Airworthiness Directives; Boeing Model 737-300, -400, and -500 Series Airplanes, 10469-10471 [E9-4734]
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<![CDATA[
10469
Federal Register / Vol. 74, No. 46 / Wednesday, March 11, 2009 / Rules and Regulations
Bombardier Canadair Regional Jet CRJ100/
200/440 Fault Isolation Manual CSP A–009,
Volume 1, Revision 38, dated January 10,
2008, contains the following effective pages:
List of Effective Pages
Page title/description
Page number(s)
Revision
number
FIM Title Page ...................................................
Transmittal Letter ...............................................
Record of Revisions ...........................................
FIM Volume 1 Title Page ...................................
None shown .............................
1 ...............................................
1 ...............................................
None shown .............................
38
38
....................
38
Date shown on page(s)
January
January
January
January
10,
10,
10,
10,
2008.
2008.
2008.
2008.
Chapter 27 Effective Pages
1–3 ...........................................
4 ...............................................
38
37
January 10, 2008.
January 10, 2007.
28
38
30
34
August 26, 2003.
January 10, 2008.
March 17, 2004.
April 10, 2005.
Section 27–50–00
101 ...........................................
102–153 ...................................
154, 156 ...................................
155 ...........................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information contained in Table 3
of this AD under 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE
Revision level
Bombardier Service Bulletin 601R–27–151 ...........................................................................
Bombardier Service Bulletin 601R–11–090 ...........................................................................
Canadair Regional Jet TR RJ/165–1, including pages 05–11–5 through 05–11–14, to the
Canadair Regional Jet AFM CSP A–012.
Canadair Regional Jet TR 05–035 to the Canadair Regional Jet AMM ................................
Section 27–50–00 of Chapter 27 of the Bombardier Canadair Regional Jet CRJ100/200/
440 Fault Isolation Manual CSP A–009, Volume 1.
rwilkins on PROD1PC63 with RULES
Service information
B .....................................
Original ...........................
Original ...........................
June 12, 2008.
August 15, 2008.
August 7, 2008.
Original ...........................
38 ...................................
July 13, 2007.
January 10, 2008.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Bombardier Service Bulletin
601R–27–150, including Appendix A, dated
July 12, 2007; and Canadair Regional Jet
Temporary Revision RJ/165, dated July 6,
2007, to the Canadair Regional Jet Airplane
Flight Manual CSP A–012; on September 5,
2007 (72 FR 46555, August 21, 2007).
(3) 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.
(4) 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 or 425–227–1152.
(5) 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.
VerDate Nov<24>2008
16:30 Mar 10, 2009
Jkt 217001
Issued in Renton, Washington, on February
26, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–5290 Filed 3–10–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0671; Directorate
Identifier 2008–NM–017–AD; Amendment
39–15796; AD 2009–02–06]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–300, –400, and –500 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
Date
Boeing Model 737–300, –400, and –500
series airplanes. This AD requires
repetitive high frequency eddy current
inspections for cracking of the 1.04-inch
nominal diameter wire penetration hole
in the frame and frame reinforcement,
between stringers S–20 and S–21, on
both the left and right sides of the
airplane, and related investigative and
corrective actions if necessary. This AD
results from reports of cracking in the
frame, or in the frame and frame
reinforcement, common to the 1.04-inch
nominal diameter wire penetration hole
intended for wire routing. We are
issuing this AD to detect and correct
cracking in the fuselage frames and
frame reinforcements, which could
reduce the structural capability of the
frames to sustain limit loads, and result
in cracking in the fuselage skin and
subsequent rapid depressurization of
the airplane.
DATES: This AD is effective April 15,
2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 15, 2009.
E:\FR\FM\11MRR1.SGM
11MRR1
10470
Federal Register / Vol. 74, No. 46 / Wednesday, March 11, 2009 / Rules and Regulations
For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1, fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
ADDRESSES:
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:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6447; fax (425) 917–6590.
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 Boeing Model 737–300, –400,
and –500 series airplanes. That NPRM
was published in the Federal Register
on June 24, 2008 (73 FR 35598). That
NPRM proposed to require repetitive
high frequency eddy current (HFEC)
inspections for cracking of the 1.04-inch
nominal diameter wire penetration hole
in the frame and frame reinforcement,
between stringers S–20 and S–21, on
both the left and right sides of the
airplane, and related investigative and
corrective actions if necessary.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received from
the single commenter.
Request To Revise Paragraph (h) To
Correct References to Parts of the
Service Bulletin
KLM Royal Dutch Airlines (KLM)
requests that we revise paragraph (h) of
the NPRM to correct the references to
certain parts of Boeing Alert Service
Bulletin 737–53A1279, dated December
18, 2007 (‘‘the service bulletin’’), for
doing certain actions. KLM points out
that paragraph (h) of the NPRM refers to
Part 3 of the service bulletin for doing
the repair and to Part 4 of the service
bulletin for doing the preventative
modification. KLM further points out
that Part 4 of the service bulletin
concerns repeat inspections, not the
preventative modification. The
preventative modification is provided in
Part 5 of the service bulletin.
We agree with the commenter. It was
our intention to refer to Part 5 of the
service bulletin for doing the
preventative modification provided in
paragraph (h) of the NPRM. Therefore,
we have revised paragraph (h) of this
AD to refer to Part 5 of the service
bulletin for doing the preventative
modification.
Request To Revise Paragraph (e) To
Clarify Compliance Times
KLM requests that we revise
paragraph (e) of the NPRM to refer to
paragraph 1.E., ‘‘Compliance,’’ of the
service bulletin. KLM asserts that
adding a reference to the location of the
compliance times in the service bulletin
would be helpful.
We do not agree to revise paragraph
(e) of this AD. A reference to paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 737–53A1279, dated December
18, 2007, is already provided in
paragraph (g) of this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
We also determined that this change
will not increase the economic burden
on any operator or increase the scope of
the AD.
Costs of Compliance
We estimate that this AD affects 616
airplanes of U.S. registry. The following
table provides the estimated costs for
U.S. operators to comply with this AD.
The average labor rate is $80 per work
hour.
ESTIMATED COSTS
Action
Work hours
Inspection ............................
Between 6 and 8 (depending on airplane configuration), per inspection cycle.
rwilkins on PROD1PC63 with RULES
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
VerDate Nov<24>2008
16:30 Mar 10, 2009
Jkt 217001
$0
Between $480 and $640,
per inspection cycle.
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
PO 00000
Frm 00016
Fmt 4700
Number
of U.S.registered
airplanes
Cost per
product
Parts
Sfmt 4700
616
Fleet cost
Between $295,680 and
$394,240, per inspection
cycle.
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
E:\FR\FM\11MRR1.SGM
11MRR1
Federal Register / Vol. 74, No. 46 / Wednesday, March 11, 2009 / Rules and Regulations
(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:
■
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:
■
2009–02–06 Boeing: Amendment 39–15796.
Docket No. FAA–2008–0671; Directorate
Identifier 2008–NM–017–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective April 15, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737–
300, –400, and –500 series airplanes,
certificated in any category; as identified in
Boeing Alert Service Bulletin 737–53A1279,
dated December 18, 2007.
Unsafe Condition
(d) This AD results from reports of cracking
in the frame, or in the frame and frame
reinforcement, common to the 1.04-inch
nominal diameter wire penetration hole
intended for wire routing. We are issuing this
AD to detect and correct cracking in the
fuselage frames and frame reinforcements,
which could reduce the structural capability
of the frames to sustain limit loads, and
result in cracking in the fuselage skin and
subsequent rapid depressurization of the
airplane.
rwilkins on PROD1PC63 with RULES
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Service Bulletin Reference Paragraph
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1279, dated December 18, 2007.
(1) The ‘‘condition’’ column of paragraph
1.E. of Boeing Alert Service Bulletin 737–
VerDate Nov<24>2008
16:30 Mar 10, 2009
Jkt 217001
53A1279, dated December 18, 2007, refers to
total flight cycles ‘‘at the date given on this
service bulletin.’’ This AD applies to the
airplanes with the specified total flight cycles
as of the effective date of this AD.
(2) Where the service bulletin specifies to
contact Boeing for instructions for removing
damage and repairing cracking: Before
further flight, remove the damage or repair
the cracking using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
(3) Although the service bulletin
referenced in this AD specifies to submit
information to the manufacturer, this AD
does not include that requirement.
Inspections, Related Investigative and
Corrective Actions
(g) At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of the service
bulletin, except as specified by paragraph
(f)(1) of this AD: Do a high frequency eddy
current (HFEC) surface inspection or an
HFEC hole/edge inspection for cracking of
the 1.04-inch nominal diameter wire
penetration hole in the frame and frame
reinforcement, between stringer S–20 and S–
21; and do all applicable related investigative
and corrective actions; by accomplishing all
the actions specified in the Accomplishment
Instructions of the service bulletin, except as
specified by paragraphs (f)(2) and (f)(3) of
this AD. Do all applicable related
investigative and corrective actions before
further flight. Thereafter, repeat the
inspections at the applicable intervals
specified in paragraph 1.E. of the service
bulletin.
Terminating Action
(h) Doing the repair in Part 3 or the
preventative modification in Part 5 of the
service bulletin terminates the repetitive
inspection requirements of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6447; fax (425)
917–6590; has the authority to approve
AMOCs for this AD, if requested using 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.
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
10471
Material Incorporated by Reference
(j) You must use Boeing Alert Service
Bulletin 737–53A1279, dated December 18,
2007, 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 Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1, fax 206–766–
5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
(3) You may review copies of the service
information incorporated by reference 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 or
425–227–1152.
(4) You may also review copies of the
service information 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 January
9, 2009.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E9–4734 Filed 3–10–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 30654; Amdt. No 3310]
Standard Instrument Approach
Procedures, and Takeoff Minimums
and Obstacle Departure Procedures;
Miscellaneous Amendments
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: This establishes, amends,
suspends, or revokes Standard
Instrument Approach Procedures
(SIAPs) and associated Takeoff
Minimums and Obstacle Departure
Procedures for operations at certain
airports. These regulatory actions are
needed because of the adoption of new
or revised criteria, or because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, adding new
obstacles, or changing air traffic
requirements. These changes are
designed to provide safe and efficient
E:\FR\FM\11MRR1.SGM
11MRR1
]]>Agencies
[Federal Register Volume 74, Number 46 (Wednesday, March 11, 2009)]
[Rules and Regulations]
[Pages 10469-10471]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-4734]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0671; Directorate Identifier 2008-NM-017-AD;
Amendment 39-15796; AD 2009-02-06]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-300, -400, and -500
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Boeing Model 737-300, -400, and -500 series airplanes. This AD requires
repetitive high frequency eddy current inspections for cracking of the
1.04-inch nominal diameter wire penetration hole in the frame and frame
reinforcement, between stringers S-20 and S-21, on both the left and
right sides of the airplane, and related investigative and corrective
actions if necessary. This AD results from reports of cracking in the
frame, or in the frame and frame reinforcement, common to the 1.04-inch
nominal diameter wire penetration hole intended for wire routing. We
are issuing this AD to detect and correct cracking in the fuselage
frames and frame reinforcements, which could reduce the structural
capability of the frames to sustain limit loads, and result in cracking
in the fuselage skin and subsequent rapid depressurization of the
airplane.
DATES: This AD is effective April 15, 2009.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 15,
2009.
[[Page 10470]]
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1, fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com.
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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6447; fax (425) 917-6590.
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 Boeing Model 737-300, -400, and -500 series airplanes. That
NPRM was published in the Federal Register on June 24, 2008 (73 FR
35598). That NPRM proposed to require repetitive high frequency eddy
current (HFEC) inspections for cracking of the 1.04-inch nominal
diameter wire penetration hole in the frame and frame reinforcement,
between stringers S-20 and S-21, on both the left and right sides of
the airplane, and related investigative and corrective actions if
necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received from the single commenter.
Request To Revise Paragraph (h) To Correct References to Parts of the
Service Bulletin
KLM Royal Dutch Airlines (KLM) requests that we revise paragraph
(h) of the NPRM to correct the references to certain parts of Boeing
Alert Service Bulletin 737-53A1279, dated December 18, 2007 (``the
service bulletin''), for doing certain actions. KLM points out that
paragraph (h) of the NPRM refers to Part 3 of the service bulletin for
doing the repair and to Part 4 of the service bulletin for doing the
preventative modification. KLM further points out that Part 4 of the
service bulletin concerns repeat inspections, not the preventative
modification. The preventative modification is provided in Part 5 of
the service bulletin.
We agree with the commenter. It was our intention to refer to Part
5 of the service bulletin for doing the preventative modification
provided in paragraph (h) of the NPRM. Therefore, we have revised
paragraph (h) of this AD to refer to Part 5 of the service bulletin for
doing the preventative modification.
Request To Revise Paragraph (e) To Clarify Compliance Times
KLM requests that we revise paragraph (e) of the NPRM to refer to
paragraph 1.E., ``Compliance,'' of the service bulletin. KLM asserts
that adding a reference to the location of the compliance times in the
service bulletin would be helpful.
We do not agree to revise paragraph (e) of this AD. A reference to
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-53A1279,
dated December 18, 2007, is already provided in paragraph (g) of this
AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the change described previously. We also determined that
this change will not increase the economic burden on any operator or
increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 616 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this AD. The average labor rate is $80 per work hour.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
U.S.-
Action Work hours Parts Cost per product registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
Inspection..................... Between 6 and 8 $0 Between $480 and 616 Between $295,680
(depending on $640, per and $394,240,
airplane inspection cycle. per inspection
configuration), cycle.
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
[[Page 10471]]
(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:
2009-02-06 Boeing: Amendment 39-15796. Docket No. FAA-2008-0671;
Directorate Identifier 2008-NM-017-AD.
Effective Date
(a) This airworthiness directive (AD) is effective April 15,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 737-300, -400, and -500
series airplanes, certificated in any category; as identified in
Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007.
Unsafe Condition
(d) This AD results from reports of cracking in the frame, or in
the frame and frame reinforcement, common to the 1.04-inch nominal
diameter wire penetration hole intended for wire routing. We are
issuing this AD to detect and correct cracking in the fuselage
frames and frame reinforcements, which could reduce the structural
capability of the frames to sustain limit loads, and result in
cracking in the fuselage skin and subsequent rapid depressurization
of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Service Bulletin Reference Paragraph
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1279, dated December 18, 2007.
(1) The ``condition'' column of paragraph 1.E. of Boeing Alert
Service Bulletin 737-53A1279, dated December 18, 2007, refers to
total flight cycles ``at the date given on this service bulletin.''
This AD applies to the airplanes with the specified total flight
cycles as of the effective date of this AD.
(2) Where the service bulletin specifies to contact Boeing for
instructions for removing damage and repairing cracking: Before
further flight, remove the damage or repair the cracking using a
method approved in accordance with the procedures specified in
paragraph (i) of this AD.
(3) Although the service bulletin referenced in this AD
specifies to submit information to the manufacturer, this AD does
not include that requirement.
Inspections, Related Investigative and Corrective Actions
(g) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of the service bulletin, except as specified by
paragraph (f)(1) of this AD: Do a high frequency eddy current (HFEC)
surface inspection or an HFEC hole/edge inspection for cracking of
the 1.04-inch nominal diameter wire penetration hole in the frame
and frame reinforcement, between stringer S-20 and S-21; and do all
applicable related investigative and corrective actions; by
accomplishing all the actions specified in the Accomplishment
Instructions of the service bulletin, except as specified by
paragraphs (f)(2) and (f)(3) of this AD. Do all applicable related
investigative and corrective actions before further flight.
Thereafter, repeat the inspections at the applicable intervals
specified in paragraph 1.E. of the service bulletin.
Terminating Action
(h) Doing the repair in Part 3 or the preventative modification
in Part 5 of the service bulletin terminates the repetitive
inspection requirements of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-
120S, 1601 Lind Avenue, SW., Renton, Washington 98057-3356;
telephone (425) 917-6447; fax (425) 917-6590; has the authority to
approve AMOCs for this AD, if requested using 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.
Material Incorporated by Reference
(j) You must use Boeing Alert Service Bulletin 737-53A1279,
dated December 18, 2007, 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
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1, fax 206-766-5680; e-mail
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information
incorporated by reference 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 or 425-227-1152.
(4) You may also review copies of the service information 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 January 9, 2009.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9-4734 Filed 3-10-09; 8:45 am]
BILLING CODE 4910-13-P
