AD 2010-03-05

[Federal Register Volume 75, Number 23 (Thursday, February 4, 2010)]
[Rules and Regulations]
[Pages 5692-5695]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2010-1690]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0608; Directorate Identifier 2008-NM-215-AD; 
Amendment 39-16188; AD 2010-03-05]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 747-200C and -
200F Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Model 747-200C and -200F series airplanes. This AD requires a high 
frequency eddy current (HFEC) inspection for cracks of certain fastener 
holes, and corrective action if necessary. This AD also requires 
repetitive replacements of the upper chords, straps (or angles), and 
radius fillers of certain upper deck floor beams, and, for any 
replacement that is done, detailed and open-hole HFEC inspections for 
cracks of the modified upper deck floor beams, and corrective actions 
if necessary. This AD results from a report from the manufacturer that 
the accomplishment of certain existing inspections, repairs, and 
modifications is not adequate to ensure the structural integrity of the 
affected 7075 series aluminum alloy upper deck floor beam upper chords 
on airplanes that have exceeded certain thresholds. We are issuing this 
AD to prevent cracking of the upper chords and straps (or angles) of 
the floor beams, which could lead to failure of the floor beams and 
consequent loss of controllability, rapid decompression, and loss of 
structural integrity of the airplane.

DATES: This AD is effective March 11, 2010.
    The Director of the Federal Register approved the incorporation by 
reference

[[Page 5693]]

of a certain publication listed in the AD as of March 11, 2010.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail <a href="/cdn-cgi/l/email-protection#2a474f0448454f4945476a48454f43444d04494547"><span class="__cf_email__" data-cfemail="7e131b501c111b1d11133e1c111b171019501d1113">[email&#160;protected]</span></a>; 
Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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 (telephone 800-647-5527) is the 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: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness directive (AD) that would apply to 
all Model 747-200C and -200F series airplanes. That NPRM was published 
in the Federal Register on July 6, 2009 (74 FR 31894). That NPRM 
proposed to require a high frequency eddy current inspection for cracks 
of certain fastener holes, and corrective action if necessary. That 
NPRM also proposed to require repetitive replacements of the upper 
chords, straps (or angles), and radius fillers of certain upper deck 
floor beams, and, for any replacement that is done, detailed and open-
hole HFEC inspections for cracks of the modified upper deck floor 
beams, and corrective actions if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received from the commenters.

Support for the NPRM

    One commenter, Boeing, agrees with the contents of the NPRM.

Request To Clarify Compliance Time of Modification

    One commenter, Northwest Airlines (NWA), requests that we clarify 
whether the modification that is mandated by paragraph (g) of AD 2005-
07-21, Amendment 39-14046 (70 FR 18277, April 11, 2005), is required 
during the accomplishment of the initial 15,000-flight-cycle post-upper 
chord replacement inspection proposed by the NPRM. NWA notes that the 
NPRM would require replacing the upper deck floor beam upper chords 
before the accumulation of 21,000 total flight cycles, or within 1,500 
flight cycles after the effective date of the AD, whichever is later. 
NWA also states that the proposed rule would mandate inspecting the 
upper deck floor beams within 15,000 flight cycles after replacement of 
the upper chords. NWA notes that the inspections are to be completed in 
accordance with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-53A2429, Revision 2, dated October 16, 2008; and Boeing 
Alert Service Bulletin 747-53A2439, Revision 2, dated July 17, 2008. 
NWA notes that inspections per Boeing Alert Service Bulletins 747-
53A2429 and 747-53A2439 were previously mandated. NWA points out that 
the Manager of the Seattle Aircraft Certification Office has previously 
approved the accomplishment of the applicable inspection, repair, and 
modification procedures contained in Boeing Alert Service Bulletin 747-
53A2696, dated October 16, 2008, as an alternative method of compliance 
(AMOC) for paragraphs (f) and (g) of AD 2006-08-02, Amendment 39-14556 
(71 FR 18618, April 12, 2006), and the inspection, repair, and 
modification requirements of paragraphs (a), (b), (c), (e), (g)(1), 
(h)(2), (i), (j), (k), and (l) of AD 2005-07-21.
    We agree to provide clarification of the post-upper chord 
replacement actions. Paragraph (h) of this final rule requires detailed 
and HFEC inspections for cracks of the modified upper deck floor beams, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2696, dated October 16, 2008, within 15,000 
flight cycles after the upper chord replacement, or within 1,500 flight 
cycles after the effective date of this AD, whichever occurs later. In 
addition, paragraph (h) of this final rule requires a repeat 
accomplishment of the upper chord replacement within 6,000 flight 
cycles after doing the initial post-upper chord replacement 
inspections. Boeing Alert Service Bulletin 747-53A2696 in turn refers 
to Boeing Alert Service Bulletins 747-53A2429, Revision 2; and 747-
53A2439, Revision 2; for inspection procedures only. Therefore, the 
modification in accordance with Boeing Alert Service Bulletin 747-
53A2429, dated March 22, 2001, as mandated by paragraph (g) of AD 2005-
07-21, is not required by this final rule. Operators should note that 
accomplishment of the actions per this AD has been approved as an AMOC 
to the corresponding requirements of AD 2005-07-21 and AD 2006-08-02 as 
described above. We have not changed the final rule in regard to this 
issue.

Explanation of Changes Made to This AD

    We have revised this AD to identify the legal name of the 
manufacturer as published in the most recent type certificate data 
sheet for the affected airplane models.
    Boeing Commercial Airplanes has received an Organization 
Designation Authorization (ODA), which replaces their previous 
designation as a Delegation Option Authorization (DOA) holder. We have 
revised paragraph (j)(3) of this AD to delegate the authority to 
approve an alternative method of compliance for any repair required by 
this AD to the Boeing Commercial Airplanes ODA.

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 changes described previously. We 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 25 airplanes of U.S. registry. The 
following table provides the estimated costs for U.S. operators to 
comply with this AD.

[[Page 5694]]



                                             Table--Estimated Costs
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                                                                              Number of
                      Average                                                   U.S.-
    Work hours       labor rate         Parts           Cost per product      registered        Fleet cost
                      per hour                                                airplanes
----------------------------------------------------------------------------------------------------------------
663...............          $80  None..............  $53,040 per inspection/          25  $1,326,000 per
                                                      replacement cycle.                   inspection/
                                                                                           replacement cycle.
----------------------------------------------------------------------------------------------------------------

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), and
    (3) 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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 AD:

2010-03-05 The Boeing Company: Amendment 39-16188. Docket No. FAA-
2009-0608; Directorate Identifier 2008-NM-215-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective March 11, 
2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all The Boeing Company Model 747-200C and 
-200F series airplanes, certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from a report from the manufacturer that the 
accomplishment of certain existing inspections, repairs, and 
modifications is not adequate to ensure the structural integrity of 
the affected 7075 series aluminum alloy upper deck floor beam upper 
chords on airplanes that have exceeded certain thresholds. We are 
issuing this AD to prevent cracking of the upper chords and straps 
(or angles) of the floor beams, which could lead to failure of the 
floor beams and consequent loss of controllability, rapid 
decompression, and loss of structural integrity of the airplane.

Compliance

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

Initial Inspection and Replacement

    (g) Before the accumulation of 21,000 total flight cycles, or 
within 1,500 flight cycles after the effective date of this AD, 
whichever occurs later: Do an open-hole high frequency eddy current 
(HFEC) inspection of all the fastener holes accessed for upper chord 
removal for cracks, and replace the upper chords, straps (or 
angles), and radius fillers of the upper deck floor beams, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2696, dated October 16, 2008.

Repetitive Replacements and Post-Replacement Inspections

    (h) Within 15,000 flight cycles after doing the replacement 
required by paragraph (g) of this AD, or within 1,500 flight cycles 
after the effective date of this AD, whichever occurs later: Do 
detailed and HFEC inspections for cracks of the modified upper deck 
floor beams, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2696, dated October 16, 2008. 
Within 6,000 flight cycles after doing the detailed and HFEC 
inspections, repeat the replacement specified in paragraph (g) of 
this AD. Repeat the post-replacement inspections and replacement at 
the applicable times specified in paragraph 1.E. of Boeing Alert 
Service Bulletin 747-53A2696, dated October 16, 2008.

Repair of Cracks

    (i) If any crack is found during any inspection required by this 
AD: Before further flight, repair the crack using a method approved 
in accordance with the procedures specified in paragraph (j) of this 
AD.

Alternative Methods of Compliance (AMOCs)

    (j)(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. Send information to 
ATTN: Ivan Li, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6437; fax (425) 917-6590. Or, e-mail information to <a href="/cdn-cgi/l/email-protection#bb8296faf5f696e8dedacfcfd7de96faf8f496faf6f4f896e9decacedec8cfc8fbdddada95dcd4cd"><span class="__cf_email__" data-cfemail="d2ebff939c9fff81b7b3a6a6beb7ff93919dff939f9d91ff80b7a3a7b7a1a6a192b4b3b3fcb5bda4">[email&#160;protected]</span></a>.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (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

[[Page 5695]]

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.

Material Incorporated by Reference

    (k) You must use Boeing Alert Service Bulletin 747-53A2696, 
dated October 16, 2008, as applicable, to do the actions required by 
this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
<a href="/cdn-cgi/l/email-protection#721f175c101d17111d1f32101d171b1c155c111d1f"><span class="__cf_email__" data-cfemail="f29f97dc909d97919d9fb2909d979b9c95dc919d9f">[email&#160;protected]</span></a>; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (3) You may review copies of the 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 or 425-227-1152.
    (4) You may also review copies of the 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: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on January 21, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-1690 Filed 2-3-10; 8:45 am]
BILLING CODE 4910-13-P