-33,
dated July 28, 2009; Bombardier Service Bulletin 670BA-78-008,
Revision B, dated December 22, 2010; and Bombardier Service Bulletin
670SH-78-029, Revision C, dated November 10, 2010; for related
information.
Material Incorporated by Reference
(n) You must use Bombardier Service Bulletin 670BA-78-008,
Revision B, dated December 22, 2010; and Bombardier Service Bulletin
670SH-78-029, Revision C, dated November 10, 2010; as applicable; to
do the actions required by this AD, unless the AD specifies
otherwise.
(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., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; e-mail thd.crj@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 August 8, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-20673 Filed 8-19-11; 8:45 am]
BILLING CODE 4910-13-P
