Document ID: FAA-2014-0423-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2014-06-30T04:00Z

[Federal Register Volume 79, Number 125 (Monday, June 30, 2014)]
[Proposed Rules]
[Pages 36669-36671]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-15248]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0423; Directorate Identifier 2013-NM-233-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model DC-10-10, DC-10-10F, DC-10-30, DC-10-
30F (KC-10A and KDC-10), DC-10-40, MD-10-10F, and MD-10-30F airplanes. 
This proposed AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the forward cargo compartment frames are 
subject to widespread fatigue damage (WFD). This proposed AD would 
require an inspection of the attachment holes at the forward cargo 
compartment frames and the cargo liner for cracking, and repair if 
necessary. This proposed AD would also require installing new oversized 
fasteners in the forward cargo compartment frames. We are proposing 
this AD to prevent fatigue cracking of the forward cargo compartment 
frames, which could result in loss of the fail-safe structural 
integrity of the airplane.

DATES: We must receive comments on this proposed AD by August 14, 2014.

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 proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; Internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA 98057-3356. 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-2014-
0423; 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: Nenita Odesa, Aerospace Engineer, 
Airframe Branch, ANM-120L, Los Angeles Aircraft Certification Office 
(ACO), FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5234; fax: 562-627-5210; email: nenita.odesa@faa.gov.

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-2014-0423; 
Directorate Identifier 2013-NM-233-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.

[[Page 36670]]

Discussion

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global damage can also occur 
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small 
initially to be reliably detected with normal inspection methods. 
Without intervention, these cracks will grow, and eventually compromise 
the structural integrity of the airplane, in a condition known as 
widespread fatigue damage (WFD). As an airplane ages, WFD will likely 
occur, and will certainly occur if the airplane is operated long enough 
without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    This proposed AD was prompted by cracking that occurred during a 
full-scale fatigue test airplane during the certification process. Such 
cracking could occur in the active airplane fleet prior to the fleet 
reaching its LOV. We are proposing this AD to prevent fatigue cracking 
of the forward cargo compartment frames, which could result in loss of 
the fail safe structural integrity of the airplane.

Relevant Service Information

    We reviewed Boeing Service Bulletin DC10-53-182, dated June 28, 
2013. 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-2014-0423.

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 these same type 
designs.

Proposed AD Requirements

    This proposed AD would require accomplishing an inspection of the 
attachment holes at the forward cargo compartment frames and the cargo 
liner for cracking, and repair if necessary. This proposed AD would 
also require installing new oversized fasteners in the forward cargo 
compartment frames. These actions are specified in the service 
information described previously, except as discussed under 
``Differences Between this Proposed AD and the Service Information.''

Differences Between This Proposed AD and the Service Information

    Boeing Service Bulletin DC10-53-182, dated June 28, 2013, specifies 
to contact the manufacturer for instructions on how to repair cracks 
detected during the high frequency eddy current inspection, but this 
proposed AD would require that those actions be done in one of the 
following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Explanation of Compliance Time

    The compliance time for the inspection specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is modified before WFD develops in airplanes. Standard 
inspection techniques cannot be relied on to detect WFD before it 
becomes a hazard to flight. We will not grant any extensions of the 
compliance time to complete any AD-mandated service bulletin related to 
WFD without extensive new data that would substantiate and clearly 
warrant such an extension.

Costs of Compliance

    We estimate that this proposed AD affects 25 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                           Cost per
            Action                   Labor cost          Parts cost        product       Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Inspection...................  Up to 19 work-hours x  $0.............  Up to $1,615...  Up to $40,375.
                                $85 per hour =
                                $1,615.
Modification.................  Up to 6 work-hours x   Up to $801.....  Up to $1,311...  Up to $32,775.
                                $85 per hour = $510.
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[[Page 36671]]

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this 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 proposed 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 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.

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-2014-0423; Directorate Identifier 
2013-NM-233-AD.

(a) Comments Due Date

    We must receive comments by August 14, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model DC-10-10, DC-10-10F, 
DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, MD-10-10F, and 
MD-10-30F airplanes, certificated in any category, identified in 
Boeing Service Bulletin DC10-53-182, dated June 28, 2013.

(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 forward cargo compartment frames 
are subject to widespread fatigue damage (WFD). We are issuing this 
AD to prevent fatigue cracking of the forward cargo compartment 
frames, which could result in loss of the fail-safe structural 
integrity of the airplane.

(f) Compliance

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

(g) Inspection

    Prior to the accumulation of 30,000 total flight cycles, or 
within 72 months after the effective date of this AD, whichever 
occurs later: Do a high frequency eddy current inspection for 
cracking of the attachment holes at the forward cargo compartment 
frames and the cargo liner, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC10-53-182, dated June 28, 
2013. If any crack is found, before further flight, repair using a 
method approved in accordance with the procedures specified in 
paragraph (i) of this AD.

(h) Installation of New Fasteners

    If no cracking is found during the inspection required by 
paragraph (g) of this AD: Before further flight, install new 
oversized fasteners to attach the forward cargo liner to the forward 
cargo compartment frame, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC10-53-182, dated June 28, 
2013.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (j)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-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, Los Angeles 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.

(j) Related Information

    (1) For more information about this AD, contact Nenita Odesa, 
Aerospace Engineer, Airframe Branch, ANM-120L, Los Angeles Aircraft 
Certification Office (ACO), FAA, 3960 Paramount Boulevard, Lakewood, 
CA 90712-4137; phone: 562-627-5234; fax: 562-627-5210; email: 
nenita.odesa@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; Internet 
https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA 98057-3356. For information on the 
availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington on June 19, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-15248 Filed 6-27-14; 8:45 am]
BILLING CODE 4910-13-P