Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 13120-13122 [E8-4644]
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13120
Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
Revision
level
Document
Page Nos.
SAAB SF340A Airplane Flight Manual, AFM 340 A
001.
SAAB 340B Airplane Flight Manual, 72LKS5968 .......
SAAB 340B Airplane Flight Manual, AFM 340 B 001
List of Effective Pages: Pages 1–4 through 1–6 ........
51
November 30, 2007.
List of Effective Pages: Pages 1–4 through 1–7 ........
List of Effective Pages: Pages 1–4 through 1–6 ........
21
29
November 30, 2007.
November 30, 2007.
(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 Saab Aircraft AB, SAAB
Aircraft Product Support, S–581.88,
¨
Linkoping, Sweden.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on March 3,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–4660 Filed 3–11–08; 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; Amendment
39–15422; AD 2008–06–10]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2B19 (Regional Jet
Series 100 & 440) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
jlentini on PROD1PC65 with RULES
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Bombardier Model CL–600–2B19
(Regional Jet Series 100 & 440)
airplanes. This AD requires 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 AD also provides an optional
terminating action for the repetitive
inspections. This AD results from
reports that cracks have been discovered
on the frame and reinforcement angles
VerDate Aug<31>2005
17:40 Mar 11, 2008
Jkt 214001
at FS 640. 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.
DATES: This AD is effective April 16,
2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 16, 2008.
ADDRESSES: For service information
identified in this AD, contact
Bombardier, Inc., Canadair, Aerospace
Group, P.O. Box 6087, Station Centreville, Montreal, Quebec H3C 3G9,
Canada.
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 (telephone 800–647–5527)
is the 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:
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:
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
certain Bombardier Model CL–600–
2B19 (Regional Jet Series 100 & 440)
airplanes. That NPRM was published in
the Federal Register on September 20,
2007 (72 FR 53704). That NPRM
proposed to require repetitive detailed
inspections for cracking of the left side
and right side frame and reinforcement
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Date
angles at fuselage station (FS) 640
between stringer 9 and stringer 12, and
corrective actions if necessary.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comments received.
Request To Address Possible
Terminating Modification
Air Wisconsin requests that we
consider including a possible
terminating modification in the NPRM.
Air Wisconsin states that the NPRM
does not recognize other options that
can be taken to modify FS640. Air
Wisconsin continues that, in fact, a
certain option is significantly better,
providing a higher level of safety than
the modification in Part C of
Bombardier Service Bulletin 601R–53–
061, Revision E, dated December 7,
2006, including Appendix B, Revision
C, dated June 25, 2003 (cited as the
appropriate source of service
information for doing the proposed
actions described in the NPRM), which
is an interim modification requiring
further inspections. Air Wisconsin
continues that Transport Canada Civil
Aviation (TCCA) issued an alternate
means of compliance (AMOC)
indicating that the inspections of
Service Bulletin 601R–53–061 can be
terminated by doing applicable actions
described in Bombardier Alert Service
Bulletin A601R–53–059, Revision E,
dated March 21, 2005 (or later); or
Bombardier Service Bulletin 601R–53–
065, Revision A, dated August 24, 2005
(or later). Air Wisconsin states it has
already modified 23 airplanes using
Service Bulletin A601R–53–059,
Revision E; or Bombardier Alert Service
Bulletin A601R–53–059, Revision F,
dated April 21, 2006; and intends to
modify all its other affected airplanes
within the next one to two years. Air
Wisconsin asserts that any AD issued
against Service Bulletin 601R–53–061
should specify that doing the applicable
actions described in Service Bulletin
A601R–53–059, Revision E or F; or
Service Bulletin 601R–53–065, Revision
A; is acceptable for terminating the
repetitive inspections of Service
Bulletin 601R–53–061.
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Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
jlentini on PROD1PC65 with RULES
We agree with this request. In the
NPRM, we stated that we considered the
proposed AD to be interim action, and
that we might consider further
rulemaking if final action was later
identified. We have determined that Air
Wisconsin’s request addresses
appropriate final action, as described in
the following service information. We
have reviewed Bombardier Alert Service
Bulletin A601R–53–059, Revision E,
dated March 21, 2005, and Revision F,
dated April 21, 2006; and Bombardier
Service Bulletin 601R–53–065, Revision
A, dated August 24, 2005, and Revision
B, dated November 2, 2007. The service
bulletins describe procedures for
reinforcing the engine support beams
that are acceptable for terminating the
repetitive inspections described by
Service Bulletin 601R–53–061, Revision
E. We have determined that any
reinforcement of the engine support
beam done in accordance with Part A,
B, or C, as applicable, of Alert Service
Bulletin A601R 53–059, Revision E or F;
or in accordance with Service Bulletin
601R–53–065, Revision A or B; is
acceptable as optional terminating
action for the repetitive inspections
required by this AD. Therefore, we have
added this service information to the
AD; deleted existing paragraph (f) of the
NPRM; revised subsequent paragraphs
(g), (h), and (i) of this AD, and reidentified them as paragraphs (f), (g),
and (h); relocated and reidentified
paragraph (j) of the NPRM as new
paragraph (h)(2)(ii) of this AD; added
new paragraph (i) of this AD to describe
the optional terminating action; and
reidentified subsequent paragraphs (k),
(l), and (m) of the NPRM, as paragraphs
(j), (k), and (l) of this AD.
Request for Clarification of Special
Flight Permits
Comair requests that we clarify
paragraph (i) of the NPRM (paragraph
(h) of this AD) regarding relocation of
airplanes to service facilities after the
discovery of cracking. Comair is
concerned that the requirement to repair
the crack before further flight forbids
moving the airplane to a repair facility
to accomplish the repair. Comair cites
earlier ADs that included a provision for
obtaining special flight permits to move
airplanes to repair facilities in
accordance with sections 21.197 and
21.199 of the Federal Aviation
Regulations (14 CFR 21.197 and 21.199).
Comair requests that such a statement
be inserted into the NPRM.
We do not agree with this request. On
July 10, 2002, we issued a new version
of 14 CFR part 39 (67 FR 47997, July 22,
2002), which governs our ADs. Part 39
now includes material that relates to
VerDate Aug<31>2005
17:40 Mar 11, 2008
Jkt 214001
altered products, special flight permits,
and AMOCs. Because this material now
appears in part 39, an AD refers to
special flight permits only when
relocation flights are limited or not
permitted. In that case, in accordance
with 14 CFR 21.197 and 21.199 as
described by the commenter, operators
may apply for a special flight permit to
move affected airplanes. However,
special flights are neither limited nor
prohibited by this AD; therefore, ‘‘before
further flight’’ in this AD applies to any
flight other than the flight taken to
relocate the airplane to the repair
facility. We have not changed the AD in
this regard.
Conclusion
We reviewed the available data,
including the comments 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.
Costs of Compliance
This AD affects about 739 airplanes of
U.S. registry. The required inspection
takes 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 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
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
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Fmt 4700
Sfmt 4700
13121
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), 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.
You can find our regulatory
evaluation and the estimated costs of
compliance 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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2008–06–10 Bombardier, Inc. (Formerly
Canadair): Amendment 39–15422.
Docket No. FAA–2007–29257;
Directorate Identifier 2007–NM–144–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective April 16, 2008.
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 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.
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13122
Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations
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.
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Detailed Inspection
(f) 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 Bombardier
Service Bulletin 601R–53–061, Revision E,
dated December 7, 2006.
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
(g) If no crack is found during the
inspection required by paragraph (f) of this
AD: Repeat the detailed inspection thereafter
at intervals not to exceed 1,100 flight cycles,
until the frame modification described in
paragraph (h)(2) of this AD or the optional
terminating modification described in
paragraph (i) of this AD has been done.
(h) 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 (h)(1), (h)(2), or
(h)(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 Bombardier Service Bulletin
601R–53–061, Revision E, dated December 7,
2006.
(2) For any crack found in the frame
reinforcement doubler only, do the actions
described in paragraphs (h)(2)(i) and (h)(2)(ii)
of this AD.
(i) Do the frame modification (including
related investigative and corrective actions)
described in Part C of the Accomplishment
Instructions of Bombardier Service Bulletin
601R–53–061, Revision E, dated December 7,
2006; except where the 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).
(ii) Within 12,000 flight cycles after doing
the modification required by paragraph
(h)(2)(i) of this AD, do the detailed inspection
required by paragraph (f) of this AD, then
repeat the detailed inspection thereafter at
intervals not to exceed 1,100 flight cycles.
(3) For any crack found in areas of the
inspection zone described in paragraph (f) of
this AD other than those areas described in
paragraphs (h)(1) and (h)(2) of this AD:
VerDate Aug<31>2005
17:40 Mar 11, 2008
Jkt 214001
Repair the crack using a method approved by
either the Manager, New York ACO, FAA; or
TCCA (or its delegated agent).
Optional Terminating Action
(i) Reinforcement of any engine support
beam in accordance with the
Accomplishment Instructions of the service
information described in paragraph (i)(1) or
(i)(2) of this AD, as applicable, ends all
repetitive inspections required by this AD for
that support beam.
(1) For all airplanes: If the reinforcement is
done before the effective date of this AD,
Bombardier Alert Service Bulletin A601R–
53–059, Revision E, dated March 21, 2005; or
Revision F, dated April 21, 2006; may be
used. After the effective date of this AD, only
Bombardier Alert Service Bulletin A601R–
53–059, Revision F, may be used.
(2) For airplanes identified in Bombardier
Service Bulletin 601R–53–065, Revision B,
dated November 2, 2007: If the reinforcement
is done before the effective date of this AD,
Bombardier Service Bulletin 601R–53–065,
Revision A, dated August 24, 2005, or
Revision B, may be used. After the effective
date of this AD, only Bombardier Service
Bulletin 601R–53–065, Revision B, may be
used.
No Reporting Requirement
(j) Although Bombardier Service Bulletin
601R–53–061, Revision E, dated December 7,
2006, specifies to submit certain information
to the manufacturer, this AD does not
include that requirement.
Alternative Methods of Compliance
(AMOCs)
(k)(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
(l) Canadian airworthiness directive CF–
2003–12, dated May 7, 2003, also addresses
the subject of this AD.
Material Incorporated by Reference
(m) You must use Bombardier Service
Bulletin 601R–53–061, Revision E, dated
December 7, 2006, including Appendix B,
Revision C, dated June 25, 2003, to do the
actions required by this AD, unless the AD
specifies otherwise. If you accomplish the
optional actions specified by this AD, you
must use Bombardier Alert Service Bulletin
A601R–53–059, Revision F, dated April 21,
2006, excluding Appendix A, dated June 14,
2001; or Bombardier Service Bulletin 601R–
53–065, Revision B, dated November 2, 2007;
as applicable; to perform those actions,
unless the AD specifies otherwise.
Bombardier Service Bulletin 601R–53–061,
Revision E, dated December 7, 2006, includes
the following effective pages:
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Page Nos.
Revision
level
shown on
page
1–44 ...........
E
Date shown on
page
December 7,
2006.
Appendix B
B1–B8 ........
C
June 25, 2003.
(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., Canadair,
Aerospace Group, P.O. Box 6087, Station
Centre-ville, Montreal, Quebec H3C 3G9,
Canada.
(3) You may review copies of the service
information incorporated by reference at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington; or 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 March 3,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–4644 Filed 3–11–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2007–28529; Airspace
Docket No. 07–ANM–12]
Modification of Class E Airspace;
Tucson, AZ
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action will modify Class
E airspace at Tucson, AZ. Additional
controlled airspace is necessary to
encompass holding patterns and
intermediate segments at Tucson
International Airport. The FAA is
proposing this action to enhance the
safety and management of Instrument
Flight Rules (IFR) operations at Tucson
International Airport, Tucson, AZ.
DATES: Effective Date: 0901 UTC, June 5,
2008. The Director of the Federal
Register approves this incorporation by
reference action under 1 CFR part 51,
subject to the annual revision of FAA
E:\FR\FM\12MRR1.SGM
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]]>Agencies
[Federal Register Volume 73, Number 49 (Wednesday, March 12, 2008)]
[Rules and Regulations]
[Pages 13120-13122]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-4644]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-29257; Directorate Identifier 2007-NM-144-AD;
Amendment 39-15422; AD 2008-06-10]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional
Jet Series 100 & 440) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes.
This AD requires 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 AD also provides an optional terminating
action for the repetitive inspections. This AD results from reports
that cracks have been discovered on the frame and reinforcement angles
at FS 640. 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.
DATES: This AD is effective April 16, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 16,
2008.
ADDRESSES: For service information identified in this AD, contact
Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station
Centre-ville, Montreal, Quebec H3C 3G9, Canada.
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 (telephone 800-647-5527) is the 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: 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:
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
certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes. That NPRM was published in the Federal Register on September
20, 2007 (72 FR 53704). That NPRM proposed to 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.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comments received.
Request To Address Possible Terminating Modification
Air Wisconsin requests that we consider including a possible
terminating modification in the NPRM. Air Wisconsin states that the
NPRM does not recognize other options that can be taken to modify
FS640. Air Wisconsin continues that, in fact, a certain option is
significantly better, providing a higher level of safety than the
modification in Part C of Bombardier Service Bulletin 601R-53-061,
Revision E, dated December 7, 2006, including Appendix B, Revision C,
dated June 25, 2003 (cited as the appropriate source of service
information for doing the proposed actions described in the NPRM),
which is an interim modification requiring further inspections. Air
Wisconsin continues that Transport Canada Civil Aviation (TCCA) issued
an alternate means of compliance (AMOC) indicating that the inspections
of Service Bulletin 601R-53-061 can be terminated by doing applicable
actions described in Bombardier Alert Service Bulletin A601R-53-059,
Revision E, dated March 21, 2005 (or later); or Bombardier Service
Bulletin 601R-53-065, Revision A, dated August 24, 2005 (or later). Air
Wisconsin states it has already modified 23 airplanes using Service
Bulletin A601R-53-059, Revision E; or Bombardier Alert Service Bulletin
A601R-53-059, Revision F, dated April 21, 2006; and intends to modify
all its other affected airplanes within the next one to two years. Air
Wisconsin asserts that any AD issued against Service Bulletin 601R-53-
061 should specify that doing the applicable actions described in
Service Bulletin A601R-53-059, Revision E or F; or Service Bulletin
601R-53-065, Revision A; is acceptable for terminating the repetitive
inspections of Service Bulletin 601R-53-061.
[[Page 13121]]
We agree with this request. In the NPRM, we stated that we
considered the proposed AD to be interim action, and that we might
consider further rulemaking if final action was later identified. We
have determined that Air Wisconsin's request addresses appropriate
final action, as described in the following service information. We
have reviewed Bombardier Alert Service Bulletin A601R-53-059, Revision
E, dated March 21, 2005, and Revision F, dated April 21, 2006; and
Bombardier Service Bulletin 601R-53-065, Revision A, dated August 24,
2005, and Revision B, dated November 2, 2007. The service bulletins
describe procedures for reinforcing the engine support beams that are
acceptable for terminating the repetitive inspections described by
Service Bulletin 601R-53-061, Revision E. We have determined that any
reinforcement of the engine support beam done in accordance with Part
A, B, or C, as applicable, of Alert Service Bulletin A601R 53-059,
Revision E or F; or in accordance with Service Bulletin 601R-53-065,
Revision A or B; is acceptable as optional terminating action for the
repetitive inspections required by this AD. Therefore, we have added
this service information to the AD; deleted existing paragraph (f) of
the NPRM; revised subsequent paragraphs (g), (h), and (i) of this AD,
and re-identified them as paragraphs (f), (g), and (h); relocated and
reidentified paragraph (j) of the NPRM as new paragraph (h)(2)(ii) of
this AD; added new paragraph (i) of this AD to describe the optional
terminating action; and reidentified subsequent paragraphs (k), (l),
and (m) of the NPRM, as paragraphs (j), (k), and (l) of this AD.
Request for Clarification of Special Flight Permits
Comair requests that we clarify paragraph (i) of the NPRM
(paragraph (h) of this AD) regarding relocation of airplanes to service
facilities after the discovery of cracking. Comair is concerned that
the requirement to repair the crack before further flight forbids
moving the airplane to a repair facility to accomplish the repair.
Comair cites earlier ADs that included a provision for obtaining
special flight permits to move airplanes to repair facilities in
accordance with sections 21.197 and 21.199 of the Federal Aviation
Regulations (14 CFR 21.197 and 21.199). Comair requests that such a
statement be inserted into the NPRM.
We do not agree with this request. On July 10, 2002, we issued a
new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which
governs our ADs. Part 39 now includes material that relates to altered
products, special flight permits, and AMOCs. Because this material now
appears in part 39, an AD refers to special flight permits only when
relocation flights are limited or not permitted. In that case, in
accordance with 14 CFR 21.197 and 21.199 as described by the commenter,
operators may apply for a special flight permit to move affected
airplanes. However, special flights are neither limited nor prohibited
by this AD; therefore, ``before further flight'' in this AD applies to
any flight other than the flight taken to relocate the airplane to the
repair facility. We have not changed the AD in this regard.
Conclusion
We reviewed the available data, including the comments 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.
Costs of Compliance
This AD affects about 739 airplanes of U.S. registry. The required
inspection takes 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 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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979), 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.
You can find our regulatory evaluation and the estimated costs of
compliance 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
0
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:
2008-06-10 Bombardier, Inc. (Formerly Canadair): Amendment 39-15422.
Docket No. FAA-2007-29257; Directorate Identifier 2007-NM-144-AD.
Effective Date
(a) This airworthiness directive (AD) is effective April 16,
2008.
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 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.
[[Page 13122]]
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.
Detailed Inspection
(f) 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 Bombardier Service
Bulletin 601R-53-061, Revision E, dated December 7, 2006.
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
(g) If no crack is found during the inspection required by
paragraph (f) of this AD: Repeat the detailed inspection thereafter
at intervals not to exceed 1,100 flight cycles, until the frame
modification described in paragraph (h)(2) of this AD or the
optional terminating modification described in paragraph (i) of this
AD has been done.
(h) 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 (h)(1), (h)(2), or (h)(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 Bombardier Service Bulletin 601R-53-061, Revision E,
dated December 7, 2006.
(2) For any crack found in the frame reinforcement doubler only,
do the actions described in paragraphs (h)(2)(i) and (h)(2)(ii) of
this AD.
(i) Do the frame modification (including related investigative
and corrective actions) described in Part C of the Accomplishment
Instructions of Bombardier Service Bulletin 601R-53-061, Revision E,
dated December 7, 2006; except where the 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).
(ii) Within 12,000 flight cycles after doing the modification
required by paragraph (h)(2)(i) of this AD, do the detailed
inspection required by paragraph (f) of this AD, then repeat the
detailed inspection thereafter at intervals not to exceed 1,100
flight cycles.
(3) For any crack found in areas of the inspection zone
described in paragraph (f) of this AD other than those areas
described in paragraphs (h)(1) and (h)(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).
Optional Terminating Action
(i) Reinforcement of any engine support beam in accordance with
the Accomplishment Instructions of the service information described
in paragraph (i)(1) or (i)(2) of this AD, as applicable, ends all
repetitive inspections required by this AD for that support beam.
(1) For all airplanes: If the reinforcement is done before the
effective date of this AD, Bombardier Alert Service Bulletin A601R-
53-059, Revision E, dated March 21, 2005; or Revision F, dated April
21, 2006; may be used. After the effective date of this AD, only
Bombardier Alert Service Bulletin A601R-53-059, Revision F, may be
used.
(2) For airplanes identified in Bombardier Service Bulletin
601R-53-065, Revision B, dated November 2, 2007: If the
reinforcement is done before the effective date of this AD,
Bombardier Service Bulletin 601R-53-065, Revision A, dated August
24, 2005, or Revision B, may be used. After the effective date of
this AD, only Bombardier Service Bulletin 601R-53-065, Revision B,
may be used.
No Reporting Requirement
(j) Although Bombardier Service Bulletin 601R-53-061, Revision
E, dated December 7, 2006, specifies to submit certain information
to the manufacturer, this AD does not include that requirement.
Alternative Methods of Compliance (AMOCs)
(k)(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
(l) Canadian airworthiness directive CF-2003-12, dated May 7,
2003, also addresses the subject of this AD.
Material Incorporated by Reference
(m) You must use Bombardier Service Bulletin 601R-53-061,
Revision E, dated December 7, 2006, including Appendix B, Revision
C, dated June 25, 2003, to do the actions required by this AD,
unless the AD specifies otherwise. If you accomplish the optional
actions specified by this AD, you must use Bombardier Alert Service
Bulletin A601R-53-059, Revision F, dated April 21, 2006, excluding
Appendix A, dated June 14, 2001; or Bombardier Service Bulletin
601R-53-065, Revision B, dated November 2, 2007; as applicable; to
perform those actions, unless the AD specifies otherwise. Bombardier
Service Bulletin 601R-53-061, Revision E, dated December 7, 2006,
includes the following effective pages:
------------------------------------------------------------------------
Revision
level
Page Nos. shown on Date shown on page
page
------------------------------------------------------------------------
1-44............................. E December 7, 2006.
------------------------------------------------------------------------
Appendix B
------------------------------------------------------------------------
B1-B8............................ C June 25, 2003.
------------------------------------------------------------------------
(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., Canadair, Aerospace Group, P.O. Box 6087, Station
Centre-ville, Montreal, Quebec H3C 3G9, Canada.
(3) You may review copies of the service information
incorporated by reference at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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 March 3, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-4644 Filed 3-11-08; 8:45 am]
BILLING CODE 4910-13-P
