Airworthiness Directives; Boeing Model 737-300, -400, and -500 Series Airplanes, 56958-56960 [E8-22755]
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56958
Federal Register / Vol. 73, No. 191 / Wednesday, October 1, 2008 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2008–17–13 Boeing: Amendment 39–15651.
Docket No. FAA–2008–0149; Directorate
Identifier 2007–NM–319–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective November 5, 2008.
Affected ADs
(b) None.
series airplanes, certificated in any category;
as identified in Boeing Alert Service Bulletin
737–38A1054, dated August 23, 2007.
Unsafe Condition
(d) This AD results from a report of a
separated hose assembly for the passenger
water system. We are issuing this AD to
prevent a water leak into the flight deck
ceiling, which could result in an electrical
short and possible loss of several functions
essential to safe flight.
Compliance
Applicability
(c) This AD applies to Boeing Model 737–
100, –200, –200C, –300, –400, and –500
(e) Comply with this AD within the
compliance times specified, unless already
done.
Replacement
(f) Within 60 months after the effective
date of this AD, replace the existing straightto-90-degree hose assembly for the Lavatory
‘‘A’’ water supply with a new straight hose
assembly and a separate 90-degree elbow
fitting, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–38A1054, dated August
23, 2007.
Parts Installation
(g) As of the effective date of this AD, any
hose assembly part having a part number
identified in Table 1 of this AD must not be
used in any location that is subject to the
requirements of this AD. However, those
parts may be used in other locations if not
otherwise prohibited.
TABLE 1—SPARE PARTS PROHIBITED FOR THIS AD
Airplane group identified in Boeing Alert
Service Bulletin 737–38A1054,
dated August 23, 2007
Existing part number(s)
1 and 2 .....................................................................................................
3 ................................................................................................................
4 ................................................................................................................
10–61998–430, AS4471–08–0401, or AS4471–08–0404.
10–61998–25 or 10–60871–125.
10–61998–31 or 10–60871–139.
Alternative Methods of Compliance
(AMOCs)
code_of_federal_regulations/
ibr_locations.html.
(h)(1) The Manager, Seattle Aircraft
Certification Office, FAA, ATTN: Marcia
Smith, Aerospace Engineer, Cabin Safety and
Environmental Systems Branch, ANM–150S,
1601 Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6484; 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.
Issued in Renton, Washington, on August
6, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–22649 Filed 9–30–08; 8:45 am]
ebenthall on PROD1PC60 with RULES
Material Incorporated by Reference
(i) You must use Boeing Alert Service
Bulletin 737–38A1054, dated August 23,
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, P.O. Box 3707, Seattle,
Washington 98124–2207.
(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/
VerDate Aug<31>2005
15:26 Sep 30, 2008
Jkt 217001
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0947; Directorate
Identifier 2008–NM–154–AD; Amendment
39–15670; AD 2008–19–03]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–300, –400, and –500 Series
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Boeing Model 737–300, –400, and –500
series airplanes. This AD requires
repetitive external detailed inspections
or non-destructive inspections to detect
cracks in the fuselage skin along the
chem-mill steps at stringers S–1 and S–
2R, between station (STA) 400 and STA
460, and repair if necessary. This AD
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results from reports of cracks in the
fuselage skin common to stringer S–1
and between STA 400 and STA 460. We
are issuing this AD to detect and correct
fatigue cracking of the fuselage skin
panels at the chem-mill steps, which
could result in sudden fracture and
failure of the fuselage skin panels, and
consequent rapid decompression of the
airplane.
DATES: This AD is effective October 16,
2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 16, 2008.
We must receive comments on this
AD by December 1, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
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Federal Register / Vol. 73, No. 191 / Wednesday, October 1, 2008 / Rules and Regulations
later. For the repetitive inspections, the
service bulletin specifies repeat
intervals ranging between 1,200 and
4,500 flight cycles, depending on the
airplane configuration and the type of
inspection previously done.
Discussion
We received three reports of cracks in
the fuselage skin common to stringer S–
1 and between station (STA) 400 and
STA 460. In all three cases, there were
cracks in adjacent 10-inch tear strap
bays. In one case, there were cracks in
four adjacent 10-inch tear strap bays.
The cracks measured between 4.0 and
10.5 inches long. The airplanes had
accumulated between 42,038 and 57,523
total flight cycles. Analysis indicates
that the cracks were caused by fatigue
due to high tension stresses and local
bending at the edge of the chem-mill
pockets of the bonded fuselage skin.
Airplanes with 20-inch tear strap bays
are also susceptible to cracks at this
location. Fatigue cracking of the
fuselage skin panels at the chem-mill
steps, if not detected and corrected,
could result in sudden fracture and
failure of the fuselage skin panels, and
consequent rapid decompression of the
airplane.
ebenthall on PROD1PC60 with RULES
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 street address for
the Docket Office (telephone 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
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:
Boeing Alert Service Bulletin 737–
53A1293, dated August 13, 2008,
specifies contacting the manufacturer
for instructions on how to repair a
certain condition, but this AD requires
repairing that condition in one of the
following ways:
• Using a method that we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by an
Authorized Representative for the
Boeing Commercial Airplanes
Delegation Option Authorization
Organization whom we have authorized
to make those findings.
Relevant Service Information
We reviewed Boeing Alert Service
Bulletin 737–53A1293, dated August 13,
2008. The service bulletin describes
procedures for repetitive external
detailed inspections or non-destructive
inspections (NDI) to detect cracks in the
fuselage skin along the chem-mill steps
at stringers S–1 and S–2R between STA
400 and STA 460, and contacting
Boeing for repair instructions. The NDI
inspections that can be used are
medium frequency eddy current,
magneto optical imaging, or c-scan. For
the initial inspection, the service
bulletin specifies a compliance time of
before 35,000 total flight cycles, or
within 500 flight cycles after the date on
the service bulletin, whichever occurs
VerDate Aug<31>2005
15:26 Sep 30, 2008
Jkt 217001
FAA’s Determination and Requirements
of This AD
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the(se)
same type design(s). This AD requires
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Difference Between the AD and the
Service Information.’’
Difference Between the AD and the
Service Information
Interim Action
We consider this AD interim action. If
final action is later identified, we might
consider further rulemaking then.
FAA’s Justification and Determination
of the Effective Date
We are issuing this AD to detect and
correct fatigue cracking of the fuselage
skin panels at the chem-mill steps,
which could result in sudden fracture
and failure of the fuselage skin panels,
and consequent rapid decompression of
the airplane. Because of our requirement
to promote safe flight of civil aircraft
and thus, the critical need to assure the
structural integrity of the fuselage and
the short compliance time involved
with this action, this AD must be issued
immediately.
Because an unsafe condition exists
that requires the immediate adoption of
this AD, we find that notice and
opportunity for prior public comment
hereon are impracticable and that good
cause exists for making this amendment
effective in less than 30 days.
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56959
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2008–0947; Directorate Identifier 2008–
NM–154–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
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,
E:\FR\FM\01OCR1.SGM
01OCR1
56960
Federal Register / Vol. 73, No. 191 / Wednesday, October 1, 2008 / Rules and Regulations
(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.
specifies a compliance time after the date on
the service bulletin, this AD requires
compliance within the specified compliance
time after the effective date of this AD: Do
repetitive external detailed inspections or
non-destructive inspections (NDI) to detect
cracks in the fuselage skin along the chemmill steps at stringers S–1 and S–2R, between
STA 400 and STA 460, by accomplishing the
applicable inspections specified in the
Accomplishment Instructions of the service
bulletin.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Repair
(g) If any crack is found during any
inspection required by paragraph (f) of this
AD, before further flight, repair the cracked
fuselage skin using a method approved in
accordance with the procedures specified in
paragraph (h) of this AD.
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:
■
2008–19–03 Boeing: Amendment 39–15670.
Docket No. FAA–2008–0947; Directorate
Identifier 2008–NM–154–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective October 16, 2008.
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 737–53A1293,
dated August 13, 2008.
Unsafe Condition
(d) This AD results from reports of cracks
in the fuselage skin common to stringer
S–1 and between station (STA) 400 and STA
460. We are issuing this AD to detect and
correct fatigue cracking of the fuselage skin
panels at the chem-mill steps, which could
result in sudden fracture and failure of the
fuselage skin panels, and consequent rapid
decompression of the airplane.
ebenthall on PROD1PC60 with RULES
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Repetitive Inspections
(f) At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1293, dated
August 13, 2008 (hereafter ‘‘the service
bulletin’’); except where the service bulletin
VerDate Aug<31>2005
15:26 Sep 30, 2008
Jkt 217001
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 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
(i) You must use Boeing Alert Service
Bulletin 737–53A1293, dated August 13,
2008, 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, P.O. Box 3707, Seattle,
Washington 98124–2207.
(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.
PO 00000
Frm 00026
Fmt 4700
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Issued in Renton, Washington, on
September 11, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–22755 Filed 9–30–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–29227; Directorate
Identifier 2007–NM–100–AD; Amendment
39–15664; AD 2008–18–07]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–300,
747–400, 747–400D, and 747SR Series
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Boeing Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–
300, 747–400, 747–400D, and 747SR
series airplanes. For certain airplanes,
this AD requires a material type
inspection to determine if the lower
forward corner reveal of the number 3
main entry doors (MEDs) is a casting. If
the reveals are castings, this AD requires
repetitive inspections of the reveals for
cracking, and corrective action if
necessary. If the reveals are not castings,
this AD requires a detailed inspection of
the reveals for a sharp edge and
repetitive inspections of the reveals for
cracking, and corrective action if
necessary. For certain other airplanes,
this AD requires only a detailed
inspection of the reveals for a sharp
edge and repetitive inspections of the
reveals for cracking, and corrective
action if necessary. For certain other
airplanes, this AD requires repetitive
inspections of the reveals for cracking
only, and corrective action if necessary.
This AD also allows a certain
replacement as an optional action for
the material type inspection for certain
airplanes. This AD results from reports
of cracking and/or a sharp edge in the
lower forward corner reveal of the
number 3 MEDs. We are issuing this AD
to detect and correct fatigue cracking of
the lower forward corner reveal of the
number 3 MEDs, which could lead to
the door escape slide departing the
airplane when the door is opened and
the slide is deployed, and consequent
E:\FR\FM\01OCR1.SGM
01OCR1
]]>Agencies
[Federal Register Volume 73, Number 191 (Wednesday, October 1, 2008)]
[Rules and Regulations]
[Pages 56958-56960]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-22755]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0947; Directorate Identifier 2008-NM-154-AD;
Amendment 39-15670; AD 2008-19-03]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-300, -400, and -500
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Boeing Model 737-300, -400, and -500 series airplanes. This AD requires
repetitive external detailed inspections or non-destructive inspections
to detect cracks in the fuselage skin along the chem-mill steps at
stringers S-1 and S-2R, between station (STA) 400 and STA 460, and
repair if necessary. This AD results from reports of cracks in the
fuselage skin common to stringer S-1 and between STA 400 and STA 460.
We are issuing this AD to detect and correct fatigue cracking of the
fuselage skin panels at the chem-mill steps, which could result in
sudden fracture and failure of the fuselage skin panels, and consequent
rapid decompression of the airplane.
DATES: This AD is effective October 16, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 16,
2008.
We must receive comments on this AD by December 1, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
[[Page 56959]]
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 street address for
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: 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 received three reports of cracks in the fuselage skin common to
stringer S-1 and between station (STA) 400 and STA 460. In all three
cases, there were cracks in adjacent 10-inch tear strap bays. In one
case, there were cracks in four adjacent 10-inch tear strap bays. The
cracks measured between 4.0 and 10.5 inches long. The airplanes had
accumulated between 42,038 and 57,523 total flight cycles. Analysis
indicates that the cracks were caused by fatigue due to high tension
stresses and local bending at the edge of the chem-mill pockets of the
bonded fuselage skin. Airplanes with 20-inch tear strap bays are also
susceptible to cracks at this location. Fatigue cracking of the
fuselage skin panels at the chem-mill steps, if not detected and
corrected, could result in sudden fracture and failure of the fuselage
skin panels, and consequent rapid decompression of the airplane.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 737-53A1293, dated August
13, 2008. The service bulletin describes procedures for repetitive
external detailed inspections or non-destructive inspections (NDI) to
detect cracks in the fuselage skin along the chem-mill steps at
stringers S-1 and S-2R between STA 400 and STA 460, and contacting
Boeing for repair instructions. The NDI inspections that can be used
are medium frequency eddy current, magneto optical imaging, or c-scan.
For the initial inspection, the service bulletin specifies a compliance
time of before 35,000 total flight cycles, or within 500 flight cycles
after the date on the service bulletin, whichever occurs later. For the
repetitive inspections, the service bulletin specifies repeat intervals
ranging between 1,200 and 4,500 flight cycles, depending on the
airplane configuration and the type of inspection previously done.
FAA's Determination and Requirements of This AD
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This AD requires accomplishing the actions specified in the
service information described previously, except as discussed under
``Difference Between the AD and the Service Information.''
Difference Between the AD and the Service Information
Boeing Alert Service Bulletin 737-53A1293, dated August 13, 2008,
specifies contacting the manufacturer for instructions on how to repair
a certain condition, but this AD requires repairing that condition in
one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Interim Action
We consider this AD interim action. If final action is later
identified, we might consider further rulemaking then.
FAA's Justification and Determination of the Effective Date
We are issuing this AD to detect and correct fatigue cracking of
the fuselage skin panels at the chem-mill steps, which could result in
sudden fracture and failure of the fuselage skin panels, and consequent
rapid decompression of the airplane. Because of our requirement to
promote safe flight of civil aircraft and thus, the critical need to
assure the structural integrity of the fuselage and the short
compliance time involved with this action, this AD must be issued
immediately.
Because an unsafe condition exists that requires the immediate
adoption of this AD, we find that notice and opportunity for prior
public comment hereon are impracticable and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2008-0947; Directorate Identifier 2008-NM-154-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
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,
[[Page 56960]]
(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:
2008-19-03 Boeing: Amendment 39-15670. Docket No. FAA-2008-0947;
Directorate Identifier 2008-NM-154-AD.
Effective Date
(a) This airworthiness directive (AD) is effective October 16,
2008.
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 737-53A1293, dated August 13, 2008.
Unsafe Condition
(d) This AD results from reports of cracks in the fuselage skin
common to stringer S-1 and between station (STA) 400 and STA 460. We
are issuing this AD to detect and correct fatigue cracking of the
fuselage skin panels at the chem-mill steps, which could result in
sudden fracture and failure of the fuselage skin panels, and
consequent rapid decompression of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Repetitive Inspections
(f) At the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293, dated
August 13, 2008 (hereafter ``the service bulletin''); except where
the service bulletin specifies a compliance time after the date on
the service bulletin, this AD requires compliance within the
specified compliance time after the effective date of this AD: Do
repetitive external detailed inspections or non-destructive
inspections (NDI) to detect cracks in the fuselage skin along the
chem-mill steps at stringers S-1 and S-2R, between STA 400 and STA
460, by accomplishing the applicable inspections specified in the
Accomplishment Instructions of the service bulletin.
Repair
(g) If any crack is found during any inspection required by
paragraph (f) of this AD, before further flight, repair the cracked
fuselage skin using a method approved in accordance with the
procedures specified in paragraph (h) of this AD.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-
120S, FAA, Seattle ACO, 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
(i) You must use Boeing Alert Service Bulletin 737-53A1293,
dated August 13, 2008, 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, P.O. Box 3707, Seattle, Washington
98124-2207.
(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 September 11, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-22755 Filed 9-30-08; 8:45 am]
BILLING CODE 4910-13-P
