[Federal Register Volume 80, Number 86 (Tuesday, May 5, 2015)]
[Proposed Rules]
[Pages 25627-25629]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10315]


 ========================================================================
 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. 80, No. 86 / Tuesday, May 5, 2015 / Proposed 
Rules  

[[Page 25627]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1270; Directorate Identifier 2014-NM-222-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 747-100, -200B, -200C, -200F, -300, -
400, -400D, and -400F series airplanes. This proposed AD was prompted 
by reports of significant fuselage skin damage at certain parts of the 
dorsal fairing, due to wear from the dorsal fairing. This proposed AD 
would require repetitive detailed inspections for wear and cracks of 
the fuselage skin under the dorsal fairing, and related investigative 
and corrective actions if necessary. This proposed AD would also 
require repetitive post-repair external surface high frequency eddy 
current inspections of the blended areas of the skin and detailed 
inspections of the unrepaired areas, and related investigative and 
corrective actions if necessary. We are proposing this AD to detect and 
correct fuselage skin damage of the dorsal fairing area, which could 
result in skin cracking and consequent depressurization of the 
airplane.

DATES: We must receive comments on this proposed AD by June 19, 2015.

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; phone: 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-2015-
1270.

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-2015-
1270; 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; 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-2015-1270; 
Directorate Identifier 2014-NM-222-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 reports of significant fuselage skin damage at the 
dorsal fairing forward of station (STA) 2280, due to wear from the 
dorsal fairing. These two airplanes had accumulated 45,707 and 71,702 
total flight hours. The skin damage occurred from inadequate clearance 
between fuselage crown skin and the lower aft corners of the dorsal 
fairing. Affected airplanes are limited to those delivered or 
retrofitted with certain dorsal fairing assemblies. Airplanes with 
other dorsal fairing configurations are not expected to develop skin 
wear. This inadequate clearance, if not corrected, could result in skin 
cracking and consequent depressurization of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014. This service information describes procedures for 
repetitive inspections, repair, and modification of the fuselage skin 
under the dorsal fairing. Refer to this service information for 
information on the procedures and compliance times. This service 
information is reasonably available at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-1270. Or see ADDRESSES 
for other ways to access this service information.

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.

[[Page 25628]]

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information identified previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.''
    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 actions, 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'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which steps in the service information are required for 
compliance with an AD. Differentiating these steps from other tasks in 
the service information is expected to improve an owner's/operator's 
understanding of crucial AD requirements and help provide consistent 
judgment in AD compliance. The steps that are identified as RC 
(required for compliance) in any service information identified 
previously have a direct effect on detecting, preventing, resolving, or 
eliminating an identified unsafe condition.
    Steps that are identified as RC must be done to comply with the 
proposed AD. However, steps that are not identified as RC are 
recommended. Those steps that are not identified as RC may be deviated 
from using accepted methods in accordance with the operator's 
maintenance or inspection program without obtaining approval of an 
alternative method of compliance (AMOC), provided the steps identified 
as RC can be done and the airplane can be put back in a serviceable 
condition. Any substitutions or changes to steps identified as RC will 
require approval of an AMOC.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin 747-53A2876, dated October 22, 2014, 
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.
    Tables 4 and 5 in paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2876, dated October 22, 2014, specify 
accomplishing the post-repair inspections identified in Part 8 of the 
service bulletin. Part 8 of the service bulletin allows the option of 
high frequency eddy current (HFEC) or low frequency eddy current (LFEC) 
inspections of the blended areas of the skin; however, this proposed AD 
does not allow the option of an LFEC inspection. This difference has 
been coordinated with Boeing.
    Tables 3, 6, and 7 in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2876, dated October 22, 2014, specify 
post-modification inspections at certain fuselage crown skin locations, 
which may be used in support of compliance with section 121.1109(c)(2) 
or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 
121.1109(c)(2) or 129.109(b)(2)). However, this NPRM does not propose 
to require those post-modification inspections. This difference has 
been coordinated with Boeing.

Costs of Compliance

    We estimate that this proposed AD affects 93 airplanes of U.S. 
registry.
    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
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections.......................  Up to 15 work-hours            $0   Up to $1,275 per      Up to $118,575 per inspection cycle.
                                     x $85 per hour =                    inspection cycle.
                                     $1,275.
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    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.

[[Page 25629]]

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-2015-1270; Directorate Identifier 
2014-NM-222-AD.

(a) Comments Due Date

    We must receive comments by June 19, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, -200B, -
200C, -200F, -300, -400, -400D, and -400F series airplanes; 
certificated in any category, as identified in Boeing Alert Service 
Bulletin 747-53A2876, dated October 22, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of significant fuselage skin 
damage at the dorsal fairing forward of station (STA) 2280 due to 
wear from the dorsal fairing. We are issuing this AD to detect and 
correct fuselage skin damage of the dorsal fairing area, which could 
result in skin cracking and consequent depressurization of the 
airplane.

(f) Compliance

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

(g) Inspections and Repair

    At the applicable time specified in tables 1 and 2 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, 
dated October 22, 2014, except as provided by paragraph (j)(1) of 
this AD, do a detailed inspection of the fuselage skin under the 
dorsal fairing for wear or cracks, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2876, dated October 22, 2014, except as required by paragraph 
(j)(2) of this AD. Do all applicable related investigative and 
corrective actions at the time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014. Repeat the applicable inspections of the fuselage 
skin thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014.

(h) Post-Repair Inspections

    At the applicable time specified in tables 4 and 5 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, 
dated October 22, 2014, except as provided by paragraph (j)(1) of 
this AD, do an external surface high frequency eddy current 
inspection of the blended areas of the skin and a detailed 
inspection of the unrepaired areas, and do all applicable related 
investigative and corrective actions, in accordance with Part 8 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
747-53A2876, dated October 22, 2014, except as required by paragraph 
(j)(2) of this AD. Do all applicable related investigative and 
corrective actions at the time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014. Repeat the applicable inspections of the blended 
areas of the skin thereafter at the applicable times specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2876, dated October 22, 2014.

(i) Post-Modification Inspections

    The post-modification inspections specified in tables 3, 6, and 
7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2876, dated October 22, 2014, are not required by 
this AD.

    Note 1 to paragraph (i) of this AD: The post-modification 
inspections specified in tables 3, 6, and 7 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014, may be used in support of compliance with section 
121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations 
(14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding 
actions specified in the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2876, dated October 22, 2014, are not 
required by this AD.

(j) Exceptions to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014, 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.
    (2) Although Boeing Alert Service Bulletin 747-53A2876, dated 
October 22, 2014, specifies to contact Boeing for repair data, and 
specifies that action as ``RC'' (Required for Compliance), this AD 
requires repair before further flight using a method approved in 
accordance with the procedures specified in paragraph (k) of this 
AD.

(k) 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 (k)(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 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.
    (4) Except as required by paragraph (j)(2) of this AD: If any 
service information contains steps that are identified as RC 
(Required for Compliance), those steps must be done to comply with 
this AD; any steps that are not identified as RC are recommended. 
Those steps that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the steps identified as RC can be done and the airplane can be put 
back in a serviceable condition. Any substitutions or changes to 
steps identified as RC require approval of an AMOC.

(l) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6428; 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; phone: 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.

    Issued in Renton, Washington, on April 27, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-10315 Filed 5-4-15; 8:45 am]
 BILLING CODE 4910-13-P