```

[Federal Register Volume 77, Number 225 (Wednesday, November 21, 2012)]
[Rules and Regulations]
[Pages 69739-69742]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-27637]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0498; Directorate Identifier 2011-NM-212-AD; 
Amendment 39-17238; AD 2012-22-02]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 747-400, -400D, and -400F series airplanes. 
This AD was prompted by reports of crown frame web cracking at left 
buttock line (LBL) 15.0, station (STA) 320. This AD requires measuring 
the web at STA 320 and, depending on findings, various inspections for 
cracks and missing fasteners, web and fastener replacement, and related 
investigative and corrective actions if necessary. We are issuing this 
AD to prevent complete fracture of the crown frame assembly, and 
consequent damage to the skin and in-flight decompression of the 
airplane.

DATES: This AD is effective December 26, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 26, 
2012.

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

[[Page 69740]]

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.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: Bill.Ashforth@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. 
That NPRM published in the Federal Register on June 12, 2012 (77 FR 
34881). That NPRM proposed to require measuring the web at STA 320 and, 
depending on findings, various inspections for cracks and missing 
fasteners, web and fastener replacement, and related investigative and 
corrective actions if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 34881, June 12, 2012), and the FAA's response to each comment.

Support for the NPRM (77 FR 34881, June 12, 2012)

    Mr. Caleb Berken stated that the fact that cracks have been seen in 
five of these airplanes is a little unnerving, but when it is 
considered that there are only 29 airplanes of this particular series 
(Model 747-400, -400D, and -400F series airplanes) currently in 
operation within the United States, these statistics become quite 
alarming. The commenter stated that he would like to put forth his full 
support for this proposed rule (77 FR 34881, June 12, 2012) to increase 
inspection and replacement of compromised parts that have developed 
within the crown frame web.

Request To Provide Credit for Prior Actions

    Boeing requested that we allow credit for work done prior to the 
effective date of the NPRM (77 FR 34881, June 12, 2012) using Boeing 
Service Bulletin 747-53A2784, dated August 27, 2009. Boeing stated that 
Boeing Service Bulletin 747-53A2784, Revision 1, dated September 14, 
2011 (which is the service information referenced in the NPRM (77 FR 
34881, June 12, 2012)), states that ``[n]o more work is necessary on 
airplanes changed in accordance with the original issue of this service 
bulletin.'' Boeing stated that the inspections and corrective actions 
described in Boeing Service Bulletin 747-53A2784, dated August 27, 
2009; and Revision 1, dated September 14, 2011; are structurally 
equivalent.
    We agree to add credit for prior actions because no more work is 
necessary on airplanes changed in accordance with Boeing Service 
Bulletin 747-53A2784, dated August 27, 2009. We have added new 
paragraph (l) to this AD to provide credit for actions required by 
paragraphs (g) through (j) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Service Bulletin 747-
53A2784, dated August 27, 2009. We have re-identified subsequent 
paragraphs accordingly.

Request To Allow Deviation Authority

    Boeing requested that paragraph (1)(3) of the NPRM (77 FR 34881, 
June 12, 2012) be revised to allow the Boeing Commercial Airplanes 
Organization Designation Authorization (ODA) to approve alternative 
methods of compliance (AMOCs) for both repairs and deviations to the 
modification that are described in either Boeing Service Bulletin 747-
53A2784, dated August 27, 2009; or Boeing Service Bulletin 747-53A2784, 
Revision 1, dated September 14, 2011. Boeing requested that we clarify 
that an AMOC can be approved for both repairs and deviations to the 
modification, and that the modification described in Boeing Service 
Bulletin 747-53A2784, dated August 27, 2009, satisfies the requirements 
of the modification described in Boeing Service Bulletin 747-53A2784 
Revision 1, dated September 14, 2011.
    We partially agree. The Boeing ODA is not currently authorized to 
provide AMOC approval of deviations that occur when doing the 
modification. However, once the AD is issued, we might delegate 
approval authority to certain authorized representatives of the Boeing 
ODA to approve AMOCs for deviations during this modification. We have 
not changed the AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the change described previously--and minor editorial 
changes. We have determined that these minor changes:
     [Agr]re consistent with the intent that was proposed in 
the NPRM (77 FR 34881, June 12, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 34881, June 12, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

 Costs of Compliance

    We estimate that this AD affects 29 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
              Action                        Labor cost                  Parts cost            Cost per product            Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Measurement.......................  1 work-hour x $85 per hour  $0........................  $85.................  $2,465.
                                     = $85.
Inspection and web replacement....  208 work-hours x $85 per    Up to $21,887.............  Up to $39,567.......  Up to $1,147,443.
                                     hour = $17,680.
Post-replacement inspection.......  135 work-hours x $85 per    $0........................  $11,475 per           $332,775 per inspection cycle.
                                     hour = $11,475 per                                      inspection cycle.
                                     inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

[[Page 69741]]

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition crack repairs specified in this AD.

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

    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):

2012-22-02 The Boeing Company: Amendment 39-17238; Docket No. FAA-
2012-0498; Directorate Identifier 2011-NM-212-AD.

(a) Effective Date

    This AD is effective December 26, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-400, -400D, and 
-400F series airplanes, certificated in any category, as specified 
in Boeing Service Bulletin 747-53A2784, Revision 1, dated September 
14, 2011.

(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 crown frame web cracking at 
left buttock line (LBL) 15.0, station (STA) 320. We are issuing this 
AD to prevent complete fracture of the crown frame assembly, and 
consequent damage to the skin and in-flight decompression of the 
airplane.

(f) Compliance

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

(g) Crown Frame Web Measurement

    At the applicable compliance time specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2784, Revision 1, 
dated September 14, 2011, except as specified in paragraph (k)(1) of 
this AD, measure the thickness of the crown frame web at STA 320, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2784, Revision 1, dated September 14, 2011. For 
airplanes with a 0.136- to 0.145-inch-thick web, no further action 
is required by this AD.

(h) Detailed Inspection and Web Replacement With No Web Repair Doubler

    For airplanes on which the web measures 0.078- to 0.083-inch-
thick during the measurement required by paragraph (g) of this AD, 
and on which a repair doubler is not installed: At the applicable 
time specified in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 747-53A2784, Revision 1, dated September 14, 2011, except 
as specified in paragraph (k)(1) of this AD, do a detailed 
inspection for cracks and a general visual inspection for missing 
fasteners of the crown frame web at STA 320; and do all applicable 
related investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2784, 
Revision 1, dated September 14, 2011, except as specified in 
paragraph (k)(2) of this AD. Do the applicable related investigative 
and corrective actions at the applicable times specified in 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2784, Revision 1, dated September 14, 2011, except as specified 
in paragraph (k)(1) of this AD. Boeing Service Bulletin 747-53A2784, 
Revision 1, dated September 14, 2011, provides options for 
accomplishing the actions that are required for airplanes on which 
no cracking is found in the crown frame web.

(i) Detailed Inspection and Web Replacement With Web Repair Doubler

    For airplanes on which the web measures 0.078- to 0.083-inch-
thick during the measurement required by paragraph (g) of this AD, 
and on which a repair doubler is installed: At the applicable 
compliance time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 747-53A2784, Revision 1, dated September 14, 
2011, except as specified in paragraph (k)(1) of this AD, do the 
actions specified in paragraphs (i)(1) and (i)(2) of this AD, and do 
all applicable corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 747-53A2784, 
Revision 1, dated September 14, 2011, except as specified in 
paragraph (k)(2) of this AD. Do all applicable corrective actions 
before further flight.
    (1) Replace the web with a new web and do all applicable related 
investigative actions.
    (2) Do a detailed inspection for cracks in the upper or lower 
chord of the crown frame web at STA 320.

(j) Post-Replacement Repetitive Inspections of Replaced Web

    Following any web replacement required by this AD, at the times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 747-53A2784, Revision 1, dated September 14, 2011: Do a 
detailed inspection for cracks of the web, upper chord, lower chord, 
and lower chord splice, and do all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 747-53A2784, Revision 1, dated September 14, 2011, except 
as specified in paragraph (k)(2) of this AD. Do all applicable 
corrective actions before further flight. If no crack is found, 
repeat the inspection thereafter at the intervals specified in 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2784, Revision 1, dated September 14, 2011. Accomplishment of the 
inspections required by AD 2009-19-05, Amendment 39-16022 (74 FR 
48138, September 22, 2009), terminates the requirements of this 
paragraph.

(k) Exceptions to the Service Information

    (1) Where Boeing Service Bulletin 747-53A2784, Revision 1, dated 
September 14,

[[Page 69742]]

2011, specifies a compliance time ``after the original issue date of 
the service bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.
    (2) Where Boeing Service Bulletin 747-53A2784, Revision 1, dated 
September 14, 2011, specifies to contact Boeing for appropriate 
action, accomplish applicable actions before further flight using a 
method approved in accordance with the procedures specified in 
paragraph (m) of this AD.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g) through (j) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Service 
Bulletin 747-53A2784, dated August 27, 2009.

(m) 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.

(n) Related Information

    For more information about this AD, Bill Ashforth, Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6432; fax: 425-917-6590; email: 
Bill.Ashforth@faa.gov.

(o) 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 Service Bulletin 747-53A2784, Revision 1, dated 
September 14, 2011.
    (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 October 19, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-27637 Filed 11-20-12; 8:45 am]
BILLING CODE 4910-13-P
```