[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
----------------------------------------------------------------------------------------------------------------
                                                                                       Cost per    Cost on U.S.
                  Action                            Labor cost           Parts cost    product       operators
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
                Action                            Labor cost             Parts cost       Cost per  product
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

    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