Airworthiness Directives; The Boeing Company Airplanes

[Federal Register Volume 81, Number 238 (Monday, December 12, 2016)]
[Rules and Regulations]
[Pages 89371-89373]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-29246]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5598; Directorate Identifier 2016-NM-001-AD; 
Amendment 39-18735; AD 2016-25-09]
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) 2012-22-02 for 
certain The Boeing Company Model 747-400, -400D, and -400F series 
airplanes. AD 2012-22-02 required measuring the web at station (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. This new AD 
requires, for certain airplanes, replacement of the web, including 
related investigative and corrective actions if necessary. This AD was 
prompted by a determination that there were no inspection or repair 
procedures included in AD 2012-22-02 for airplanes with a certain crown 
frame web thickness. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective January 17, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 17, 
2017.

ADDRESSES: For service information identified in this final rule, 
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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5598.

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-2016-
5598; 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: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2012-22-02, Amendment 39-17238 (77 FR 69739, 
November 21, 2012) (``AD 2012-22-02''). AD 2012-22-02 applied to 
certain The Boeing Company Model 747-400, -400D, and -400F series 
airplanes. The NPRM published in the Federal Register on April 28, 2016 
(81 FR 25357) (``the NPRM''). The NPRM was prompted by a determination 
that there were no inspection or repair procedures included in AD 2012-
22-02 for airplanes with a STA 320 crown frame web thickness less than 
0.078 inch, or greater than or equal to 0.084 inch and less than or 
equal to 0.135 inch. The NPRM proposed to continue to require certain 
actions required by AD 2012-22-02. The NPRM also proposed to require, 
for certain airplanes, replacement of the web, including 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. Such damage could result in in-flight 
decompression of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Support for the NPRM

    United Airlines stated that it concurs with the NPRM.

Request To Remove Redundant Requirements

    Boeing requested we change paragraph (i) of the proposed AD to 
remove redundant language. Boeing requested we remove the second half 
of the paragraph and subparagraphs (i)(1) and (i)(2) of the proposed AD 
because they include redundant requirements. Boeing also noted that the 
redundant requirements include an exception that does not apply to 
table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2784, Revision 2, dated August 20, 2015.
    We agree to revise paragraph (i) of this AD for the reasons 
provided by Boeing. We have revised paragraph (i) of this AD 
accordingly.

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 change described previously, and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2784, Revision 2, 
dated August 20, 2015. The service information describes procedures for 
various inspections for cracks and missing fasteners, web and fastener 
replacement, and related investigative and corrective actions, if 
necessary. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

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

[[Page 89372]]



                                                 Estimated Costs
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                                                                            Cost per
            Action                   Labor cost          Parts cost         product       Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Measurement, inspection, and   219 work-hours x $85   Up to $21,887...  Up to $40,502    Up to $1,174,558 per
 web replacement [retained      per hour = $18,615                       per inspection   inspection and
 actions from AD 2012-22-02].   per inspection and                       and              replacement.
                                replacement.                             replacement.
Post-replacement inspection    135 work-hours x $85   $0..............  $11,475 per      $332,775 per inspection
 [retained actions from AD      per hour = $11,475                       inspection       cycle.
 2012-22-02].                   per inspection cycle.                    cycle.
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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) 
2012-22-02, Amendment 39-17238 (77 FR 69739, November 21, 2012), and 
adding the following new AD:

2016-25-09 The Boeing Company: Amendment 39-18735; Docket No. FAA-
2016-5598; Directorate Identifier 2016-NM-001-AD.

(a) Effective Date

    This AD is effective January 17, 2017.

(b) Affected ADs

    This AD replaces AD 2012-22-02, Amendment 39-17238 (77 FR 69739, 
November 21, 2012) (``AD 2012-22-02'').

(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 Alert Service Bulletin 747-53A2784, Revision 2, dated 
August 20, 2015.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a determination that there were no 
inspection or repair procedures included in AD 2012-22-02 for 
airplanes with a station (STA) 320 crown frame web thickness less 
than 0.078 inch, or greater than or equal to 0.084 inch and less 
than or equal to 0.135 inch. We are issuing this AD to prevent 
complete fracture of the crown frame assembly, and consequent damage 
to the skin. Such damage could result in 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 for Certain Airplanes

    For Group 1, Configuration 3 airplanes, identified in Boeing 
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 
2015: At the compliance time specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, 
Revision 2, dated August 20, 2015, measure the thickness 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 Alert Service Bulletin 747-
53A2784, Revision 2, dated August 20, 2015, except as required by 
paragraph (l)(2) of this AD. Do all related investigative and 
corrective actions at the applicable times specified in tables 2 and 
3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2784, Revision 2, dated August 20, 2015.

(h) Inspections (Web With No Repair Doubler) and Related Investigative 
and Corrective Actions (Including Web Replacement)

    For Group 1, Configuration 1 airplanes, identified in Boeing 
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 
2015: For airplanes with a web thickness less than 0.136 inch and no 
repair doubler installed on the web, at the time specified in table 
2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2784, Revision 2, dated August 20, 2015, 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 Alert 
Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, 
except as specified in paragraph (l)(2) of this AD. Do the 
applicable related investigative and corrective actions at the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 
20, 2015.

(i) Inspection (Web With Repair Doubler) and Related Investigative and 
Corrective Actions (Including Web Replacement)

    For Group 1, Configuration 1 airplanes, identified in Boeing 
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 
2015: For airplanes with a web thickness less than 0.136 inch and a 
repair doubler installed on the web, at the time specified in table 
3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2784, Revision 2, dated August 20, 2015, do a

[[Page 89373]]

detailed inspection for any crack in the upper chord and lower chord 
of the STA 320 crown frame, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2784, Revision 2, dated August 20, 2015, except as specified in 
paragraph (l)(2) of this AD. Do the applicable related investigative 
and corrective actions at the applicable times specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2784, Revision 2, dated August 20, 2015.

(j) Web Replacement for Certain Airplanes

    For Group 1, Configuration 2 airplanes, identified in Boeing 
Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 
2015: At the applicable time specified in table 5 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, 
Revision 2, dated August 20, 2015, except as provided by paragraph 
(l)(1) of this AD, replace the web, including doing related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2784, Revision 2, dated August 20, 2015, except as required by 
paragraph (l)(2) of this AD. Do all applicable related investigative 
and corrective actions before further flight.

(k) Post-Replacement Repetitive Inspections of Replaced Web

    Following any web replacement required by this AD, at the time 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2784, Revision 2, dated August 20, 2015: 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 Alert 
Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, 
except as required by paragraph (l)(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 Alert Service Bulletin 
747-53A2784, Revision 2, dated August 20, 2015. 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.

(l) Exceptions to the Service Information, With Updated Service 
Information

    (1) Where Boeing Alert Service Bulletin 747-53A2784, Revision 2, 
dated August 20, 2015, specifies a compliance time ``after the 
Revision 2 date of the service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Where Boeing Alert Service Bulletin 747-53A2784, Revision 2, 
dated August 20, 2015, 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 (n) of this AD.

(m) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraphs (h), (i), and (k) of this AD, if those actions were 
performed before December 26, 2012 (the effective date of AD 2012-
22-02), using Boeing Service Bulletin 747-53A2784, dated August 27, 
2009.
    (2) This paragraph provides credit for the actions required by 
paragraphs (h), (i), and (k) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Service 
Bulletin 747-53A2784, Revision 1, dated September 14, 2011. This 
service information was incorporated by reference in AD 2012-22-02.

(n) 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 (o)(1) of this AD.
    (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, modification, or alteration 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. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(o) 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: 
[email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(3) and (p)(4) of this AD.

(p) 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 747-53A2784, Revision 2, dated 
August 20, 2015.
    (ii) Reserved.
    (3) 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.
    (4) You may view this 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 November 25, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-29246 Filed 12-9-16; 8:45 am]
 BILLING CODE 4910-13-P

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