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[Federal Register Volume 78, Number 208 (Monday, October 28, 2013)]
[Rules and Regulations]
[Pages 64164-64167]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-24042]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0303; Directorate Identifier 2012-NM-220-AD; 
Amendment 39-17620; AD 2013-20-14]
RIN 2120-AA64

Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
the Boeing Company Model 747-400 and -400F series airplanes. 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 (STA) 2598 
bulkhead, and the bulkhead upper and lower webs. This AD requires, 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 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 STA 2598 bulkhead, 
which could adversely affect the structural integrity of the airplane.

DATES:DATES: This AD is effective December 2, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 2, 
2013.

ADDRESSES: 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.

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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

[[Page 64165]]

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
The NPRM published in the Federal Register on April 12, 2013 (78 FR 
21854). The NPRM proposed to require, as applicable, repetitive HFEC 
and 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 21854, April 12, 2013) and the FAA's response to each comment.

Request To Include the Lower Web in the Inspection of the Unrepaired 
Structure

    Boeing requested that we revise paragraph (g) of the NPRM (78 FR 
21854, April 12, 2013) to clarify that the inspection of the unrepaired 
structure includes the lower webs. Boeing stated that the inspections 
for the unrepaired structure include both the upper and lower bulkhead 
webs, but that paragraph (g)(2)(ii) of the NPRM (78 FR 21854, April 12, 
2013) specifies only the upper web.
    We agree with Boeing's comment. For appropriate service 
information, the NPRM (78 FR 21854, April 12, 2013) referred to Boeing 
Alert Service Bulletin 747-53A2815, dated November 8, 2012, which also 
describes procedures for inspecting the bulkhead lower web. We have 
clarified the inspection in paragraph (g)(2)(ii) of this AD by 
referring to Boeing Alert Service Bulletin 747-53A2815, dated November 
8, 2012, for specific inspection procedures and locations.

Request To Revise the Unsafe Condition

    Boeing requested that, for clarity, the unsafe condition be revised 
to more specifically identify the location of potential cracking (i.e., 
the body station 2598 bulkhead).
    We agree with Boeing's request. We have revised the unsafe 
condition in the SUMMARY and paragraph (e) of this final rule to 
clarify the location of the bulkhead.

Request To Clarify the Discussion Section

    Boeing requested clarification of the Discussion section in the 
NPRM (78 FR 21854, April 12, 2013). Boeing stated that the Discussion 
does not mention cracks found in the splice fitting and incorrectly 
refers to the ``cutout for the horizontal stabilizer rear spar.''
    We agree that the commenter's proposed clarification provides a 
more accurate description of the report of cracks. However, the 
Discussion section is not carried over into the final rule; therefore, 
no change to this final rule is necessary in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 21854, April 12, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 21854, April 12, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 11 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections.....................  28 work-hours x $85              $0   $2,380 per           $26,180 per
                                   per hour = $2,380                     inspection cycle.    inspection cycle.
                                   per 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 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,

[[Page 64166]]

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2013-20-14 The Boeing Company: Amendment 39-17620; Docket No. FAA-
2013-0303; Directorate Identifier 2012-NM-220-AD.

(a) Effective Date

    This AD is effective December 2, 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.

(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 
(STA) 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 STA 2598 bulkhead, 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) Inspections

    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 HFEC and LFEC inspections for cracks in the 
unrepaired structure, and do an HFEC inspection for cracks in the 
repaired structure; as specified in and 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) Exceptions 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 paragraph (j) 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

    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.

[[Page 64167]]

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 747-53A2815, dated November 8, 
2012.
    (ii) Reserved.
    (3) 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.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 19, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-24042 Filed 10-25-13; 8:45 am]
BILLING CODE 4910-13-P
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