
[Federal Register Volume 79, Number 84 (Thursday, May 1, 2014)]
[Proposed Rules]
[Pages 24628-24631]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-09941]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0257; Directorate Identifier 2014-NM-012-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 737-100, -200, -200C, -300, -400, and 
-500 series airplanes. This proposed AD was prompted by reports of 
fatigue cracking in certain areas. This proposed AD would require 
repetitive inspections for cracking of the skin assembly and bear strap 
of the forward airstair stowage doorway; post-repair and post-
modification inspections for certain airplanes; and related 
investigative and corrective actions, if necessary. This proposed AD 
would also provide optional terminating actions for certain repetitive 
inspections. We are proposing this AD to detect and correct fatigue 
cracking, which could result in rapid loss of cabin pressure.

DATES: We must receive comments on this proposed AD by June 16, 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, 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 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-
0257; 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: Alan Pohl, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-6450; 
fax: (425) 917-6590; email: alan.pohl@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-2014-0257; 
Directorate Identifier 2014-NM-012-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 fatigue cracking in the skin assembly and 
bear strap at the aft lower corner of the forward airstair stowage 
doorway. The cracking was caused by fatigue from cyclic pressurization 
loading. At the time of crack detection, the airplanes had accumulated 
between 16,177 and 74,036 total flight cycles. This condition, if not 
corrected, could result in rapid loss of cabin pressure.

Related Rulemaking

    AD 90-06-02, Amendment 39-6489 (Docket No. 89-NM-67-AD; 55 FR 8372, 
March 7, 1990), mandates certain structural modifications for Model 
737-100, -200, -200C series airplanes. AD 98-11-04 R1, Amendment 39-
10984 (64 FR 987, January 7, 1999); AD 2008-08-23, Amendment 39-15477 
(73 FR 21237, April 21, 2008); and AD 2008-09-13, Amendment 39-15494 
(73 FR 24164, May 2, 2008); are supplemental structural inspection 
(SSI) program ADs that contain inspection requirements that are near or 
overlap the inspection areas that this proposed AD would require. The 
modification mandated by AD 90-06-02 and the inspections mandated by 
the exploratory SSI program ADs are not sufficient to address the 
unsafe condition identified in this proposed AD.

Relevant Service Information

    We reviewed Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2014-0257.

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 this Proposed AD and the Service 
Information.'' This proposed AD would also provide optional terminating 
actions for certain repetitive inspections.
    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

[[Page 24629]]

actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    The service information 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 132 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.....................  5 work-hours x $85 per   None............  $425 per           $56,100 per
                                  hour = $425 per                            inspection cycle.  inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for any on-condition actions specified in this proposed 
AD. We have no way of determining the number of aircraft that might 
need this repair.

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-2014-0257; Directorate Identifier 
2014-NM-012-AD.

(a) Comments Due Date

    We must receive comments by June 16, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category, as identified in Boeing Service Bulletin 737-53-1058, 
Revision 4, dated January 9, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of fatigue cracking in the skin 
assembly and bear strap of the aft lower corner of the forward 
airstair stowage doorway. We are issuing this AD to detect and 
correct fatigue cracking, which could result in rapid loss of cabin 
pressure.

(f) Compliance

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

(g) Inspections and Corrective Actions for Group 1 and Group 2 
Airplanes That Do Not Have a Certain Repair or Preventative 
Modification Installed

    For Group 1 and Group 2 airplanes identified in Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, on which no 
repair or preventative modification has been done as specified in 
any of the service information identified in paragraphs (g)(1) 
through (g)(4) of this AD: At the applicable times specified in 
Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as 
required by paragraph (o)(1) of this AD, do high frequency eddy 
current and detailed inspections for cracking of the skin assembly 
and bear strap of the forward airstair stowage doorway, and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as 
required by paragraph (o)(2) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspections at the applicable times specified in Table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-53-
1058, Revision 4, dated January 9, 2014, until the applicable 
terminating action specified in paragraph (m) of this AD is done.
    (1) Boeing Service Bulletin 737-53-1058, dated April 4, 1980.
    (2) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.
    (3) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (4) Boeing Service Bulletin 737-53-1058, Revision 3, dated March 
11, 1993.

[[Page 24630]]

(h) Inspections and Corrective Actions for Group 1 and Group 2 
Airplanes That Have a Certain Repair Installed

    For Group 1 and Group 2 airplanes identified in Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, on which a 
repair has been installed as specified in Boeing Service Bulletin 
737-53-1058, dated April 4, 1980: Within the applicable times 
specified in Table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014, 
except as required by paragraph (o)(1) of this AD, do a high 
frequency eddy current inspection for cracking of the bear strap of 
the forward airstair stowage doorway, and do low frequency eddy 
current and detailed inspections for cracking of the skin assembly 
and bear strap of the forward airstair stowage doorway; and do all 
applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as 
required by paragraph (o)(2) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspections at the applicable times specified in Table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-53-
1058, Revision 4, dated January 9, 2014, until the applicable 
terminating action specified in paragraph (m) of this AD is done.

(i) Inspections and Corrective Actions for Group 1 and Group 2 
Airplanes That Have a Certain Preventative Modification Installed

    For Group 1 and Group 2 airplanes identified in Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, on which a 
preventative modification has been installed as specified in any of 
the service information identified in paragraphs (i)(1) through 
(i)(4) of this AD: Within the applicable times specified in Table 1 
of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-
53-1058, Revision 4, dated January 9, 2014, except as required by 
paragraph (o)(1) of this AD, do a high frequency eddy current 
inspection for cracking of the bear strap of the forward airstair 
stowage doorway, a low frequency eddy current inspection for 
cracking of the skin assembly and bear strap of the forward airstair 
stowage doorway, and detailed inspections for cracking of the skin 
assembly and bear strap of the forward airstair stowage doorway; and 
do all related investigative and applicable corrective actions; in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as 
required by paragraph (o)(2) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspections at the applicable times specified in Table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-53-
1058, Revision 4, dated January 9, 2014, until the applicable 
terminating action specified in paragraph (m) of this AD is done.
    (1) Boeing Service Bulletin 737-53-1058, dated April 4, 1980.
    (2) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.
    (3) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (4) Boeing Service Bulletin 737-53-1058, Revision 3, dated March 
11, 1993.

(j) Inspections and Corrective Actions for Group 3 Through Group 5 
Airplanes

    For Group 3 through Group 5 airplanes identified in Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014: At 
the applicable times specified in Table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 2014, except as required by paragraph (o)(1) of 
this AD, do a high frequency eddy current inspection for cracking of 
the bear strap of the forward airstair stowage doorway, a low 
frequency eddy current inspection for cracking of the skin assembly 
and bear strap of the forward airstair stowage doorway, and detailed 
inspections for cracking of the skin assembly and bear strap of the 
forward airstair stowage doorway; and do all related investigative 
and applicable corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 737-53-1058, 
Revision 4, dated January 9, 2014, except as required by paragraph 
(o)(2) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspections at 
the applicable times specified in Table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 2014, until the applicable terminating action 
specified in paragraph (m) of this AD is done.

(k) Inspections and Corrective Actions for Group 6 Airplanes

    For Group 6 airplanes identified in Boeing Service Bulletin 737-
53-1058, Revision 4, dated January 9, 2014: Within 120 days after 
the effective date of this AD, inspect and repair any cracking using 
a method approved in accordance with the procedures specified in 
paragraph (q) of this AD.

(l) Post-Repair and Post-Modification Inspections for Group 1 and Group 
2 Airplanes

    For Group 1 and Group 2 airplanes on which any repair has been 
done as specified in any of the service information identified in 
paragraphs (l)(1) through (l)(3) of this AD, or on which any repair 
or modification has been done as specified in the service 
information identified in paragraph (l)(4) of this AD: At the 
applicable times specified in Table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 2014, except as required by paragraph (o)(1) of 
this AD, do a high frequency eddy current inspection for cracking in 
the bear strap and skin assembly and a general visual inspection for 
cracking in the frame of the forward airstair stowage doorway; or do 
low frequency eddy current inspections for cracking of the skin 
assembly and bear strap of the forward airstair stowage doorway; in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014. Options 
provided in Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014, for accomplishing the inspections are acceptable 
for compliance with the corresponding requirements of this paragraph 
provided that the inspections are done at the applicable times in 
paragraph 1.E., ``Compliance,'' of the Boeing Service Bulletin 737-
53-1058, Revision 4, dated January 9, 2014. If any cracking is 
found, before further flight, repair the cracking using a method 
approved in accordance with the procedures specified in paragraph 
(q) of this AD. Repeat the inspections at the applicable times 
specified in Table 3 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014.
    (1) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.
    (2) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (3) Boeing Service Bulletin 737-53-1058, Revision 3, dated March 
11, 1993.
    (4) Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014.

(m) Optional Terminating Actions

    (1) For Group 1 and Group 2 airplanes identified in Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014: 
Accomplishment of a repair for cracking of the skin assembly and 
bear strap of the forward airstair stowage doorway before the 
effective date of this AD, using any service information specified 
in paragraphs (m)(1)(i) through (m)(1)(iv) of this AD, terminates 
the repetitive inspections required by paragraphs (g), (h), and (i) 
of this AD.
    (i) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.
    (ii) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (iii) Boeing Service Bulletin 737-53-1058, Revision 3, dated 
March 11, 1993.
    (iv) Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014.
    (2) For Group 1 and Group 2 airplanes identified in Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014: 
Accomplishment of a preventative modification for cracking of the 
skin assembly and bear strap of the forward airstair stowage doorway 
before the effective date of this AD, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 737-53-1058, 
Revision 4, dated January 9, 2014, terminates the repetitive 
inspections required by paragraphs (g), (h), and (i) of this AD.
    (3) For Group 3 through Group 5 airplanes identified in Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014: 
Repairing or modifying the forward airstair stowage doorway, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, terminates 
the repetitive inspections required by paragraph (j) of this AD.

(n) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before the effective date of this AD using any service 
information specified in paragraphs (n)(i) through (n)(iii) of this 
AD.
    (i) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.

[[Page 24631]]

    (ii) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (iii) Boeing Service Bulletin 737-53-1058, Revision 3, dated 
March 11, 1993.

(o) Exceptions to the Service Information

    (1) Where Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014, specifies a compliance time ``after the Revision 4 
date of this service bulletin,'' this AD requires compliance within 
the specified compliance time ``after the effective date of this 
AD.''
    (2) Where Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014, specifies to contact Boeing for repair 
instructions: Before further flight, repair using a method approved 
in accordance with the procedures specified in paragraph (q) of this 
AD.

(p) Post-Repair and Post-Modification Inspections for Group 3 Through 
Group 5 Airplanes Not Required

    The post-repair and post-modification inspections specified in 
Table 4 of paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, are not 
required by this AD.

    Note 1 to paragraph (p) of this AD: The post-repair and post-
modification inspections specified in Table 4 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 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)).

(q) 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 (r)(1) 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.

(r) Related Information

    (1) For more information about this AD, contact Alan Pohl, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: (425) 917-6450; fax: (425) 917-6590; email: 
alan.pohl@faa.gov.
    (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 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 25, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-09941 Filed 4-30-14; 8:45 am]
BILLING CODE 4910-13-P


