[Federal Register Volume 78, Number 206 (Thursday, October 24, 2013)]
[Proposed Rules]
[Pages 63431-63433]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-24975]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0866; Directorate Identifier 2013-NM-131-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. This proposed AD was prompted by reports of cracks
found in the aft support fitting, the rear spar upper chord, and the
rear spar web. This proposed AD would require repetitive inspections
for cracking of the aft support fitting for the main landing gear (MLG)
beam, and the rear spar upper chord and rear spar web in the area of
rear spar station (RSS) 224.14; and repair if necessary. We are
proposing this AD to detect and correct such cracks, which could grow
and result in a fuel leak and possible fire.
DATES: We must receive comments on this proposed AD by December 9,
2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service
information at the FAA, at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-
917-6440; fax: 425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2013-0866;
Directorate Identifier 2013-NM-131-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received five reports of cracks found in the aft support
fitting for the MLG beam, and the rear spar upper chord and rear spar
web in the area of rear spar station (RSS) 224.14. One report was of a
vertical crack found in the rear spar web, along with cracks in the aft
support fitting and rear spar upper chord. A second report indicated
cracks found in two holes in the rear spar upper chord and rear spar
web. A third report was of a crack in the rear spar upper chord that
extended downward to the edge of the vertical flange and upward to the
horizontal flange. The affected airplanes had accumulated between
42,988 and 66,572 total flight hours, and between 29,015
[[Page 63432]]
and 60,238 total flight cycles. Analysis shows that cracks in the aft
support fitting, rear spar web, and rear spar upper chord are caused by
operating load fatigue. Such cracks, if not corrected, could grow and
result in a fuel leak and possible fire.
Related Rulemaking
AD 2005-18-08, Amendment 39-14248 (70 FR 52899, September 6, 2005)
(``AD 2005-18-08''), affects certain Model 737-100, -200, -200C, and -
300 series airplanes. AD 2005-18-08 requires--as one of two options for
corrective action--replacement of the support fitting of the MLG beam
in accordance with Boeing Special Attention Service Bulletin 737-57-
1216. This replacement also terminates the inspections required by AD
2005-18-08. The compliance times for certain inspections specified in
this proposed AD depend on accomplishment of that optional action in AD
2005-18-08.
Relevant Service Information
We reviewed Boeing Special Attention Service Bulletin 737-57-1318,
dated May 15, 2013. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2013-0866.
FAA's Determination
We are proposing 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 same type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information identified previously, except as discussed
below.
Differences Between the Proposed AD and the Service Information
Boeing Special Attention Service Bulletin 737-57-1318, dated May
15, 2013, specifies to contact the manufacturer for instructions on how
to inspect certain airplanes, and how to repair cracks detected on all
airplanes, but this proposed AD would require that those actions be
done in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD affects 353 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection..................... Up to 86 work-hours x $0 Up to $7,310 per Up to $2,580,430
$85 per hour = $7,310 inspection cycle. per inspection
per inspection cycle. cycle.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
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
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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 airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2013-0866; Directorate Identifier
2013-NM-131-AD.
(a) Comments Due Date
We must receive comments by December 9, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of cracks found in the aft
support fitting for the main
[[Page 63433]]
landing gear (MLG) beam, and the rear spar upper chord and rear spar
web. We are issuing this AD to detect and correct such cracks, which
could grow and result in a fuel leak and possible fire.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections: Group 1
For airplanes identified in Group 1 of Boeing Special Attention
Service Bulletin 737-57-1318, dated May 15, 2013: At the applicable
time specified in paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-57-1318, dated May 15, 2013, except
as required by paragraph (i) of this AD, do inspections and
applicable corrective actions using a method approved in accordance
with the procedures specified in paragraph (j) of this AD.
(h) Inspection: Groups 2-7
For airplanes identified in Groups 2 through 7 of Boeing Special
Attention Service Bulletin 737-57-1318, dated May 15, 2013: At the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 737-57-1318, dated May 15,
2013, except as required by paragraph (i) of this AD, do high
frequency eddy current inspections to detect cracking of the aft
support fitting for the MLG beam, and the rear spar upper chord and
rear spar web in the area of rear spar station 224.14, as
applicable, in accordance with Option 1, 2, or 3 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-57-1318, dated May 15, 2013.
(1) If no crack is found, repeat the inspection thereafter at
the time specified in paragraph 1.E., ``Compliance,'' of Boeing
Special Attention Service Bulletin 737-57-1318, dated May 15, 2013,
as applicable. Accomplishment of the inspection of the 12 fastener
holes (locations 1-12) in accordance with Option 2, Action 3; or
Option 3, Action 3; as specified in note (b) of tables 2 through 5
of paragraph 1.E., ``Compliance,'' of Boeing Special Attention
Service Bulletin 737-57-1318, dated May 15, 2013, terminates only
the corresponding inspections that include note (b) in the ``Repeat
Interval'' column of the applicable table.
(2) If any crack is found during any inspection required by this
paragraph, repair before further flight using a method approved in
accordance with the procedures specified in paragraph (j) of this
AD.
(i) Exception to Service Information Specifications
Where Boeing Special Attention Service Bulletin 737-57-1318,
dated May 15, 2013, specifies a compliance time ``after the original
issue date of this service bulletin,'' this AD requires compliance
within the specified compliance time after the effective date of
this AD.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(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 the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA), which 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.
(k) Related Information
(1) For more information about this AD, contact Nancy Marsh,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: 425-917-6440; fax: 425-917-6590; email:
[email protected].
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on October 17, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-24975 Filed 10-23-13; 8:45 am]
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