
[Federal Register Volume 79, Number 218 (Wednesday, November 12, 2014)]
[Rules and Regulations]
[Pages 67044-67047]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-26434]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0836; Directorate Identifier 2013-NM-126-AD; 
Amendment 39-18011; AD 2014-22-06]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2005-07-12, 
which applies to certain the Boeing Company Model 737-100, -200, -200C, 
-300, -400, and -500 series airplanes. AD 2005-07-12 required detailed 
and eddy current inspections to detect cracking of the frame web around 
the cutout for the doorstop intercostal strap at the aft side of the 
station (STA) 291.5 frame at stringer 16R, and corrective action if 
necessary. Since we issued AD 2005-07-12, we received reports of new 
findings of cracking at various locations of the STA 277 to STA 291.5 
frames and intercostals, including webs, chords, clips, and shear ties, 
between stringers 7R and 17R. This new AD requires inspections for 
cracking at the forward galley door cutout, and corrective actions if 
necessary. This new AD also reduces a certain inspection threshold 
required by AD 2005-07-12. We are issuing this AD to detect and correct 
fatigue cracking of the aft frame and frame support structure of the 
forward galley door, which could result in a severed fuselage frame 
web, rapid decompression of the airplane, and possible loss of the 
forward galley door.

DATES: This AD is effective December 17, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 17, 
2014.

ADDRESSES: 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 copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind Ave. 
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-2013-
0836; 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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2005-07-12, Amendment 39-14036 (70 FR 17596, 
April 7, 2005). AD 2005-07-12 applied to certain The Boeing Company 
Model 737-100, -200, -300, -400, and -500 series airplanes. The NPRM 
published in the Federal Register on October 2, 2013 (78 FR 60804). The 
NPRM was prompted by reports of new findings of cracking at various 
locations of the STA 277 to STA 291.5 frames and intercostals, 
including webs, chords, clips, and shear ties, between stringers 7R and 
17R. The NPRM proposed to continue to require detailed and eddy current 
inspections to detect cracking of the frame web around the cutout for 
the doorstop intercostal strap at the aft side of the STA 291.5 frame 
at stringer 16R, and corrective action if necessary. The NPRM also 
proposed to require new inspections for cracking at the forward galley 
door cutout, and corrective actions if necessary. In addition, the NPRM 
also proposed to reduce a certain inspection threshold required by AD 
2005-07-12. We are issuing this AD to

[[Page 67045]]

detect and correct fatigue cracking of the aft frame and frame support 
structure of the forward galley door, which could result in a severed 
fuselage frame web, rapid decompression of the airplane, and possible 
loss of the forward galley door.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (78 
FR 60804, October 2, 2013), and the FAA's response to each comment.
    Boeing stated that it concurs with the contents of the NPRM (78 FR 
60804, October 2, 2013).

Effect of Winglets on AD

    Aviation Partners Boeing stated that accomplishing the installation 
of winglets per supplemental type certificate (STC) ST01219SE (http://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
082838ee177dbf62862576a4005cdfc0/$FILE/ST01219SE.pdf) does not affect 
the actions specified in the NPRM (78 FR 60804, October 2, 2013).
    We concur with the commenter. We have redesignated paragraph (c) of 
the NPRM (78 FR 60804, October 2, 2013) as (c)(1) in this AD and added 
new paragraph (c)(2) to this AD to state that installation of STC 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/082838ee177dbf62862576a4005cdfc0/$FILE/ST01219SE.pdf) does 
not affect the ability to accomplish the actions required by this final 
rule. Therefore, for airplanes on which STC ST01219SE is installed, a 
``change in product'' alternative method of compliance (AMOC) approval 
request is not necessary to comply with the requirements of 14 CFR 
39.17.

Request To Clarify That Certain Inspections Are Not Required for Areas 
With Existing Repairs

    Southwest Airlines (SWA) requested that paragraph (h)(1) of the 
NPRM (78 FR 60804, October 2, 2013), be revised to include language 
stating that when operators are accomplishing Steps 2 and 6 in Part 2 
of Paragraph 3.B., ``Work Instructions,'' of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, 
dated June 11, 2013, they do not need to do inspections in areas that 
are common to repairs that were previously approved by Boeing via FAA 
Form 8100-9, ``Statement of Compliance with Airworthiness Standards.'' 
We infer that the basis for SWA's request is that the existing repairs 
have inspections included in the engineering for those repairs, so the 
inspections included in the service information are not needed.
    SWA also requested that the NPRM (78 FR 60804, October 2, 2013), be 
revised to clarify that inspections are not required in areas that are 
common to existing repairs that were installed using a certain repair 
in the applicable Boeing Model 737 structural repair manual (SRM). SWA 
noted that Step 6 in Part 2 of Paragraph 3.B., ``Work Instructions,'' 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1241, Revision 1, dated June 11, 2013, only addresses repetitive 
inspections when a new SRM repair is installed. We infer that SWA is 
suggesting that the service information should have also addressed 
repetitive inspections for areas with a certain existing SRM repair 
installed.
    We agree with the commenter. The inspections required by paragraph 
(h)(1) of this AD include detailed and surface eddy current inspections 
that cannot be accomplished with certain repairs installed. Repairs 1, 
15, and 16, of Chapter 53 of the applicable Boeing 737 SRM, are 
referenced in the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-53A1241, Revision 1, dated June 11, 2013, and are 
considered corrective actions for cracking found during the inspections 
required by paragraph (h)(1) of this AD. These SRM repairs can also be 
used as a preventive modification.
    We revised paragraph (h)(1) in this AD to state that 
``Accomplishment of a repair specified in Steps 1.a., 2.a., 6.a., or 
6.b. of Part 2 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, as 
applicable, and except as required by paragraph (k)(1) of this AD, 
terminates the inspections required by this paragraph for the repaired 
area(s) only.''

Request To Address Notes 11 and 13 in the Service Information Regarding 
Existing Repairs and Existing Repairs at Certain Body Stations

    SWA requested clarification regarding existing repairs common to 
the inspection areas addressed in Part 2 of Paragraph 3.B., ``Work 
Instructions,'' of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013. SWA 
observed that Notes 11 and 13 in Paragraph 3.A., ``General 
Information,'' of that service bulletin include provisions for omitting 
inspections in areas covered by repairs that were previously approved 
by Boeing via FAA Form 8100-9, ``Statement of Compliance with 
Airworthiness Standards,'' but those notes are not included or 
referenced in Part 2 of Paragraph 3.B., ``Work Instructions.''
    SWA also requested approval for existing repairs common to the body 
station (BS) 291.5 frame at locations from stringer (STR) 8R to STR 15R 
that were previously approved by Boeing via FAA Form 8100-9, 
``Statement of Compliance with Airworthiness Standards,'' as 
terminating action for the inspection requirements in paragraph (h)(1) 
of the NPRM (78 FR 60804, October 2, 2013), for the repaired area only.
    Furthermore, SWA requested approval for existing repairs common to 
the BS 277 frame and shear ties between STR 7R and STR 17R that were 
previously approved by Boeing via FAA Form 8100-9, ``Statement of 
Compliance with Airworthiness Standards,'' or that were installed using 
certain repairs in the applicable Boeing 737 SRM as terminating action 
for the inspection requirements of paragraph (h)(1) of the NPRM (78 FR 
60804, October 2, 2013), for the repaired areas only.
    We agree that the existing repairs mentioned by the commenter can 
be used as terminating action for the inspection requirements of 
paragraph (h)(1) of this AD. Several SRM repairs are referenced in 
Steps 6.a. and 6.b. of Part 2 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 
2013, and are considered corrective actions for cracking found during 
the inspections required by paragraph (h)(1) of this AD. The notes to 
Steps 6.a. and 6.b. state that the SRM repairs terminate the repetitive 
inspections. As stated previously, paragraph (h)(1) of this AD was 
revised accordingly.
    We have also added a new paragraph (i), Terminating Action, to this 
AD and redesignated subsequent paragraphs accordingly. Paragraph (i) of 
this AD states ``The inspections required by paragraph (h)(1) of this 
AD may be terminated at areas with repairs installed prior to the 
effective date of this AD, provided the repairs meet the conditions 
specified in note 11 or note 13 of paragraph 3.A., ``General 
Information,'' of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013.''

Request To Include Exception to the Service Information Specifications

    SWA requested that the NPRM (78 FR 60804, October 2, 2013) address 
a typographical error that appears in the

[[Page 67046]]

title to figure 5 of Boeing Alert Service Bulletin 737-53A1241, 
Revision 1, dated June 11, 2013. SWA noted that the title refers to STR 
16R, however, the inspection location is STR 14R.
    We agree to address this typographical error in Boeing Alert 
Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, and have 
added a new paragraph (k)(3) to this AD to notify operators that the 
title to figure 5 should reference STR 14R.

Clarification of Affected Airplanes

    We have added ``certificated in any category'' to the applicability 
specified in paragraph (c)(1) of this AD to clarify the affected 
airplanes.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 60804, October 2, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 60804, October 2, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 419 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                  Labor cost           Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained from AD    2 work-hours x $85  None...............  $170 per            $71,230 per
 2005-07-12, Amendment 39 14036   per hour = $170                          inspection cycle.   inspection cycle.
 (70 FR 17596, April 7, 2005)].   per inspection
                                  cycle.
Inspections [new proposed        40 work-hours x     None...............  $3,400 per          $1,424,600 per
 action].                         $85 per hour =                           inspection cycle.   inspection cycle.
                                  $3,400 per
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in the service 
information.

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 have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in, 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 removing Airworthiness Directive (AD) 
2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005), and adding 
the following new AD:

2014-22-06 The Boeing Company: Amendment 39-18011 ; Docket No. FAA-
2013-0836; Directorate Identifier 2013-NM-126-AD.

(a) Effective Date

    This AD is effective December 17, 2014.

(b) Affected ADs

    This AD replaces AD 2005-07-12, Amendment 39-14036 (70 FR 17596, 
April 7, 2005).

(c) Applicability

    (1) 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 Alert Service Bulletin 737-
53A1241, Revision 1, dated June 11, 2013.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/082838ee177dbf62862576a4005cdfc0/$FILE/ST01219SE.pdf) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01219SE is 
installed, a ``change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of new findings of cracking at 
various locations of the stations (STA) 277 to STA 291.5 frames and 
intercostals, including webs, chords, clips, and shear ties, between 
stringers 7R and 17R. We are issuing this AD to detect

[[Page 67047]]

and correct fatigue cracking of the aft frame and frame support 
structure of the forward galley door, which could result in a 
severed fuselage frame web, rapid decompression of the airplane, and 
possible loss of the forward galley door.

(f) Compliance

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

(g) Group 1 Airplanes: Inspections and Corrective Actions

    For airplanes identified as Group 1 in Boeing Alert Service 
Bulletin 737-53A1241, Revision 1, dated June 11, 2013: Within 120 
days after the effective date of this AD, do inspections for 
cracking from STA 277 to STA 328, stringer 7R to 17R of the forward 
galley door cutout, using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD. Do all applicable 
corrective actions before further flight using a method approved in 
accordance with the procedures specified in paragraph (m) of this 
AD.

(h) Group 2 and Group 3 Airplanes: Inspections and Corrective Actions

    (1) For airplanes identified as Group 2 and Group 3 in Boeing 
Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013: 
Except as provided by paragraph (k)(2) of this AD, at the applicable 
times specified in tables 1 and 2 in paragraph 1.E, ``Compliance,'' 
of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 
11, 2013, do detailed and surface high frequency eddy current (HFEC) 
inspections, as applicable, for cracking in the forward galley door 
cutout, in accordance with Part 2 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 
11, 2013. Repeat the detailed and surface HFEC inspections 
thereafter at the applicable intervals specified in tables 1 and 2 
in paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1241, Revision 1, dated June 11, 2013. If any crack is found, 
before further flight, do all applicable corrective actions in 
accordance with Part 2 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, 
except as required by paragraph (k)(1) of this AD. Accomplishment of 
a repair specified in Steps 1.a., 2.a., 6.a., or 6.b. of Part 2, of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1241, Revision 1, dated June 11, 2013, as applicable, and 
except as required by paragraph (k)(1) of this AD, terminates the 
inspections required by this paragraph for the repaired area(s) 
only.
    (2) Removal and replacement of a cracked part, in accordance 
with Part 2 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, does 
not terminate the repetitive inspections required by paragraph 
(h)(1) of this AD.

(i) Terminating Action

    The inspections required by paragraph (h)(1) of this AD may be 
terminated at areas with repairs installed prior to the effective 
date of this AD, provided the repairs meet the conditions specified 
in note 11 or note 13 of paragraph 3.A., ``General Information,'' of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1241, Revision 1, dated June 11, 2013.

(j) Optional Terminating Action

    Accomplishment of the preventive modification on the STA 291.5 
frame web, in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 
1, dated June 11, 2013, terminates the inspections required by 
paragraph (h)(1) of this AD for the area that is common to the 
preventive modification.

 (k) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 737-53A1241, Revision 1, 
dated June 11, 2013, specifies to contact Boeing for a corrective 
action: Before further flight, do the applicable action using a 
method approved in accordance with the procedures specified in 
paragraph (m) of this AD.
    (2) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, 
specifies a compliance time ``after the date on Revision 1 of this 
service bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (3) The title to each page of figure 5 of Boeing Alert Service 
Bulletin 737-53A1241, Revision 1, dated June 11, 2013, is incorrect 
and refers to ``Stringer 16R'' when it should refer to ``Stringer 
14R.''

(l) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (h)(1) of this AD, if those actions were performed before 
the effective date of this AD using Boeing Alert Service Bulletin 
737-53A1241, dated June 13, 2002, which is not incorporated by 
reference in this AD.

(m) 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 (n)(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.
    (4) AMOCs approved for the actions specified in AD 2005-07-12, 
Amendment 39-14036 (70 FR 17596, April 7, 2005), are approved as 
AMOCs for the corresponding provisions of this AD.

(n) 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated 
June 11, 2013. (ii) Reserved.
    (3) For Boeing 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.
    (4) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Ave. SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-26434 Filed 11-10-14; 8:45 am]
BILLING CODE 4910-13-P


