Document ID: FAA-2013-0303-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2013-04-12T04:00Z

[Federal Register Volume 78, Number 71 (Friday, April 12, 2013)]
[Proposed Rules]
[Pages 21854-21856]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-08610]

 ========================================================================
 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.
 
 ========================================================================
 

  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).

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

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: 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-2013-0303; 
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
----------------------------------------------------------------------------------------------------------------
Inspections....................  28 work-hours x $85 per              $0  $2,380 per          $26,180 per
                                  hour = $2,380 per                        inspection cycle.   inspection cycle
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

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: 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.

(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: 
Nathan.P.Weigand@faa.gov.
    (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