[Federal Register Volume 78, Number 71 (Friday, April 12, 2013)]
[Proposed Rules]
[Pages 21854-21856]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-08610]
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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. 71 / Friday, April 12, 2013 /
Proposed Rules
[[Page 21854]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0303; Directorate Identifier 2012-NM-220-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 747-400 and -400F series airplanes.
This proposed AD was prompted by a report of cracks on airplanes prior
to line number 1308 in the forward and aft inner chords of the station
(STA) 2598 bulkhead, and the bulkhead upper and lower webs. This
proposed AD would require, as applicable, repetitive high frequency
eddy current (HFEC) and low frequency eddy current (LFEC) inspections
for cracks in the splice fitting, support frame, forward and aft inner
chords, floor support, bulkhead upper web on the upper left and right
side of the bulkhead, and the bulkhead lower web on the lower left side
of the bulkhead and repair if necessary; and repetitive post-repair
inspections and repair if necessary. We are proposing this AD to detect
and correct cracks in the splice fitting, support frame, floor support,
forward and aft inner chords, and the bulkhead upper and lower webs of
the body station, which could adversely affect the structural integrity
of the airplane.
DATES: We must receive comments on this proposed AD by May 28, 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, WA. 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: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 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-2013-0303;
Directorate Identifier 2012-NM-220-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 a report of cracks, on airplanes prior to line number
1308, in the forward and aft inner chords of the STA 2598 bulkhead, the
bulkhead upper and lower webs near the inner chord to shear deck
connection in the STA 2598 bulkhead, the forward and aft inner chords
and bulkhead upper web in the upper corners of the cutout for the
horizontal stabilizer rear spar, and the aft inner chord and lower
bulkhead web in the lower corner of the cutout for the horizontal
stabilizer rear spar. On airplanes line numbers 1308 through 1419,
although there was a production change to the STA 2598 bulkhead,
analysis showed that cracks could still occur in the structure. This
condition, if not corrected, could adversely affect the structural
integrity of the airplane.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 747-53A2815, dated
November 8, 2012. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2013-0303.
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
[[Page 21855]]
AD. ``Related investigative actions'' are follow-on actions that: (1)
Are related to the primary actions, and (2) further investigate the
nature of any condition found. Related investigative 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 747-53A2815, dated November 8, 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.
Costs of Compliance
We estimate that this proposed AD affects 11 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.................... 28 work-hours x $85 per $0 $2,380 per $26,180 per
hour = $2,380 per inspection cycle. inspection cycle
inspection cycle.
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We estimate the following costs to do any necessary repairs and
post-repair inspections 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 this repair:
On-condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
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Repair....................................... 13 work-hours x $85 per hour = $0 $1,105
$1,105.
Post-repair Inspection....................... 12 work-hours x $85 per hour = $0 $1,020
$1,020.
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For any repairs that would be necessary based on the results of the
post-repair inspection, we have not received definitive data that would
enable us to provide cost estimates for that on-condition action.
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-2013-0303; Directorate Identifier
2012-NM-220-AD.
(a) Comments Due Date
We must receive comments by May 28, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 747-400 and -400F
series airplanes, certificated in any category, as identified in
Boeing Alert Service Bulletin 747-53A2815, dated November 8, 2012.
[[Page 21856]]
(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 on airplanes prior to
line number 1308 in the forward and aft inner chords of the station
2598 bulkhead, and the bulkhead upper and lower webs. We are issuing
this AD to detect and correct cracks in the splice fitting, support
frame, floor support, forward and aft inner chords, and the bulkhead
upper and lower webs of the body station, which could adversely
affect the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) High Frequency Eddy Current (HFEC) and Low Frequency Eddy Current
(LFEC) Inspection
At the compliance time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2815, dated
November 8, 2012; except as provided by paragraph (h)(2) of this AD:
Do HFEC and LFEC inspections, as applicable, for cracks in the
splice fitting, support frame, floor support, forward and aft inner
chords, the bulkhead upper web on the upper left and right side of
the bulkhead, and the bulkhead lower web on the lower left side of
the bulkhead, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2815, dated November 8, 2012.
(1) If no cracking is found, repeat the applicable inspections
specified in paragraph (g) of this AD, thereafter at the applicable
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2815, dated November 8, 2012.
(2) If any cracking is found, do the actions specified in
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Before further flight, do the applicable repair, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2815, dated November 8, 2012; except as
provided by paragraph (h)(1) of this AD.
(ii) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2815, dated
November 8, 2012, do an HFEC and LFEC inspections for cracks in the
unrepaired structure, which includes splice fitting, support frame,
aft and forward inner chord, and the bulkhead upper web; and do an
HFEC inspection for cracks in the repaired structure, which is the
bulkhead upper web; in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2815, dated
November 8, 2012.
(A) If no cracking is found, repeat the applicable HFEC and LFEC
inspections specified in paragraph (g)(2)(ii) of this AD, thereafter
at the applicable time specified in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 747-53A2815, dated November 8,
2012.
(B) If any cracking is found, before further flight, repair
using a method approved in accordance with the procedures specified
in paragraph (i) of this AD.
(h) Exception to the Service Information
(1) If any crack is found during any inspection required by this
AD, and Boeing Alert Service Bulletin 747-53A2815, dated November 8,
2012, specifies to contact Boeing for appropriate action: Before
further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (i) of this
AD.
(2) Where Boeing Alert Service Bulletin 747-53A2815, dated
November 8, 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.
(i) 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.
(j) Related Information
(1) For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6428; 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, WA. For information on the availability of
this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on March 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-08610 Filed 4-11-13; 8:45 am]
BILLING CODE 4910-13-P