
[Federal Register Volume 81, Number 82 (Thursday, April 28, 2016)]
[Proposed Rules]
[Pages 25357-25360]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-09647]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 81, No. 82 / Thursday, April 28, 2016 / 
Proposed Rules  

[[Page 25357]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5598; Directorate Identifier 2016-NM-001-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-22-
02, which applies to certain The Boeing Company Model 747-400, -400D, 
and -400F series airplanes. AD 2012-22-02 currently requires 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. Since we issued AD 2012-22-02, it was determined that there 
were no inspection or repair procedures included 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. This 
proposed AD would 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.

DATES: We must receive comments on this proposed AD by June 13, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-5598; 
Directorate Identifier 2016-NM-001-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On October 19, 2012, we issued AD 2012-22-02, Amendment 39-17238 
(77 FR 69739, November 21, 2012) (``AD 2012-22-02''), for certain The 
Boeing Company Model 747-400, -400D, and -400F series airplanes. AD 
2012-22-02 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. AD 2012-22-02 resulted from reports of crown frame web 
cracking at left buttock line (LBL) 15.0, STA 320. We issued AD 2012-
22-02 to prevent complete fracture of the crown frame assembly, and 
consequent damage to the skin and in-flight decompression of the 
airplane.

Actions Since AD 2012-22-02 Was Issued

    Since we issued AD 2012-22-02, it was determined that there was no 
work included 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.

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.

[[Page 25358]]

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2012-22-02, this proposed AD would retain certain 
requirements of AD 2012-22-02. Those requirements are referenced in the 
service information identified previously, which, in turn, is 
referenced in paragraphs (h), (i), and (k) of this proposed AD. This 
proposed AD would require accomplishing the actions specified in the 
service information described previously, except as discussed under 
``Differences Between the Proposed AD and the Service Information.''
    For information on the procedures and compliance times, see this 
service information at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-5598.
    The phrase ``related investigative actions'' is used in this 
proposed AD. Related investigative actions are follow-on actions that 
(1) are related to the primary action, and (2) further investigate the 
nature of any condition found. Related investigative actions in an AD 
could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
Corrective actions correct or address any condition found. Corrective 
actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    For Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated 
August 20, 2015, Table 4: STA 320 Post Web Replacement Inspection of 
paragraph 1.E., ``Compliance,'' the conditional action statement does 
not include airplanes that were inspected or repaired in accordance 
with Part 8 of the Work Instructions. The statement should read: ``All 
airplanes that have done the STA 320 crown frame web replacement in 
accordance with paragraph 3.B. WORK INSTRUCTIONS, PARTS 5 OR PART 8.'' 
Paragraph (k) of this proposed AD applies to all airplanes on which a 
web replacement is done as required by paragraphs (h), (i), and (j) of 
the proposed AD, e.g., the replacement is done as specified in Part 5 
or Part 8 of paragraph 3.B., ``Work Instructions,'' of the service 
information.

Costs of Compliance

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

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
              Action                      Labor cost             Parts cost          Cost per product                 Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Measurement, inspection, and web    219 work-hours x $85   Up to $21,887........  Up to $40,502 per      $Up to 1,174,558.
 replacement. [retained actions      per hour = $18,615.                           inspection and
 from AD 2012[dash]22[dash]02].                                                    replacement.
Post-replacement inspection         135 work-hours x $85   $0...................  $11,475 per            $332,775 per inspection cycle.
 [retained actions from AD           per hour = $11,475                            inspection cycle.
 2012[dash]22[dash]02].              per inspection 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

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

The Boeing Company: Docket No. FAA-2016-5598; Directorate Identifier 
2016-NM-001-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by June 13, 
2016.

(b) Affected ADs

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

[[Page 25359]]

(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 reports of crown frame web cracking at 
left buttock line (LBL) 15.0, station (STA) 320 and 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. 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 Table 2 and 
Table 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 
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. At the applicable 
compliance time specified in 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, 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 2, dated August 20, 2015, except as required by paragraph 
(l)(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) 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, which is not incorporated by reference in this AD.
    (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.

(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) 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

[[Page 25360]]

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: 425-91-6590; email: 
Bill.Ashforth@faa.gov.
    (2) 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 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.

    Issued in Renton, Washington, on April 15, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-09647 Filed 4-27-16; 8:45 am]
 BILLING CODE 4910-13-P


