Document ID: FAA-2014-0283-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2014-05-28T04:00Z

[Federal Register Volume 79, Number 102 (Wednesday, May 28, 2014)]
[Proposed Rules]
[Pages 30486-30490]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-12260]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0283; Directorate Identifier 2012-NM-183-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 supersede Airworthiness Directive (AD) 2010-03-
05, which applies to all The Boeing Company Model 747-200C and -200F 
series airplanes. AD 2010-03-05 currently requires, for section 41 
upper deck floor beam upper chords, an inspection for cracks of certain 
fastener holes, and corrective action if necessary; and repetitive 
replacements of the upper chords, straps (or angles), and radius 
fillers of certain upper deck floor beams and, for any replacement that 
is done, inspections for cracks, and corrective actions if necessary. 
Since we issued AD 2010-03-05, we have determined that the upper deck 
floor beams are subject to widespread fatigue damage (WFD), the 
existing inspection program is not sufficient to maintain an acceptable 
level of safety, and section 42 upper deck floor beam upper chords are 
subject to the unsafe condition. This proposed AD would add post-
replacement inspections for section 41 and reduce certain compliance 
times. This proposed AD would also require repetitive inspections of 
section 42 upper deck floor beam upper chords, repetitive replacements 
of the upper chords, post-replacement inspections,

[[Page 30487]]

and corrective action if necessary. We are proposing this AD to detect 
and correct cracking of the upper chords and straps (or angles) of the 
floor beams, which could lead to failure of the floor beams and 
consequent loss of controllability, rapid decompression, and loss of 
structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by July 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 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 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 by searching for and locating Docket No. FAA-2014-
0283; 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: Roger Caldwell, Aerospace Engineer, 
Technical Operations Center, ANM-100D, FAA, Denver Aircraft 
Certification Office (ACO), 26805 East 68th Avenue, Room 214, Denver, 
CO 80249; phone: 303-342-1086; fax: 303-342-1088; email: 
roger.caldwell@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-2014-0283; 
Directorate Identifier 2012-NM-183-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

    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 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 design 
approval holders (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.
    On January 21, 2010, we issued AD 2010-03-05, Amendment 39-16188 
(75 FR 5692, February 4, 2010), for all The Boeing Company Model 747-
200C and -200F series airplanes. AD 2010-03-05 requires a high 
frequency eddy current (HFEC) inspection for cracks of certain fastener 
holes, and corrective action if necessary. AD 2010-03-05 also requires 
repetitive replacements of the upper chords, straps (or angles), and 
radius fillers of certain upper deck floor beams and, for any 
replacement that is done, detailed and open-hole HFEC inspections for 
cracks of the modified upper deck floor beams, and corrective actions 
if necessary. AD 2010-03-05 resulted from a report from the 
manufacturer that the accomplishment of certain existing inspections, 
repairs, and modifications is not adequate to ensure the structural 
integrity of the affected upper chords of the upper deck floor beams 
made of 7075 series aluminum alloy on airplanes that have exceeded 
certain thresholds. We issued AD 2010-03-05 to prevent cracking of the 
upper chords and straps (or angles) of the floor beams, which could 
lead to failure of the floor beams and

[[Page 30488]]

consequent loss of controllability, rapid decompression, and loss of 
structural integrity of the airplane.

Actions Since AD 2010-03-05, Amendment 39-16188 (75 FR 5692, February 
4, 2010), Was Issued

    Since we issued AD 2010-03-05, Amendment 39-16188 (75 FR 5692, 
February 4, 2010), we have determined that replacement of the upper 
chord of the upper deck floor beam is necessary at body stations aft of 
station 520. Upper chords of the upper deck floor beam aft of STA 520 
(540 through 740) are made from 2024 aluminum, and these upper chords 
aft of STA 520 have been determined to be a structure that is also 
susceptible to WFD. Ongoing inspection of this structure is not 
sufficient to maintain an acceptable level of safety, and therefore 
replacement of the structure is necessary. The modifications and 
inspections of the upper deck floor beams were developed to support the 
airplane's LOV of the engineering data that support the established 
structural maintenance program. It has also been determined that 
section 42 of the airplane is subject to the unsafe condition.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-53A2696, Revision 1, 
dated April 12, 2012. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2014-0283.

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 2010-03-05, Amendment 39-16188 (75 FR 5692, February 
4, 2010), this proposed AD would retain all of the requirements of AD 
2010-03-05. Those retained requirements are referenced in the service 
information identified previously, which, in turn, is referenced in 
paragraphs (g) and (h) of this proposed AD. This proposed AD would 
require, for section 41 upper deck floor beam upper chords, an HFEC 
inspection for cracks of certain fastener holes, and corrective action 
if necessary; and repetitive replacements of the upper chords, straps 
(or angles), and radius fillers of certain upper deck floor beams and, 
for any replacement that is done, detailed and open-hole HFEC 
inspections for cracks of the modified upper deck floor beams, and 
corrective actions if necessary.
    This proposed AD would add post-replacement inspections for section 
41 upper deck floor beam upper chords and reduce certain compliance 
times. This proposed AD also would require repetitive inspections of 
section 42 upper deck floor beam upper chords, repetitive replacements 
of the upper chords, post-replacement inspections, and corrective 
action if necessary.

Differences Between This 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.

Explanation of Compliance Time

    The compliance time for the replacement specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is replaced 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 information 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 on  U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Retained inspection and           663 work-hours x    $0................  $56,355 per         $1,408,875 per
 replacement (AD 2010-03-05,       $85 per hour =                          inspection/         inspection/
 Amendment 39[dash]16188 (75 FR    $56,355.                                replacement cycle.  replacement
 5692, February 4, 2010)).                                                                     cycle.
New post-replacement              Up to 525 work-     Manufacturer has    $44,625...........  Up to $1,115,625.
 inspections--section 41.          hours x $85 per     not provided cost
                                   hour =              of parts.
                                   $44,625.\1\
New inspections, replacement,     Up to 525 work-     Manufacturer has    $44,625...........  Up to $1,115,625.
 and post-replacement              hours x $85 per     not provided cost
 inspections--section 42.          hour =              of parts.
                                   $44,625.\1\
----------------------------------------------------------------------------------------------------------------
\1\ Includes time to manufacture parts.

    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.

[[Page 30489]]

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. Amend Sec.  39.13 by removing Airworthiness Directive (AD) 2010-03-
05, Amendment 39-16188 (75 FR 5692, February 4, 2010), and adding the 
following new AD:

The Boeing Company: Docket No. FAA-2014-0283; Directorate Identifier 
2012-NM-183-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by July 14, 
2014.

(b) Affected ADs

    This AD supersedes AD 2010-03-05, Amendment 39-16188 (75 FR 
5692, February 4, 2010).

(c) Applicability

    This AD applies to all The Boeing Company Model 747-200C and -
200F series airplanes, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an evaluation done by the design 
approval holder (DAH) indicating that the upper deck floor beams are 
not adequate to ensure structural integrity and are subject to 
widespread fatigue damage (WFD). Inspections and modifications were 
developed to support the airplane's limit of validity (LOV) of the 
engineering data that support the established structural maintenance 
program. We are issuing this AD to detect and correct cracking of 
the upper chords and straps (or angles) of the floor beams, which 
could lead to failure of the floor beams and consequent loss of 
controllability, 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) Inspection and Replacement for Section 41 Upper Deck Floor Beam 
Upper Chords

    At the applicable time specified in Table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2696, 
Revision 1, dated April 12, 2012: At stations (STA) 340 through STA 
440, STA 500, and STA 520, do an open-hole HFEC inspection at all 
accessed fastener holes to detect cracking; and install new upper 
deck floor beam upper chords, straps, angles, and radius fillers, in 
accordance with Part 2 and Part 3 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-53A2696, Revision 1, dated 
April 12, 2012.

(h) Post-Replacement Inspections and Replacements for Section 41 Upper 
Deck Floor Beam Upper Chords

    At the applicable time specified in Table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2696, 
Revision 1, dated April 12, 2012; or within 1,500 flight cycles 
after March 11, 2010 (the effective date of AD 2010-03-05, Amendment 
39-16188 (75 FR 5692, February 4, 2010)); whichever occurs later: Do 
detailed and HFEC inspections to detect cracking of the replaced 
upper deck floor beam chords, the floor panel attachment holes, and 
the permanent fastener locations of the replaced upper deck floor 
beam chords, in accordance with Part 4 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2696, Revision 
1, dated April 12, 2012. If no crack is found, do the actions 
specified in paragraphs (h)(1) and (h)(2) of this AD.
    (1) Do the detailed and HFEC inspections of the replaced upper 
deck floor beam chords within 3,000 flight cycles after the most 
recent inspection, or within 300 flight cycles after the effective 
date of this AD, whichever occurs later, and repeat thereafter at 
the applicable time specified in Table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2696, 
Revision 1, dated April 12, 2012.
    (2) Do the open-hole HFEC inspection and chord replacement 
required by paragraph (g) of this AD at the applicable time 
specified in Table 2 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2696, Revision 1, dated April 12, 
2012, or within 240 flight cycles after the effective date of this 
AD, whichever occurs later. Repeat the inspections and replacement 
specified in paragraph (h) of this AD at the applicable time 
specified in Table 2 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2696, Revision 1, dated April 12, 
2012.

(i) Inspection and Replacement for Section 42 Upper Deck Floor Beam 
Upper Chords

    At the applicable time specified in Tables 3 and 4 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2696, 
Revision 1, dated April 12, 2012, except as required by paragraph 
(l) of this AD: Do the actions specified in paragraph (i)(1) or 
(i)(2) of this AD as applicable.
    (1) At STA 540 through STA 740 for Group 1 airplanes identified 
in Boeing Alert Service Bulletin 747-53A2696, Revision 1, dated 
April 12, 2012: Do an open-hole HFEC inspection to detect cracking, 
and install new upper deck floor beam upper chord replacements, in 
accordance with Part 7 and Part 8 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-53A2696, Revision 1, dated 
April 12, 2012.
    (2) At STA 540 through STA 780 for Group 2 airplanes identified 
in Boeing Alert Service Bulletin 747-53A2696, Revision 1, dated 
April 12, 2012: Do an open-hole HFEC inspection to detect cracking, 
and install new upper deck floor beam upper chord replacements, in 
accordance with Part 7 and Part 8 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-53A2696, Revision 1, dated 
April 12, 2012.

(j) Post-Replacement Inspections and Replacement for Section 42 Upper 
Deck Floor Beam Upper Chords

    At the applicable time specified in Table 5 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2696, 
Revision 1, dated April 12, 2012; or within 1,500 flight cycles 
after March 11, 2010 (the effective date of AD 2010-03-05, Amendment 
39-16188 (75 FR 5692, February 4, 2010)); whichever occurs later: Do 
HFEC inspections to detect cracking of the replaced upper deck floor 
beam chords, in accordance with Part 9 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2696, Revision 
1, dated April 12, 2012. If no crack is found, do the actions 
specified in paragraphs (j)(1) and (j)(2) of this AD.
    (1) Repeat the HFEC inspections of the replaced upper deck floor 
beam chords thereafter at the applicable time specified Table 5 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2696, Revision 1, dated April 12, 2012.
    (2) Do the open-hole HFEC inspection and chord replacement 
required by paragraph (i) of this AD at the applicable time 
specified in Table 5 of paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2696, Revision 1, dated April 12, 
2012. Repeat the inspections and replacement, as specified in 
paragraph (j) of this AD, at the applicable

[[Page 30490]]

time specified in Table 5 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2696, Revision 1, dated April 
12, 2012.

(k) Corrective Actions

    If any cracking is found during any inspection required by this 
AD, before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD.

(l) Exception to Service Information Specifications

    Where Boeing Alert Service Bulletin 747-53A2696, Revision 1, 
dated April 12, 2012, specifies a compliance time ``after the 
revision 1 date on this service bulletin,'' this AD requires 
compliance within the specified compliance time ``after the 
effective date of this AD.''

(m) Credit for Previous Actions

    This paragraph provides credit for the installation of floor 
beam replacements required by this AD, if those actions were 
performed before the effective date of this AD using Boeing Alert 
Service Bulletin 747-53A2696, dated October 16, 2008.

(n) Special Flight Permit

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(o) 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 persons identified in paragraphs (o)(1) and (o)(2) 
of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-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, 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.

(p) Related Information

    (1) For more information about this AD, contact Roger Caldwell, 
Aerospace Engineer, Technical Operations Center, ANM-100D, FAA, 
Denver Aircraft Certification Office, 26805 East 68th Avenue, Room 
214, Denver, CO 80249; phone: 303-342-1086; fax: 303-342-1088; 
email: roger.caldwell@faa.gov.
    (2) For information about AMOCs, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6432; fax: 425-917-6590; email: 
bill.ashforth@faa.gov.
    (3) 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 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 May 15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-12260 Filed 5-27-14; 8:45 am]
BILLING CODE 4910-13-P