[Federal Register Volume 78, Number 187 (Thursday, September 26, 2013)]
[Proposed Rules]
[Pages 59293-59295]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-23456]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0830; Directorate Identifier 2013-NM-128-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 777 airplanes. This proposed AD was 
prompted by a report of cracking in the fuselage skin underneath the 
satellite communication (SATCOM) antenna adapter. This proposed AD 
would require repetitive inspections of the visible fuselage skin and 
doubler if installed, for cracking, corrosion, and any indication of 
contact of a certain fastener to a bonding jumper, and repair if 
necessary. We are proposing this AD to detect and correct cracking and 
corrosion in the fuselage skin, which could lead to rapid decompression 
and loss of structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by November 12, 
2013.

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, 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 review copies of the 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; 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: Melanie Violette, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6422; 
fax: (425) 917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION:

[[Page 59294]]

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-2013-0830; 
Directorate Identifier 2013-NM-128-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

    We received a report of cracking and corrosion in the fuselage skin 
underneath the SATCOM antenna adapter. During a maintenance planning 
data inspection, one operator reported a 16-inch crack under the 3-bay 
SATCOM antenna adapter plate in the crown skin of the fuselage on an 
airplane that was 14 years old with approximately 14,000 total flight 
cycles. Subsequent to this crack finding, the same operator inspected 
42 other airplanes that are between 6 and 16 years old and found some 
local corrosion, but no other cracking. Cracking and corrosion in the 
fuselage skin, if not corrected, could lead to rapid decompression and 
loss of structural integrity of the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 777-53A0068, dated June 
12, 2013. For information on the procedures and compliance times, see 
this service information at http://www.regulations.gov by searching for 
Docket No. FAA-2013-0830.

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

    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.''

Differences Between the Proposed AD and the Service Information

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions 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.

Costs of Compliance

    We estimate that this proposed AD affects 120 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................  Up to 36                       $0  Up to $3,060 per      Up to $367,200 per
                                    work[dash]hours x                  inspection cycle.     inspection cycle.
                                    $85 per hour =
                                    $3,060 per
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

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-2013-0830; Directorate Identifier 
2013-NM-128-AD.

[[Page 59295]]

(a) Comments Due Date

    We must receive comments by November 12, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and -777F series airplanes, certificated in any 
category, as identified in Boeing Alert Service Bulletin 777-
53A0068, dated June 12, 2013.

 (d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report of cracking in the fuselage 
skin underneath the satellite communication (SATCOM) antenna 
adapter. We are issuing this AD to detect and correct cracking and 
corrosion in the fuselage skin, which could lead to rapid 
decompression and loss of structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    (1) For Group 1-4 airplanes and Group 5, Configuration 3 and 4 
airplanes identified in Boeing Alert Service Bulletin 777-53A0068, 
dated June 12, 2013: Except as required by paragraphs (h)(1) and 
(h)(2) of this AD, within the applicable compliance times specified 
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
777-53A0068, dated June 12, 2013, do internal detailed and surface 
high frequency eddy current (HFEC) inspections of the visible 
fuselage skin, and doubler if installed, for cracking; do external 
detailed and surface HFEC inspections of the visible fuselage skin, 
and doubler if installed, for cracking, corrosion, and any 
indication that shows a contact of a certain fastener to a bonding 
jumper; and do all applicable repairs; in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
53A0068, dated June 12, 2013, except as required by paragraph (h)(3) 
of this AD. Thereafter, repeat the inspections at the applicable 
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 777-53A0068, dated June 12, 2013. Do all 
applicable repairs before further flight.
    (2) For Group 5, Configuration 1, 2, and 5 airplanes identified 
in Boeing Alert Service Bulletin 777-53A0068, dated June 12, 2013: 
No action is required by this AD.

(h) Exceptions to the Service Information

    (1) The ``Condition Questionnaire'' column in Tables 1, 5, and 9 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
777-53A0068, dated June 12, 2013, refers to airplanes with certain 
conditions ``at the time of the original issue date of this service 
bulletin.'' For this AD, use ``as of the effective date of this AD'' 
instead of ``at the time of the original issue date of this service 
bulletin.''
    (2) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 777-53A0068, dated June 12, 2013, specifies a 
compliance time ``after the original issue date of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (3) If any crack, corrosion, or indication that shows a contact 
of the fastener attaching the SATCOM lug adapter plate to the 
bonding plate is found during any inspection required by this AD, 
and Boeing Alert Service Bulletin 777-53A0068, dated June 12, 2013, 
specifies to contact Boeing for repair instructions: Before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (i) of this AD.

 (i) 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 the Related Information 
section 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 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.

(j) Related Information

    (1) For more information about this AD, contact Melanie 
Violette, Aerospace Engineer, Airframe Branch, ANM 120S, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, 
WA 98057 3356; phone: (425) 917-6422; fax: (425) 917-6590; email: 
[email protected].
    (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 review copies of the 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.

    Issued in Renton, Washington, on September 18, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-23456 Filed 9-25-13; 8:45 am]
BILLING CODE 4910-13-P