Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 53704-53706 [E7-18539]
Download as PDF
53704
Federal Register / Vol. 72, No. 182 / Thursday, September 20, 2007 / Proposed Rules
accordance with the service bulletin or
Boeing Special Attention Service Bulletin
767–27–0197 or 767–27–0198, both dated
October 27, 2005, whichever occurs first.
Repetitive Lubrication
(j) Repeat the lubrication required in
paragraph (i) of this AD at the applicable
interval specified in paragraph (j)(1) or (j)(2)
of this AD.
(1) For airplanes on which BMS 3–33
grease is not already in use prior to the time
the lubrication task is being accomplished:
At intervals not to exceed 3,000 flight hours
or 9 months, whichever occurs first.
(2) For airplanes on which BMS 3–33
grease is already in use prior to the time the
lubrication task is being accomplished: At
intervals not to exceed 6,000 flight hours or
18 months, whichever occurs first.
Repetitive Prior or Concurrent Inspection
(k) For airplanes specified in paragraphs
(k)(1) and (k)(2) of this AD: Prior to or
concurrently with the accomplishment of
each elevator freeplay measurement specified
in paragraph (g) of this AD, do all applicable
actions required by AD 2001–04–09.
(1) Group 1, configuration 2, airplanes as
identified in Boeing Special Attention
Service Bulletin 767–27–0197, Revision 1,
dated July 19, 2007.
(2) Group 1, configuration 1, airplanes as
identified in Boeing Special Attention
Service Bulletin 767–27–0198, Revision 1,
dated July 19, 2007.
pwalker on PROD1PC71 with PROPOSALS
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 2006–11–12 are
approved as AMOCs for the corresponding
provisions of this AD.
(5) AMOCs approved previously in
accordance with AD 2001–04–09, are
approved as AMOCs for the corresponding
provisions of paragraph (k) of this AD.
VerDate Aug<31>2005
17:12 Sep 19, 2007
Jkt 211001
Issued in Renton, Washington, on
September 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–18544 Filed 9–19–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29257; Directorate
Identifier 2007–NM–144–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model CL–600–
2B19 (Regional Jet Series 100 & 440)
airplanes. This proposed AD would
require repetitive detailed inspections
for cracking of the left side and right
side frame and reinforcement angles at
fuselage station (FS) 640 between
stringer 9 and stringer 12, and corrective
actions if necessary. This proposed AD
results from reports that cracks have
been discovered on the frame and
reinforcement angles at FS 640. We are
proposing this AD to detect and correct
cracking of the frame, which could lead
to failure of the fuselage structure and
possible loss of the airplane.
DATES: We must receive comments on
this proposed AD by October 22, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• 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.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Bombardier, Inc., Canadair,
Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec
H3C 3G9, Canada, for service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Pong K. Lee, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7324; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2007–29257; Directorate
Identifier 2007–NM–144–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Operations office (telephone
(800) 647–5527) is located on the
ground level of the West Building at the
DOT street address stated in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
the Docket Management System receives
them.
E:\FR\FM\20SEP1.SGM
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Federal Register / Vol. 72, No. 182 / Thursday, September 20, 2007 / Proposed Rules
Discussion
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, notified us that an
unsafe condition may exist on certain
Bombardier Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. TCCA advises that cracks
have been discovered on the frame and
reinforcement angles at fuselage station
(FS) 640 on a number of CRJ (Canadair
Regional Jet) airplanes. This condition,
if not corrected, could result in failure
of the fuselage structure and possible
loss of the airplane.
Relevant Service Information
Bombardier has issued Alert Service
Bulletin 601R–53–061, Revision E,
dated December 7, 2006. The alert
service bulletin describes procedures for
doing repetitive detailed visual
inspections for cracking of the frame at
fuselage station (FS) 640 between
stringer 9 and stringer 12 (Part A of the
Accomplishment Instructions) and, if
necessary, corrective actions as follows:
• Repair as described in Part A of the
Accomplishment Instructions;
• Install a modification, including
related investigative and corrective
actions; or
• Contact Bombardier for repair
instructions.
The related investigative and corrective
actions of the modification (Part C of the
Accomplishment Instructions) include
cutting out a section of the flange frame
at FS640 then doing a liquid penetrant
or eddy current inspection for cracking
of the skin doubler, and contacting
Bombardier for repair instructions.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition. TCCA mandated the service
information and issued Canadian
airworthiness directive CF–2003–12,
dated May 7, 2003, to ensure the
continued airworthiness of these
airplanes in Canada.
pwalker on PROD1PC71 with PROPOSALS
FAA’s Determination and Requirements
of the Proposed AD
These airplanes are manufactured in
Canada and are type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Pursuant to
this bilateral airworthiness agreement,
TCCA has kept the FAA informed of the
situation described above. We have
examined TCCA’s findings, evaluated
all pertinent information, and
determined that we need to issue an AD
for airplanes of this type design that are
VerDate Aug<31>2005
17:12 Sep 19, 2007
Jkt 211001
53705
certificated for operation in the United
States.
Therefore, we are proposing this AD,
which would require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Between the Proposed AD and
Bombardier Alert Service Bulletin/
Canadian Airworthiness Directive.’’
Costs of Compliance
This proposed AD would affect about
739 airplanes of U.S. registry. The
proposed inspection would take about 2
work hours per airplane, at an average
labor rate of $80 per work hour. Based
on these figures, the estimated cost of
the proposed AD for U.S. operators is
$118,240, or $160 per airplane, per
inspection cycle.
Differences Between the Proposed AD
and Bombardier Alert Service Bulletin/
Canadian Airworthiness Directive
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.
The Canadian airworthiness directive
specifies that Bombardier Alert Service
Bulletin 601R–53–061, Revision B,
dated February 20, 2003, or later
revisions, must be used to do all
described inspections and actions.
However, we have determined that
Revision E, dated December 7, 2006, of
the alert service bulletin no longer
contains certain actions described by
Revision B. Therefore, this proposed AD
would require doing all actions in
accordance with Alert Service Bulletin
601R–53–061, Revision E, dated
December 7, 2006. This difference has
been coordinated with TCCA.
In this proposed AD, the ‘‘detailed
visual inspection’’ specified in the
Bombardier alert service bulletin and
Canadian airworthiness directive is
referred to as a ‘‘detailed inspection.’’
We have included the definition for a
detailed inspection in a note in the
proposed AD.
The Bombardier alert service bulletin
and Canadian airworthiness directive
specify to contact Bombardier for
instructions on how to repair certain
conditions, but this proposed AD would
require repairing those conditions using
a method approved by the FAA or
TCCA (or its delegated agent). In light of
the type of repair that would be required
to address the unsafe condition, and
consistent with existing bilateral
airworthiness agreements, we have
determined that, for this proposed AD,
a repair approved by the FAA or TCCA
(or its delegated agent) would be
acceptable for compliance with this
proposed AD.
Although the Accomplishment
Instructions of the alert service bulletin
describe procedures for submitting
certain information to the manufacturer,
this proposed AD would not require that
action.
Interim Action
We consider this proposed AD
interim action. If final action is later
identified, we might consider further
rulemaking then.
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
E:\FR\FM\20SEP1.SGM
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53706
Federal Register / Vol. 72, No. 182 / Thursday, September 20, 2007 / Proposed Rules
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Bombardier, Inc. (Formerly Canadair):
Docket No. FAA–2007–29257;
Directorate Identifier 2007–NM–144–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by November 5, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
CL–600–2B19 (Regional Jet Series 100 & 440)
airplanes, certificated in any category; as
identified in Bombardier Alert Service
Bulletin 601R–53–061, Revision E, dated
December 7, 2006.
Unsafe Condition
(d) This AD results from reports that cracks
have been discovered on the frame and
reinforcement angles at fuselage station (FS)
640. Failure of this frame could degrade the
structural integrity of the airplane. We are
issuing this AD to detect and correct cracking
of the frame, which could lead to failure of
the fuselage structure and possible loss of the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
pwalker on PROD1PC71 with PROPOSALS
Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Bombardier Alert Service
Bulletin 601R–53–061, Revision E, dated
December 7, 2006.
Detailed Inspection
(g) Before the accumulation of 8,600 total
flight cycles or within 1,100 flight cycles
after the effective date of this AD, whichever
occurs later: Perform a detailed inspection to
detect cracking of the left side and right side
frames and reinforcement angles at FS640
between stringer 9 and stringer 12, in
accordance with Part A of the
Accomplishment Instructions of the service
bulletin.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
VerDate Aug<31>2005
17:12 Sep 19, 2007
Jkt 211001
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Repetitive Inspection and Corrective Action
(h) If no crack is found during the
inspection required by paragraph (g) of this
AD: Repeat the detailed inspection thereafter
at intervals not to exceed 1,100 flight cycles,
until the frame modification described in
paragraph (i)(2) of this AD has been done.
(i) If any crack is found during the
inspection required by paragraph (g) of this
AD: Before further flight, repair the crack in
accordance with paragraph (i)(1), (i)(2), or
(i)(3) of this AD, as applicable.
(1) For any crack found in the frame at the
stringer 9 cut-out only, repair in accordance
with Part A of the Accomplishment
Instructions of the service bulletin.
(2) For any crack found in the frame
reinforcement doubler only: Do the frame
modification (including related investigative
and corrective actions) described in Part C of
the Accomplishment Instructions of the
service bulletin, except where the alert
service bulletin specifies to contact the
manufacturer for repair instructions, repair
the crack using a method approved by either
the Manager, New York Aircraft Certification
Office (ACO), FAA; or Transport Canada
Civil Aviation (TCCA) (or its delegated
agent); then do the detailed inspection
required by paragraph (j) of this AD.
(3) For any crack found in areas of the
inspection zone described in paragraph (g) of
this AD other than those described in
paragraphs (i)(1) and (i)(2) of this AD: Repair
the crack using a method approved by either
the Manager, New York ACO, FAA; or TCCA
(or its delegated agent).
Repetitive Inspection After Frame
Modification
(j) Within 12,000 flight cycles after doing
the modification described in paragraph (i)(2)
of this AD, do the detailed inspection
required by paragraph (g) of this AD. Repeat
the detailed inspection thereafter at intervals
not to exceed 1,100 flight cycles.
No Reporting Requirement
(k) Although the alert service bulletin
referred to in this AD specifies to submit
certain information to the manufacturer, this
AD does not include that requirement.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, New York ACO, FAA,
has the authority to approve AMOCs for this
AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. 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
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(m) Canadian airworthiness directive CF–
2003–12, dated May 7, 2003, also addresses
the subject of this AD.
Issued in Renton, Washington, on
September 12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–18539 Filed 9–19–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29255; Directorate
Identifier 2007–NM–085–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 737–100, –200,
–200C, –300, –400, and –500 series
airplanes. This proposed AD would
require doing repetitive internal eddy
current and detailed inspections to
detect cracked stringer tie clips; doing
applicable corrective and related
investigative actions, if necessary; and
measuring the fastener spacing and the
edge margin; as applicable. As a
temporary alternative to doing the
actions described previously, this
proposed AD would require repetitive
external general visual inspections of
the skin and lap joints for cracks and
evidence of overload resulting from
cracked stringer tie clips, and applicable
corrective actions if necessary. This
proposed AD results from a report of
several cracked stringer tie clips. We are
proposing this AD to prevent multiple
cracked stringer tie clips and damaged
skin and frames, which could lead to
the skin and frame structure developing
cracks and consequent decompression
of the airplane.
DATES: We must receive comments on
this proposed AD by November 5, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
E:\FR\FM\20SEP1.SGM
20SEP1
Agencies
[Federal Register Volume 72, Number 182 (Thursday, September 20, 2007)]
[Proposed Rules]
[Pages 53704-53706]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-18539]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29257; Directorate Identifier 2007-NM-144-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 &
440) airplanes. This proposed AD would require repetitive detailed
inspections for cracking of the left side and right side frame and
reinforcement angles at fuselage station (FS) 640 between stringer 9
and stringer 12, and corrective actions if necessary. This proposed AD
results from reports that cracks have been discovered on the frame and
reinforcement angles at FS 640. We are proposing this AD to detect and
correct cracking of the frame, which could lead to failure of the
fuselage structure and possible loss of the airplane.
DATES: We must receive comments on this proposed AD by October 22,
2007.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
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.
Fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087,
Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Pong K. Lee, Aerospace Engineer,
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7324; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
29257; Directorate Identifier 2007-NM-144-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Operations office between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
Docket Operations office (telephone (800) 647-5527) is located on the
ground level of the West Building at the DOT street address stated in
the ADDRESSES section. Comments will be available in the AD docket
shortly after the Docket Management System receives them.
[[Page 53705]]
Discussion
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, notified us that an unsafe condition may exist on
certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes. TCCA advises that cracks have been discovered on the frame
and reinforcement angles at fuselage station (FS) 640 on a number of
CRJ (Canadair Regional Jet) airplanes. This condition, if not
corrected, could result in failure of the fuselage structure and
possible loss of the airplane.
Relevant Service Information
Bombardier has issued Alert Service Bulletin 601R-53-061, Revision
E, dated December 7, 2006. The alert service bulletin describes
procedures for doing repetitive detailed visual inspections for
cracking of the frame at fuselage station (FS) 640 between stringer 9
and stringer 12 (Part A of the Accomplishment Instructions) and, if
necessary, corrective actions as follows:
Repair as described in Part A of the Accomplishment
Instructions;
Install a modification, including related investigative
and corrective actions; or
Contact Bombardier for repair instructions.
The related investigative and corrective actions of the modification
(Part C of the Accomplishment Instructions) include cutting out a
section of the flange frame at FS640 then doing a liquid penetrant or
eddy current inspection for cracking of the skin doubler, and
contacting Bombardier for repair instructions. Accomplishing the
actions specified in the service information is intended to adequately
address the unsafe condition. TCCA mandated the service information and
issued Canadian airworthiness directive CF-2003-12, dated May 7, 2003,
to ensure the continued airworthiness of these airplanes in Canada.
FAA's Determination and Requirements of the Proposed AD
These airplanes are manufactured in Canada and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, TCCA has kept the FAA informed of
the situation described above. We have examined TCCA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Between
the Proposed AD and Bombardier Alert Service Bulletin/Canadian
Airworthiness Directive.''
Differences Between the Proposed AD and Bombardier Alert Service
Bulletin/Canadian Airworthiness Directive
The Canadian airworthiness directive specifies that Bombardier
Alert Service Bulletin 601R-53-061, Revision B, dated February 20,
2003, or later revisions, must be used to do all described inspections
and actions. However, we have determined that Revision E, dated
December 7, 2006, of the alert service bulletin no longer contains
certain actions described by Revision B. Therefore, this proposed AD
would require doing all actions in accordance with Alert Service
Bulletin 601R-53-061, Revision E, dated December 7, 2006. This
difference has been coordinated with TCCA.
In this proposed AD, the ``detailed visual inspection'' specified
in the Bombardier alert service bulletin and Canadian airworthiness
directive is referred to as a ``detailed inspection.'' We have included
the definition for a detailed inspection in a note in the proposed AD.
The Bombardier alert service bulletin and Canadian airworthiness
directive specify to contact Bombardier for instructions on how to
repair certain conditions, but this proposed AD would require repairing
those conditions using a method approved by the FAA or TCCA (or its
delegated agent). In light of the type of repair that would be required
to address the unsafe condition, and consistent with existing bilateral
airworthiness agreements, we have determined that, for this proposed
AD, a repair approved by the FAA or TCCA (or its delegated agent) would
be acceptable for compliance with this proposed AD.
Although the Accomplishment Instructions of the alert service
bulletin describe procedures for submitting certain information to the
manufacturer, this proposed AD would not require that action.
Interim Action
We consider this proposed AD interim action. If final action is
later identified, we might consider further rulemaking then.
Costs of Compliance
This proposed AD would affect about 739 airplanes of U.S. registry.
The proposed inspection would take about 2 work hours per airplane, at
an average labor rate of $80 per work hour. Based on these figures, the
estimated cost of the proposed AD for U.S. operators is $118,240, or
$160 per airplane, per inspection cycle.
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 have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
[[Page 53706]]
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
Bombardier, Inc. (Formerly Canadair): Docket No. FAA-2007-29257;
Directorate Identifier 2007-NM-144-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by November
5, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) airplanes, certificated in any category; as
identified in Bombardier Alert Service Bulletin 601R-53-061,
Revision E, dated December 7, 2006.
Unsafe Condition
(d) This AD results from reports that cracks have been
discovered on the frame and reinforcement angles at fuselage station
(FS) 640. Failure of this frame could degrade the structural
integrity of the airplane. We are issuing this AD to detect and
correct cracking of the frame, which could lead to failure of the
fuselage structure and possible loss of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Bombardier Alert Service Bulletin
601R-53-061, Revision E, dated December 7, 2006.
Detailed Inspection
(g) Before the accumulation of 8,600 total flight cycles or
within 1,100 flight cycles after the effective date of this AD,
whichever occurs later: Perform a detailed inspection to detect
cracking of the left side and right side frames and reinforcement
angles at FS640 between stringer 9 and stringer 12, in accordance
with Part A of the Accomplishment Instructions of the service
bulletin.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repetitive Inspection and Corrective Action
(h) If no crack is found during the inspection required by
paragraph (g) of this AD: Repeat the detailed inspection thereafter
at intervals not to exceed 1,100 flight cycles, until the frame
modification described in paragraph (i)(2) of this AD has been done.
(i) If any crack is found during the inspection required by
paragraph (g) of this AD: Before further flight, repair the crack in
accordance with paragraph (i)(1), (i)(2), or (i)(3) of this AD, as
applicable.
(1) For any crack found in the frame at the stringer 9 cut-out
only, repair in accordance with Part A of the Accomplishment
Instructions of the service bulletin.
(2) For any crack found in the frame reinforcement doubler only:
Do the frame modification (including related investigative and
corrective actions) described in Part C of the Accomplishment
Instructions of the service bulletin, except where the alert service
bulletin specifies to contact the manufacturer for repair
instructions, repair the crack using a method approved by either the
Manager, New York Aircraft Certification Office (ACO), FAA; or
Transport Canada Civil Aviation (TCCA) (or its delegated agent);
then do the detailed inspection required by paragraph (j) of this
AD.
(3) For any crack found in areas of the inspection zone
described in paragraph (g) of this AD other than those described in
paragraphs (i)(1) and (i)(2) of this AD: Repair the crack using a
method approved by either the Manager, New York ACO, FAA; or TCCA
(or its delegated agent).
Repetitive Inspection After Frame Modification
(j) Within 12,000 flight cycles after doing the modification
described in paragraph (i)(2) of this AD, do the detailed inspection
required by paragraph (g) of this AD. Repeat the detailed inspection
thereafter at intervals not to exceed 1,100 flight cycles.
No Reporting Requirement
(k) Although the alert service bulletin referred to in this AD
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, New York ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
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.
Related Information
(m) Canadian airworthiness directive CF-2003-12, dated May 7,
2003, also addresses the subject of this AD.
Issued in Renton, Washington, on September 12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-18539 Filed 9-19-07; 8:45 am]
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