
[Federal Register Volume 78, Number 45 (Thursday, March 7, 2013)]
[Proposed Rules]
[Pages 14731-14734]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-05189]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0204; Directorate Identifier 2012-NM-229-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 747-400 and 747-400F series airplanes. 
This proposed AD was prompted by reports of cracking in the outboard 
flange of the longeron extension fittings, which attach to the wing-to-
body fairing support frame. This proposed AD would require repetitive 
inspections of the longeron extension fittings for cracking, and 
corrective actions if necessary. We are proposing this AD to detect and 
correct cracks in the longeron extension fittings, which can become 
large and adversely affect the structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by April 22, 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: Nathan.P.Weigand@faa.gov.

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-2013-0204; 
Directorate Identifier 2012-NM-229-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 cracks were found in the outboard flanges 
of the

[[Page 14732]]

longeron extension fittings installed on the left and right sides of 
the airplane. Longeron extension fittings are installed on the fuselage 
under the wing-to-body fairing and attach the overwing longeron to the 
fuselage. The outboard flange of the fitting attaches to the wing-to-
body fairing support frame web. Subsequent analysis by Boeing indicated 
that the cracks were caused by fatigue combined with preload stress 
from improper fit-up during assembly. A manufacturing process change 
that began at line number 1199 might have resulted in preloading the 
longeron extension fittings. We are proposing this AD to detect and 
correct cracks in the longeron extension fittings, which can become 
large and adversely affect the structural integrity of the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-53A2860, dated 
December 4, 2012. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2013-0204.

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 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.

Differences Between the Proposed AD and the Service Information

    This proposed AD includes airplanes that are not included in the 
effectivity of Boeing Alert Service Bulletin 747-53A2860, dated 
December 4, 2012. That service bulletin defines actions for airplanes 
having line numbers 1199 through 1419 inclusive. Boeing recently 
reported an event that involved a cracked longeron extension fitting on 
the airplane having line number 1101. Based on this event we are 
expanding the airplane applicability in this proposed AD from airplanes 
having line numbers 1199 through 1419 inclusive to airplanes having 
line numbers 1076 through 1419 inclusive. We have coordinated this 
difference with Boeing.
    Although Boeing Alert Service Bulletin 747-53A2860, dated December 
4, 2012, specifies that operators may contact the manufacturer for the 
disposition of certain repair conditions, 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 41 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                        Cost per
                 Action                          Labor cost            Parts cost        product                    Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
High frequency eddy current inspection   32 work-hours x $85 per                 $0          $2,720  $111,520, per inspection cycle.
 for cracking in longeron extension       hour = $2,720, per
 fittings.                                inspection cycle.
Option to do preventative modification   479 work-hours x $85 per                 0          40,715  $1,669,315.
 instead of repetitive inspections.       hour = $40,715.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    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 
this replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement................................  464 work-hours x $85 per hour =                  $0         $39,440
                                              $39,440.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions 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

[[Page 14733]]

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-2013-0204; Directorate Identifier 
2012-NM-229-AD.

(a) Comments Due Date

    We must receive comments by April 22, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-400 and 747-400F 
series airplanes, certificated in any category, line numbers 1076 
through 1419 inclusive.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracking in the outboard 
flange of the longeron extension fittings, which attach to the wing-
to-body fairing support frame. We are issuing this AD to detect and 
correct cracks in the longeron extension fittings, which can become 
large and adversely affect the structural integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection of Longeron Extension Fitting

    For all airplanes: Except as required by paragraphs (i)(1) and 
(i)(4) of this AD, at the time specified in table 1 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2860, 
dated December 4, 2012: Do a surface high frequency eddy current 
(HFEC) inspection of the left and right longeron extension fittings 
for cracking, and do all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2860, dated December 4, 2012, except as 
required by paragraphs (i)(2) and (i)(3) of this AD. Do all 
applicable corrective actions before further flight. If no cracking 
is found, repeat the inspection thereafter at the intervals 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2860, dated December 4, 2012, until a permanent 
repair, longeron extension fitting replacement, or preventative 
modification is done, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2860, dated 
December 4, 2012.

(h) Inspection of Temporary Repair and Corrective Actions

    For airplanes on which a temporary repair as specified in Boeing 
Alert Service Bulletin 747-53A2860 has been done: At the times 
specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2860, dated December 4, 2012, do a 
surface HFEC inspection of the temporary repair of the longeron 
extension fittings for cracking, and all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2860, dated December 4, 2012, 
except as required by paragraph (i)(3) of this AD. Do all applicable 
corrective actions before further flight.

(i) Exceptions to Service Bulletin Specifications

    The following exceptions apply to this AD.
    (1) Where Boeing Alert Service Bulletin 747-53A2860, dated 
December 4, 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.
    (2) Where Boeing Alert Service Bulletin 747-53A2860, dated 
December 4, 2012, specifies to contact Boeing for repair 
information: Before further flight, repair using a method approved 
in accordance with the procedures specified in paragraph (k) of this 
AD.
    (3) For airplanes not identified in Boeing Alert Service 
Bulletin 747-53A2860, dated December 4, 2012: These airplanes are in 
Group 1 for the purposes of this AD and are required to do the 
applicable actions specified in the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2860, dated December 4, 2012.
    (4) Where Boeing Alert Service Bulletin 747-53A2860, dated 
December 4, 2012, specifies ``all airplanes,'' this means all 
airplanes identified in paragraph (c) of this AD.

(j) Optional Terminating Action

    Doing the permanent repair, longeron extension fitting 
replacement, or preventative modification, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2860, dated December 4, 2012, terminates the repetitive 
inspection required by paragraph (g) of this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office, 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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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 Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 
98057-3356; phone: 425-917-6428; fax: 425-917-6590; email: 
Nathan.P.Weigand@faa.gov.
    (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-

[[Page 14734]]

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 February 25, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-05189 Filed 3-6-13; 8:45 am]
BILLING CODE 4910-13-P


