[Federal Register Volume 79, Number 248 (Monday, December 29, 2014)]
[Proposed Rules]
[Pages 77970-77972]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-30271]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0929; Directorate Identifier 2014-NM-118-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 767 airplanes. This proposed AD was
prompted by reports that six fasteners may not have been installed in
the left and right stringer 37 (S-37) between body station (BS) 428 and
431 lap splices on certain airplanes. This proposed AD would require a
general visual inspection of S-37 lap splices for missing fasteners;
and all applicable related investigative and corrective actions. We are
proposing this AD to detect and correct missing fasteners, which could
result in cracks in the fuselage skin that could adversely affect the
structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by February 12,
2015.
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 view this 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 by searching for and locating Docket No. FAA-2014-
0929; 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: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6590; 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-2014-0929;
Directorate Identifier 2014-NM-118-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 that six fasteners may not have been installed
in the left and right stringer 37 (S-37) between BS 428 and 431 lap
splices on certain airplanes during production. This condition, if not
corrected, could result in cracks in the fuselage skin that could
adversely affect the structural integrity of the airplane.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 767-53A0251, dated August
7, 2013. For information on the procedures and compliance times, see
this service information at http://www.regulations.gov by searching for
and locating Docket No. FAA-2014-0929.
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 these same type
designs.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the Service
Information.''
The phrase ``related investigative actions'' is used in this
proposed AD. ``Related investigative actions'' are follow-on actions
that (1) are related to the primary action, and (2) further investigate
the nature of any condition found. Related investigative actions in an
AD could include, for example, inspections.
The phrase ``corrective actions'' is 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.
Explanation of ``RC'' Steps in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directives Implementation Aviation Rulemaking Committee,
to enhance the AD system. One enhancement was a new process for
annotating which steps in the service information are required for
compliance with an AD. Differentiating these steps from other tasks in
the service information is
[[Page 77971]]
expected to improve an owner's/operator's understanding of crucial AD
requirements and help provide consistent judgment in AD compliance. The
actions specified in the service information described previously
include steps that are labeled as RC (required for compliance) because
these steps have a direct effect on detecting, preventing, resolving,
or eliminating an identified unsafe condition.
As noted in the specified service information, steps labeled as RC
must be done to comply with the proposed AD. However, steps that are
not labeled as RC are recommended. Those steps that are not labeled as
RC may be deviated from, done as part of other actions, or done using
accepted methods different from those identified in the service
information without obtaining approval of an alternative method of
compliance (AMOC), provided the steps labeled as RC can be done and the
airplane can be put back in a serviceable condition. Any substitutions
or changes to steps labeled as RC will require approval of an AMOC.
Differences Between This Proposed AD and the Service Information
Boeing Alert Service Bulletin 767-53A0251, dated August 7, 2013,
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 23 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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General visual inspection........... 1 work-hour x $85 per $0 $85 $1,955
hour = $85.
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We estimate the following costs to do any necessary inspections/
installations 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 inspections/installations:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Detailed and high frequency eddy current 13 work-hours x $85 per hour = $0 $1,105
inspections and fastener installation. $1,105.
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We have received no definitive data that would enable us to provide
cost estimates for the repairs specified in this proposed AD.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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. Amend Sec. 39.13 by adding the following new airworthiness
directive (AD):
[[Page 77972]]
The Boeing Company: Docket No. FAA-2014-0929; Directorate Identifier
2014-NM-118-AD.
(a) Comments Due Date
We must receive comments by February 12, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 767-53A0251, dated
August 7, 2013.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports that six fasteners may not have
been installed in the left and right stringer 37 (S-37) between body
station 428 and 431 lap splices on certain airplanes. We are issuing
this AD to detect and correct missing fasteners, which could result
in cracks in the fuselage skin that could adversely affect the
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections, Related Investigative Actions, and Corrective Actions
Except as provided by paragraph (h)(2) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 767-53A0251, dated August 7, 2013: Do
an external general visual inspection of the S-37 lap splice for
missing fasteners, and do all applicable related investigative and
corrective actions; in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 767-53A0251, dated
August 7, 2013, except as provided by paragraph (h)(1) of this AD.
Do all applicable related investigative and corrective actions
before further flight.
(h) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 767-53A0251, dated
August 7, 2013, specifies to contact Boeing for repair instructions:
Before further flight, do the repair using an FAA-approved method.
(2) Where Paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 767-53A0251, dated August 7, 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.
(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 paragraph (j)(1) 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.
(4) Except as required by paragraph (h)(1) of this AD: If the
service information contains steps that are labeled as RC, those
steps must be done to comply with this AD; any steps that are not
labeled as RC are recommended. Those steps that are not labeled as
RC may be deviated from, done as part of other actions, or done
using accepted methods different from those identified in the
specified service information without obtaining approval of an AMOC,
provided the steps labeled as RC can be done and the airplane can be
put back in a serviceable condition. Any substitutions or changes to
steps labeled as RC require approval of an AMOC.
(j) Related Information
(1) For more information about this AD, contact Berhane Alazar,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6590; 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 20-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this 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 December 17, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-30271 Filed 12-24-14; 8:45 am]
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