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[Federal Register Volume 79, Number 90 (Friday, May 9, 2014)]
[Rules and Regulations]
[Pages 26606-26608]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-09832]

[[Page 26606]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0686; Directorate Identifier 2013-NM-006-AD; 
Amendment 39-17843; AD 2014-09-08]
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 superseding Airworthiness Directive (AD) 2007-16-19, 
which applied to certain The Boeing Company Model 747-200B, 747-300, 
and 747-400 series airplanes. AD 2007-16-19 required repetitive 
detailed inspections for cracking of the aft tension tie channels from 
body station (BS) 1120 to BS 1220 and from BS 880 to BS 1100, and 
corrective actions if necessary. AD 2007-16-19 also provided optional 
terminating action. This new AD retains the existing requirements, 
limits the area of the detailed inspection, adds repetitive surface 
high-frequency eddy current inspections, and mandates the previously 
optional terminating action. This AD was prompted by an analysis that 
indicated the need to mandate the previously optional modification. We 
are issuing this AD to prevent fatigue cracking of the tension ties, 
which could result in reduced structural integrity of the airplane and 
rapid depressurization of the airplane.

DATES: This AD is effective June 13, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 13, 
2014
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
September 12, 2012 (77 FR 47267, August 8, 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 view this 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 by searching for and locating Docket No. FAA-2013-
0686; 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 Docket 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 supersede AD 2007-16-19, Amendment 39-15158 (72 FR 45151, 
August 13, 2007). AD 2007-16-19 applied to certain The Boeing Company 
Model 747-200B, 747-300, and 747-400 series airplanes. The NPRM 
published in the Federal Register on August 12, 2013 (78 FR 48835). The 
NPRM was prompted by an analysis that indicated the need to mandate the 
previously optional modification. The NPRM proposed to continue to 
require repetitive detailed inspections for cracking of the aft tension 
tie channels from body station (BS) 1120 to BS 1220 and from BS 880 to 
BS 1100, and corrective actions if necessary. The NPRM also proposed to 
provide optional terminating action for the repetitive detailed 
inspections at BS 1120 to 1220. The NPRM also proposed to limit the 
area of the detailed inspection, add repetitive surface high-frequency 
eddy current inspections, and mandate the previously optional 
terminating action for BS 880 to 1100. We are issuing this AD to 
prevent fatigue cracking of the tension ties, which could result in 
reduced structural integrity of the airplane and rapid depressurization 
of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 48835, August 12, 2013) and the FAA's response to each comment.

Request To Change Service Information Reference

    Paragraph (h) of the NPRM (78 FR 48835, August 12, 2013) specified 
a modification and related investigative and corrective actions, in 
accordance with Boeing Alert Service Bulletin 747-53A2610, Revision 1, 
dated December 4, 2012. Paragraph (h) of the NPRM included the 
following provision:

    Modification of a tension tie at STA 1120 to 1220, as required 
by paragraph (p) of AD 2012-15-13 . . ., is acceptable for 
compliance with the requirements of paragraph (h) of this AD for 
that tension tie location only.

Boeing requested that we revise that sentence to specify that the 
modification is terminating action if done in accordance with Boeing 
Service Bulletin 747-53A2559, Revision 1, dated August 4, 2011--instead 
of AD 2012-15-13, Amendment 39-17142 (77 FR 47267, August 8, 2012), 
which could be superseded in the future.
    We agree with the request, for the reasons provided by the 
commenter, and have revised this terminating action provision 
accordingly in this final rule. We have also revised paragraph (b) of 
this final rule to remove the reference to AD 2012-15-13, Amendment 39-
17142 (77 FR 47267, August 8, 2012). In addition, we have moved the 
terminating action provisions from paragraph (h) of this final rule to 
a new paragraph (i) in this final rule, and redesignated subsequent 
paragraphs accordingly.

Requests for More Specific Exception References

    Boeing requested that we revise paragraphs (g) and (h) of the NPRM 
(78 FR 48835, August 12, 2013) to change the reference to the 
compliance-time exception paragraph, which the NPRM identified as 
paragraph ``(i).'' Boeing requested that we more specifically identify 
this exception as paragraph ``(i)(2)'' of the NPRM.
    We agree, and have revised paragraphs (g) and (h) accordingly in 
this final rule--except that paragraph (i)(2) of the NPRM (78 FR 48835, 
August 12, 2013) has been redesignated as paragraph (j)(2) in this 
final rule.

Additional Changes to NPRM (78 FR 48835, August 12, 2013)

    Paragraph (h) of the NPRM (78 FR 48835, August 12, 2013) provided 
terminating action for all tension tie locations (BS 880 to 1220). We 
have revised paragraph (h) in this final rule to require terminating 
action for BS 880

[[Page 26607]]

to 1100 only, and to move the (optional) terminating action for BS 1120 
to 1220 to new paragraph (i) in this final rule. We redesignated 
subsequent paragraphs accordingly.
    We have further revised paragraph (h) of the NPRM (78 FR 48835, 
August 12, 2013), now paragraphs (h) and (i) in this final rule, to 
clarify that modification of a tension tie is acceptable for compliance 
with the requirements of paragraph (g) of this AD for the affected 
tension tie location only.
    Paragraph (h) of the NPRM (78 FR 48835, August 12, 2013) 
incorrectly stated that it terminated paragraph (h) of the AD. 
Paragraphs (h) and (i) in this final rule instead identify paragraph 
(g) of the AD as the terminated action.

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 48835, August 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 48835, August 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 1 airplane 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
----------------------------------------------------------------------------------------------------------------
Retained detailed inspection       4 work-hours x $85               $0  $340 per inspection  $340 per inspection
 (retained actions).                per hour = $340                      cycle.               cycle.
                                    per inspection
                                    cycle.
New surface high-frequency eddy    4 work-hours x $85                0  $340 per inspection  $340 per inspection
 current inspection.                per hour = $340                      cycle.               cycle.
                                    per inspection
                                    cycle.
New modification.................  64 work-hours x $85          14,948  $20,388............  $20,388
                                    per hour = $5,440.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
work-hour estimates for repair of cracks found in a bolt hole during 
the detailed inspection specified in this AD. The cost for parts 
(oversized fastener kit) for this condition is $2,292.

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 have determined that 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 removing Airworthiness Directive (AD) 
2007-16-19, Amendment 39-15158 (72 FR 45151, August 13, 2007), and 
adding the following new AD:

2014-09-08 The Boeing Company: Amendment 39-17843; Docket No. FAA-
2013-0686; Directorate Identifier 2013-NM-006-AD.

(a) Effective Date

    This AD is effective June 13, 2014.

(b) Affected ADs

    This AD supersedes AD 2007-16-19, Amendment 39-15158 (72 FR 
45151, August 13, 2007).

(c) Applicability

    This AD applies to The Boeing Company Model 747-200B, 747-300, 
and 747-400 series airplanes, certificated in any category, as 
identified in Boeing Alert Service Bulletin 747-53A2610, Revision 1, 
dated December 4, 2012.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the tension ties are subject to 
widespread fatigue damage (WFD). We are issuing this AD to prevent 
fatigue cracking of the tension ties, which could result in reduced 
structural integrity of the airplane and rapid depressurization of 
the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2610, 
Revision 1, dated December 4, 2012, except as specified in paragraph 
(j)(2) of this AD: Do

[[Page 26608]]

detailed and surface high-frequency eddy current inspections for 
cracks in the tension ties at body station (BS) 880 to 1100, 1120, 
1160, 1200, and 1220, and do all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2610, Revision 1, dated December 4, 2012, 
except as required by paragraph (j)(3) of this AD. Do all applicable 
corrective actions before further flight. Repeat the inspections 
thereafter at the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2610, 
Revision 1, dated December 4, 2012, until the tension ties have been 
modified as required by paragraph (h) of this AD or as specified in 
paragraph (i) of this AD. Repair or modification of a tension tie at 
any location in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2610, Revision 
1, dated December 4, 2012, terminates the repetitive inspection 
requirements of this AD for that tension tie location only.

(h) Tension Tie Modification: BS 880 to 1100

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2610, 
Revision 1, dated December 4, 2012, except as specified in paragraph 
(j)(2) of this AD: Modify the tension ties from BS 880 to 1100, and 
do all applicable related investigative and corrective actions, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2610, Revision 1, dated December 4, 
2012, except as required by paragraph (j)(3) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight. Modification as required by this paragraph 
terminates the repetitive inspection requirements of paragraph (g) 
of this AD for the affected tension tie location(s) only.

(i) Optional Terminating Action: BS 1120 to 1220

    Modification of a tension tie at BS 1120 to 1220 in accordance 
with Boeing Service Bulletin 747-53A2559, Revision 1, dated August 
4, 2011, except as required by paragraph (j)(4) of this AD, 
terminates the requirements of paragraph (g) of this AD for that 
tension tie location only. Paragraph (p) of AD 2012-15-13, Amendment 
39-17142 (77 FR 47267, August 8, 2012), mandates the accomplishment 
of the modification and associated actions specified in Boeing 
Service Bulletin 747-53A2559, Revision 1, dated August 4, 2011.

(j) Service Information Clarification and Exceptions

    (1) Paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2610, Revision 1, dated December 4, 2012, specifies 
certain compliance times ``after August 28, 2007.'' August 28, 2007, 
is the effective date of AD 2007-16-19, Amendment 39-15158 (72 FR 
45151, August 13, 2007).
    (2) Where Boeing Alert Service Bulletin 747-53A2610, Revision 1, 
dated December 4, 2012, specifies a compliance time ``after the 
Revision 1 date of this service bulletin,'' this AD requires 
compliance within the specified time after the effective date of 
this AD.
    (3) Where Boeing Alert Service Bulletin 747-53A2610, Revision 1, 
dated December 4, 2012, specifies to contact Boeing for certain 
repair instructions: Repair before further flight using a method 
approved in accordance with the procedures specified in paragraph 
(l) of this AD.
    (4) Where Boeing Service Bulletin 747-53A2559, Revision 1, dated 
August 4, 2011, specifies to contact Boeing for repair instructions 
or additional modification requirements, repair of the cracking or 
additional actions must be done using a method approved in 
accordance with the procedures specified in paragraph (l) of this 
AD.

(k) Credit for Previous Actions

    This paragraph provides credit for the detailed inspections, 
repairs, and modification specified in paragraphs (g) and (h) of 
this AD, for that affected tension tie location only, if those 
actions were performed before the effective date of this AD using 
Boeing Alert Service Bulletin 747-53A2610, dated May 10, 2007 (which 
is not incorporated by reference in this AD).

(l) 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 (m)(1) 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.
    (4) AMOCs approved previously in accordance with AD 2007-16-19, 
Amendment 39-15158 (72 FR 45151, August 13, 2007), are approved as 
AMOCs for the corresponding provisions of this AD.

(m) Related Information

    (1) For more information about this AD, 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.
    (2) Service information identified in this AD that is not 
incorporated by reference may be viewed at the addresses specified 
in paragraphs (n)(4) and (n)(5) of this AD.

(n) 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.
    (3) The following service information was approved for IBR on 
June 13, 2014.
    (i) Boeing Alert Service Bulletin 747-53A2610, Revision 1, dated 
December 4, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
September 12, 2012 (77 FR 47267, August 8, 2012).
    (i) Boeing Service Bulletin 747-53A2559, Revision 1, dated 
August 4, 2011.
    (ii) Reserved.
    (5) 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.
    (6) You may view this service information at FAA, 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.
    (7) 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 April 22, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-09832 Filed 5-8-14; 8:45 am]
BILLING CODE 4910-13-P
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