[Federal Register Volume 82, Number 233 (Wednesday, December 6, 2017)]
[Proposed Rules]
[Pages 57552-57554]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26193]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 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.
 
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 

  Federal Register / Vol. 82, No. 233 / Wednesday, December 6, 2017 / 
Proposed Rules  

[[Page 57552]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1099; Product Identifier 2017-NM-093-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 adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 767-200 and -300 series airplanes. 
This proposed AD was prompted by a report of two cracks at a certain 
frame inner chord. This proposed AD would require a detailed inspection 
for any material review board (MRB) filler installed in the area from 
the frame web to the stub-beam fitting at certain stations to determine 
if the filler extends above the frame-to-stub-beam joint, and 
applicable on-condition actions. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by January 22, 
2018.

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: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; 
telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may 
view this referenced service information at the FAA, Transport 
Standards Branch, 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-2017-1099.

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-2017-
1099; 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 NPRM, 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: Wayne Lockett, Aerospace Engineer, 
Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6447; fax: 425-917-6590; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-1099; 
Product Identifier 2017-NM-093-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM 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

    We have received a report of a crack on the transition radius of 
the station (STA) 883.5 frame inner chord and an additional crack 
indication at a fastener hole in the frame inner chord common to a MRB 
filler that extended above the frame-to-stub-beam joint. Extending the 
MRB filler above the frame-to-stub-beam joint changes the critical 
fastener location. For this configuration of the overwing frame-to-
stub-beam joint, the upper-lobe-interior-structural and internal zonal 
(general visual) inspections in the existing baseline maintenance 
program together with supplemental structural inspections of the 
overwing stub frames are not adequate to reliably detect a crack in the 
frame inner chord before the crack grows to a critical length. This 
condition, if not corrected, could result in the inability of one or 
more overwing stub frames between STA 808 and STA 933, each a principal 
structural element, to sustain limit load, which could adversely affect 
the structural integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Requirements Bulletin 767-53A0278 RB, 
dated June 30, 2017. The service information describes procedures for a 
detailed inspection for any MRB filler installed in the area from the 
frame web to the stub-beam fitting on the left and right side at STA 
859.5, 883.5, and 903.5 to determine if the filler extends above the 
frame-to-stub-beam joint, and applicable on-condition actions. The 
applicable on-condition actions include repetitive surface high 
frequency eddy current inspections and repair for cracking in the frame 
inner chord around the end fastener common to each affected MRB filler. 
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.

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

[[Page 57553]]

develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishment of the actions 
identified in the Boeing Alert Requirements Bulletin 767-53A0278 RB, 
dated June 30, 2017, described previously, except for any differences 
identified as exceptions in the regulatory text of this proposed AD.
    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-2017-1099.

Explanation of Requirements Bulletin

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(AD ARC), to enhance the AD system. One enhancement is a process for 
annotating which steps in the service information are ``required for 
compliance'' (RC) with an AD. Boeing has implemented this RC concept 
into Boeing service bulletins.
    In an effort to further improve the quality of ADs and AD-related 
Boeing service information, a joint process improvement initiative was 
worked between the FAA and Boeing. The initiative resulted in the 
development of a new process in which the service information more 
clearly identifies the actions needed to address the unsafe condition 
in the ``Accomplishment Instructions.'' The new process results in a 
Boeing Requirements Bulletin, which contains only the actions needed to 
address the unsafe condition (i.e., only the RC actions).

Differences Between This Proposed AD and the Service Information

    Airplanes in Group 1, Configuration 1, and Group 2, Configuration 
1, as identified in Boeing Alert Requirements Bulletin 767-53A0278 RB, 
dated June 30, 2017, may be modified to a freighter configuration per 
certain supplemental type certificates. For the modified airplanes, in 
lieu of accomplishing the actions specified in Boeing Alert 
Requirements Bulletin 767-53A0278 RB, dated June 30, 2017, for Group 1, 
Configuration 1, and Group 2, Configuration 1, the actions specified in 
Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 2017, 
for Group 1, Configuration 2, and Group 2, Configuration 2, as 
applicable, must be done. We have coordinated this difference with 
Boeing.

Costs of Compliance

    We estimate that this proposed AD affects 51 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Detailed Inspection................  20 work-hours x $85 per                  $0          $1,700         $86,700
                                      hour = $1,700.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required. We have no way of determining the 
number of aircraft that might need these on-condition actions:

               Estimated Costs of On-Condition Inspections
------------------------------------------------------------------------
            Labor cost                Parts cost      Cost per product
------------------------------------------------------------------------
3 work-hours x $85 per hour = $255              $0  $255 per inspection
 per inspection cycle.                               cycle.
------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repairs specified in this proposed 
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.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

    We 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 this 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.

[[Page 57554]]

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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2017-1099; Product Identifier 
2017-NM-093-AD.

(a) Comments Due Date

    We must receive comments by January 22, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 767-200 and -300 
series airplanes, as identified in Boeing Alert Requirements 
Bulletin 767-53A0278 RB, dated June 30, 2017, certificated in any 
category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of a crack on the transition 
radius of the station (STA) 883.5 frame inner chord and an 
additional crack indication at a fastener hole in the frame inner 
chord common to a material review board (MRB) filler that extended 
above the frame-to-stub-beam joint. We are issuing this AD to detect 
and correct cracking of the frame inner chord, which could result in 
the inability of one or more overwing stub frames between STA 808 
and STA 933, each a principal structural element, to sustain limit 
load; this condition could adversely affect the structural integrity 
of the airplane.

(f) Compliance

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

(g) Required Actions

    Except as required by paragraph (h) of this AD: At the 
applicable times specified in the ``Compliance'' paragraph of Boeing 
Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 2017, do 
all applicable actions identified in, and in accordance with, the 
Accomplishment Instructions of Boeing Alert Requirements Bulletin 
767-53A0278 RB, dated June 30, 2017.
    Note 1 to paragraph (g) of this AD: Guidance for accomplishing 
the actions required by this AD can be found in Boeing Alert Service 
Bulletin 767-53A0278, dated June 30, 2017, which is referred to in 
Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 
2017.

(h) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements 
of this AD, the phrase ``the effective date of this AD'' may be 
substituted for ``the original issue date of Requirements Bulletin 
767-53A0278 RB'' as specified in Boeing Alert Requirements Bulletin 
767-53A0278 RB, dated June 30, 2017.
    (2) Where Boeing Alert Requirements Bulletin 767-53A0278 RB, 
dated June 30, 2017, specifies contacting Boeing, this AD requires 
repair using a method approved in accordance with the procedures 
specified in paragraph (i) of this AD.
    (3) For airplanes identified as Group 1, Configuration 1, in 
Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 
2017, that have been modified to a freighter configuration: The 
actions specified in Boeing Alert Requirements Bulletin 767-53A0278 
RB, dated June 30, 2017, for Group 1, Configuration 2, must be done 
instead of the actions for Group 1, Configuration 1, except as 
required by paragraph (h)(2) of this AD.
    (4) For airplanes identified as Group 2, Configuration 1, in 
Boeing Alert Requirements Bulletin 767-53A0278 RB, dated June 30, 
2017, that have been modified to a freighter configuration: The 
actions specified in Boeing Alert Requirements Bulletin 767-53A0278 
RB, dated June 30, 2017, for Group 2, Configuration 2, must be done 
instead of the actions for Group 2, Configuration 1, except as 
required by paragraph (h)(2) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO Branch, 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 certification office, send it to the attention of the 
person identified in paragraph (j)(1) of this AD. Information may be 
emailed to: [email protected].
    (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 Branch, 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.

(j) Related Information

    (1) For more information about this AD, contact Wayne Lockett, 
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 
Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; fax: 
425-917-6590; email: [email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Standards Branch, 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 November 27, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26193 Filed 12-5-17; 8:45 am]
BILLING CODE 4910-13-P