[Federal Register Volume 78, Number 124 (Thursday, June 27, 2013)]
[Proposed Rules]
[Pages 38608-38610]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-15425]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 78, No. 124 / Thursday, June 27, 2013 /
Proposed Rules
[[Page 38608]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0538; Directorate Identifier 2012-NM-212-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
certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and
-500 series airplanes. This proposed AD was prompted by a report of
cracks in stringer splices at body station STA 360 and STA 908, between
stringer (S) S-10L and S-10R; cracks in butt straps between S-5L and S-
3L, and S-3R and S-5R; vertical chem-mill fuselage skin cracks at
certain butt joints; and an instance of cracking that occurred in all
those three structural elements on one airplane. This proposed AD would
require repetitive inspections for any cracking of stringer splices and
butt straps, and related corrective and investigative actions if
necessary. We are proposing this AD to detect and correct cracking in
the three structural elements, which could result in the airplane not
being able to sustain limit load requirements and possibly result in
uncontrolled decompression.
DATES: We must receive comments on this proposed AD by August 12, 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, 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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6447;
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-2013-0538;
Directorate Identifier 2012-NM-212-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 received reports of 197 stringer splice cracks at body station
(STA) 360 and STA 908, between stringer (S) S-10L and S-10R; 16 butt
strap cracks between S-5L and S-3L, and S-3R and S-5R; and 12 vertical
chem-mill fuselage skin cracks at certain butt joints. On one airplane,
a maintenance inspection found that all three structural elements were
cracked. Analysis indicates the cracking of the stringer splices is
attributed to airplane fatigue loads. Cracking of the butt strap at STA
360 and STA 908 is attributed to fatigue loading from the S-4 lap
joint. This condition, if not corrected, could result in the airplane
not being able to sustain limit load requirements and possibly result
in uncontrolled decompression.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 737-53A1322, dated
November 5, 2012. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2013-0538.
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 described previously, except as discussed
under ``Differences Between the Proposed AD and the Service
Information.''
The phrase ``related investigative actions'' might be used in this
proposed AD. ``Related investigative actions'' are follow-on actions
that: (1) Are related to the primary actions, and (2) are actions that
further investigate the nature of any condition found. Related
investigative
[[Page 38609]]
actions in an AD could include, for example, inspections.
In addition, the phrase ``corrective actions'' might be used in
this proposed AD. ``Corrective actions'' are actions that correct or
address any condition found. Corrective actions in an AD could include,
for example, repairs.
Differences Between the Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-53A1322, dated November 5, 2012,
specifies to contact the manufacturer for instructions on how to repair
certain conditions, but this proposed AD would require repairing those
conditions 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.
Boeing Alert Service Bulletin 737-53A1322, dated November 5, 2012,
specifies to contact the manufacturer for instructions on how to
inspect airplanes having line number 1 through 291, but this proposed
AD would require inspections in accordance with a method we approve.
Costs of Compliance
We estimate that this proposed AD affects 612 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspections...................... Up to 362 work-hours None Up to $30,770, per Up to $18,831,240,
x $85 per hour = inspection cycle. per inspection
$30,770, per cycle
inspection cycle.
Removal and reinstallation of Up to 2 work-hours x $0 Up to $170, per Up to $104,040, per
butt strap fastener(s). $85 per hour = inspection cycle. inspection cycle
$170, per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
these replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Stringer splice replacement.............. 3 work-hours x $85 per hour Operator-supplied, $255
= $255. information not available.
----------------------------------------------------------------------------------------------------------------
The work-hour estimate and parts cost information are not available
for estimating the cost of a butt strap replacement.
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-2013-0538; Directorate Identifier
2012-NM-212-AD.
(a) Comments Due Date
We must receive comments by August 12, 2013.
[[Page 38610]]
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certified in any
category, as identified in Boeing Alert Service Bulletin 737-
53A1322, dated November 5, 2012.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of cracks in stringer splices
at body station STA 360 and STA 908, between stringer (S) S-10L and
S-10R; cracks in butt straps between S-5L and S-3L, and S-3R and S-
5R; vertical chem-mill fuselage skin cracks at certain butt joints;
and an instance of cracking that occurred in all those three
structural elements on one airplane. We are issuing this AD to
detect and correct cracking in the three structural elements, which
could result in the airplane not being able to sustain limit load
requirements and possibly result in uncontrolled decompression.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions for Group 1 Airplanes
For Group 1 airplanes, as identified in Boeing Alert Service
Bulletin 737-53A1322, dated November 5, 2012: At the compliance time
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1322, dated November 5, 2012, except as provided by
paragraph (j)(2) of this AD, inspect the stringers and butt straps
and repair as applicable, using a method approved in accordance with
the procedures specified in paragraph (k) of this AD.
(h) Actions for Groups 2 Through 6 Airplanes
For Groups 2 through 6 airplanes, as identified in Boeing Alert
Service Bulletin 737-53A1322, dated November 5, 2012: At the
applicable compliance time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1322, dated
November 5, 2012, do the applicable inspections for cracking
identified in paragraphs (h)(1) through (h)(4) of this AD, and all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1322, dated
November 5, 2012, except as provided by paragraph (j) of this AD. Do
all applicable corrective actions before further flight. Thereafter,
repeat the applicable inspections at the compliance times specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1322, dated November 5, 2012. Accomplishing the corrective
actions for a cracked stringer splice, as specified in Boeing Alert
Service Bulletin 737-53A1322, dated November 5, 2012, terminates the
repetitive inspections required by this paragraph for that stringer
splice only.
(1) Internal detailed inspections of the stringer splices and
butt straps.
(2) Internal high-frequency eddy current (HFEC) surface
inspections of the butt straps.
(3) Internal low-frequency eddy current (LFEC) inspection of the
butt straps.
(4) HFEC open hole rotary probe inspections of butt straps or of
one location of a butt strap, as applicable.
(i) Post-Repair Inspections
The post-repair inspection specified in Table 11 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1322,
dated November 5, 2012, is not required by this AD.
Note 1 to paragraph (i) of this AD: The post-repair inspections
specified in Table 11 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1322, dated November 5, 2012, may be
used in support of compliance with section 121.1109(c)(2) or
129.109(b)(2) of the Federal Aviation Regulations (14 CFR
121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions
specified in the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1322, dated November 5, 2012, are not required by
this AD.
(j) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin 737-53A1322, dated
November 5, 2012, specifies to contact Boeing for appropriate
action: Before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (k) of this
AD.
(2) Where Boeing Alert Service Bulletin 737-53A1322, dated
November 5, 2012, 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.
(k) 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) that 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.
(l) Related Information
(1) For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: (425) 917-6447; 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 June 13, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-15425 Filed 6-26-13; 8:45 am]
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