[Federal Register Volume 78, Number 69 (Wednesday, April 10, 2013)]
[Proposed Rules]
[Pages 21276-21279]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-08342]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0301; Directorate Identifier 2013-NM-025-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 767-200, -300, -300F, and -400ER
series airplanes. This proposed AD was prompted by reports of cracked
and corroded nuts on an outboard flap support rib. This proposed AD
would require, for certain airplanes, repetitive inspections of the cap
seal for damaged sealant on nuts common to certain outboard flap
support ribs, related investigative and corrective actions if
necessary, and replacement of all fasteners in the support ribs, which
terminates the repetitive inspections. For certain other airplanes,
this proposed AD would require repetitive inspections of the cap seal
for damaged sealant on nuts common to certain outboard flap support
ribs, related investigative and corrective actions if necessary, and if
necessary, a detailed inspection to determine the nut type installed in
the outboard flap support rib and corrective actions; for these
airplanes, this proposed AD provides optional replacement of all
fasteners in the support ribs, which would terminate the repetitive
inspections. We are proposing this AD to detect and correct cracked and
corroded nuts and bolts and the installation of incorrect nuts on
certain outboard flap support ribs, which could lead to additional nut
and bolt damage in the joint, and result in loss of an outboard flap,
and adversely affect continued safe flight and landing 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 Boeing 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: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6577; 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-2013-0301;
Directorate Identifier 2013-NM-025-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 two cracked and corroded nuts were found
on support rib number 2 of an outboard flap. It was determined that
incorrect nuts were installed on support rib numbers 2 and 7. The
correct nuts for this installation have part number (P/N) BACN10HR12
and a torque of 3,300 to 4,300 inch-pounds (in-lbs). The installed
incorrect nuts have P/N
[[Page 21277]]
NAS1804-12 and a torque of 2,400 to 3,500 in-lbs. The installed P/N
NAS1804-12 nuts might have been over-torqued. Over-torqued nuts are at
risk of fracture. Fractured nuts could create a breach in the cap seal
and allow moisture to contact the nuts, resulting in corrosion. Nut
fractures could lead to additional nut or bolt fractures within that
support rib, and these additional fractures could cause the joint to be
compromised. We are proposing this AD to detect and correct cracked and
corroded nuts and bolts and the installation of incorrect nuts on
certain outboard flap support ribs, which could lead to additional nut
and bolt damage in the joint, and result in loss of an outboard flap,
and adversely affect continued safe flight and landing of the airplane.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 767-57A0131, dated
October 30, 2012. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2013-0301.
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.
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 action, and (2) are actions that
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.
Costs of Compliance
We estimate that this proposed AD affects 440 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Detailed inspections..................... 1 work-hour x $85 per hour $0 $85 $37,400
= $85.
Replacement of all fasteners (Group 1 2 work-hours x $85 per hour 2,553 2,723 1,198,120
airplanes). = $170.
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We estimate the following costs to do any necessary related
investigative and corrective actions and detailed inspections for nut
type that would be required based on the results of the proposed
inspections. We have no way of determining the number of aircraft that
might need these actions.
On-Condition Costs
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Action Labor cost Parts cost Cost per product
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Related investigative and corrective Up to 3 work-hours x $85 per $2,553 Up to $2,808
actions and detailed inspection for hour = $255.
nut type.
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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:
[[Page 21278]]
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-2013-0301; Directorate Identifier
2013-NM-025-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 767-200, 767-300,
767-300F, and 767-400ER series airplanes; certificated in any
category; as identified in Boeing Alert Service Bulletin 767-
57A0131, dated October 30, 2012.
(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 cracked and corroded nuts on
an outboard flap support rib. We are issuing this AD to detect and
correct cracked and corroded nuts and bolts and the installation of
incorrect nuts on certain outboard flap support ribs, which could
lead to additional nut and bolt damage in the joint, and result in
loss of an outboard flap, and adversely affect continued safe flight
and landing of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) For Group 1 Airplanes: Repetitive Inspections of the Support Ribs,
Related Investigative and Corrective Actions, and Fastener Replacement
For Group 1 airplanes, as specified in Boeing Alert Service
Bulletin 767-57A0131, dated October 30, 2012: Except as required by
paragraph (j) of this AD, at the time specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
767-57A0131, dated October 30, 2012: Do a detailed inspection of the
cap seal for damaged sealant on the nuts common to outboard flap
support rib numbers 1, 2, 7, and 8, and do all applicable related
investigative and corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0131, dated October 30, 2012. Do all applicable related
investigative and corrective actions before further flight, except
as specified in paragraphs (g)(1)(ii) and (g)(2)(ii) of this AD.
(1) If, during any detailed inspection of the cap seal required
by paragraph (g) of this AD, no damaged sealant is found on any
support rib, do the actions specified in paragraphs (g)(1)(i) and
(g)(1)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that
support rib thereafter at the intervals specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
767-57A0131, dated October 30, 2012, until all fasteners are
replaced within that support rib as required by paragraph (g)(1)(ii)
of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 767-57A0131, dated October 30, 2012: Replace
all fasteners within the support rib in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0131, dated October 30, 2012.
(2) If, during any related investigative action required by
paragraph (g) of this AD, no cracking and no corrosion is found on
the nut, bolt, and washers of any support rib, do the actions
specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that
support rib thereafter at the intervals specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
767-57A0131, dated October 30, 2012, until all fasteners are
replaced within that support rib as required by paragraph (g)(2)(ii)
of this AD.
(ii) Except as required by paragraph (j) of this AD, at the time
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 767-57A0131, dated October 30, 2012: Replace
all fasteners within the support rib in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0131, dated October 30, 2012.
(h) For Group 2 and 3 Airplanes: Repetitive Inspections of the Support
Ribs, Related Investigative and Corrective Actions, and Fastener
Replacement
For Group 2 and 3 airplanes, as specified in Boeing Alert
Service Bulletin 767-57A0131, dated October 30, 2012: Except as
required by paragraph (j) of this AD, at the time specified in table
2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 767-57A0131, dated October 30, 2012: Do a detailed
inspection of the cap seal for damaged sealant on the nuts common to
outboard flap support rib numbers 1, 2, 7, and 8, and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-57A0131, dated October 30, 2012. Do all
applicable related investigative and corrective actions before
further flight.
(1) If, during any detailed inspection of the cap seal required
by paragraph (h) of this AD, no damaged sealant is found on any
support rib, do the actions specified in paragraphs (h)(1)(i) and
(h)(1)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that
support rib thereafter at the intervals specified in table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
767-57A0131, dated October 30, 2012, until the actions required by
paragraph (h)(1)(ii) of this AD are done or until all fasteners are
replaced within that support rib as specified in paragraph (i) of
this AD.
(ii) Except as required by paragraph (j) of this AD, at the time
specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 767-57A0131, dated October 30, 2012: Do a
detailed inspection to determine the nut type installed in the
outboard flap support rib and do all applicable corrective actions,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-57A0131, dated October 30, 2012. Do all
applicable corrective actions before further flight.
(2) If, during any related investigative action required by
paragraph (h) of this AD, no cracking and no corrosion is found on
the nut, bolt, and washers of any support rib, do the actions
specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Repeat the detailed inspection of the cap seal on that
support rib thereafter at the intervals specified in table 2 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
767-57A0131, dated October 30, 2012, until the actions required by
paragraph (h)(2)(ii) of this AD are done or until all fasteners are
replaced within that support rib as specified in paragraph (i) of
this AD.
(ii) Except as required by paragraph (j) of this AD, at the time
specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 767-57A0131, dated October 30, 2012: Do a
detailed inspection to determine the nut type installed in the
outboard flap support rib and do all applicable corrective actions,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 767-57A0131, dated October 30, 2012. Do all
applicable corrective actions before further flight.
(i) Replacement of all Fasteners Within Outboard Flap Support Ribs 1,
2, 7, and 8
Replacing all fasteners within outboard flap support rib number
1, 2, 7, or 8, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 767-57A0131, dated October 30, 2012,
terminates the inspections required by paragraphs (g) and (h) of
this AD for that support rib only.
(j) Exception to Service Information
Where Boeing Alert Service Bulletin 767-57A0131, dated October
30, 2012, specifies a compliance time relative to the issue date of
that 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.
[[Page 21279]]
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 Berhane Alazar,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: 425-917-6577; fax: 425-917-6590; email:
[email protected].
(2) For Boeing 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 also 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 March 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-08342 Filed 4-9-13; 8:45 am]
BILLING CODE 4910-13-P