[Federal Register Volume 78, Number 90 (Thursday, May 9, 2013)]
[Rules and Regulations]
[Pages 27001-27005]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-10005]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1161; Directorate Identifier 2011-NM-277-AD; 
Amendment 39-17442; AD 2013-09-01]
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 an existing airworthiness directive (AD) 
for certain The Boeing Company Model 737-200, -200C, -300, -400, and -
500 series airplanes. That AD currently requires a one-time mid-
frequency eddy current (MFEC) inspection, a low-frequency eddy current 
(LFEC) inspection, and a detailed inspection for damage or cracking of 
stringer S-4L and S-4R lap joints and stringer clips between body 
station (BS) 540 and BS 727, and follow-on inspections and repair if 
necessary. This new AD instead requires repetitive external eddy 
current inspections for cracking of certain fuselage crown lap joints, 
and corrective actions if necessary; internal eddy current and detailed 
inspections for cracking of certain fuselage crown lap joints, and 
repair if necessary; and detailed inspections of certain stringer 
clips, and replacement with new stringer clips if necessary. This AD 
also adds airplanes to the applicability. This AD was prompted by 
reports of cracking of the lap joint lower row. We are issuing this AD 
to detect and correct cracking of the fuselage lap joints, which could 
result in sudden decompression of the airplane.

DATES: This AD is effective June 13, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publication listed in the AD as of June 13, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of May 
17, 2002 (67 FR 17917, April 12, 2002).

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data

[[Page 27002]]

& Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document 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: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; fax: 
425-917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2003-08-15, Amendment 39-13128 (68 FR 20341, 
April 25, 2003). That AD applies to the specified products. The NPRM 
published in the Federal Register on November 7, 2012 (77 FR 66757). 
That NPRM proposed to require repetitive external eddy current 
inspections for cracking of certain fuselage crown lap joints and 
corrective actions; internal eddy current and detailed inspections for 
cracking of certain fuselage crown lap joints, and repair if necessary; 
and detailed inspections of certain stringer clips, and replacement 
with new stringer clips if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 66757, November 7, 2012) and the FAA's response to each comment.

Support of NPRM (77 FR 66757, November 7, 2012)

    Ann Harrison stated that she supports the NPRM (77 FR 66757, 
November 7, 2012).

Request for Clarification of Inspection Requirements

    Boeing and Lufthansa requested clarification that the repetitive 
inspections referred to in paragraph (i)(3) of the NPRM (77 FR 66757, 
November 7, 2012) are external inspections. The commenters noted that 
the internal inspection specified in Boeing Alert Service Bulletin 737-
53A1255, Revision 2, dated August 7, 2012, is a one-time inspection. 
Lufthansa suggested we delete paragraph (i)(3) from the NPRM. Boeing 
suggested we revise paragraph (i)(3) of the NPRM to state that the 
repetitive inspection is external.
    We agree that clarification is needed. The internal inspection is 
required only once prior to the accomplishment of the lap splice 
modification. Since the external inspection specified in paragraph (g) 
of this AD is repetitive, we have deleted paragraph (i)(3) of this AD.

Request To Use Previous Alternative Methods of Compliance (AMOCs)

    Alaska Airlines requested that we change the NPRM (77 FR 66757, 
November 7, 2012) to state that ``AMOCs approved previously in 
accordance with AD 2003-08-15 [(68 FR 20341, April 25, 2003)] and AD 
2004-18-06 [(69 FR 54206, September 8, 2004)] are approved as AMOCs for 
the corresponding provisions of this AD.'' Alaska Airlines stated that 
there is a global AMOC for the PEMCO main deck cargo door installation 
in accordance with supplemental type certificate (STC) SA2969SO (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2A10F5D4090A534686257A79006F0F97?OpenDocument&Highlight=stcsa2969so). 
The commenter stated that since the STC is not a repair, this global 
AMOC should be specified in paragraph (n) of the NPRM.
    We agree with the request to include in the AD previously approved 
AMOCs for the corresponding requirements of this AD. Installation of 
the PEMCO main deck cargo door done in accordance with STC SA2969SO 
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2A10F5D4090A534686257A79006F0F97?OpenDocument&Highlight=stcsa2969so) 
involves installation of an external doubler onto the existing skin and 
lap splices from stringer S-3R to S-23L between body station (BS) 312 
and BS 500B. We have added new paragraph (n)(6) to this AD to state 
that installation of STC SA2969SO is approved as an AMOC to the 
corresponding requirements of paragraphs (g) and (i) of this AD from 
stringer S-3R to S-23L between BS 312 and BS 500B only.
    Boeing requested that we revise paragraph (n)(4) of the NPRM (77 FR 
66757, November 7, 2012) to add references to paragraphs (g) and (h) of 
AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002), in 
order to provide approval for lap joint modifications that have been 
approved as AMOCs to paragraphs (g) and (h) of AD 2002-07-08.
    We agree with the request. Lap joints modified prior to the 
effective date of this AD that have been approved as an AMOC for 
paragraphs (g) and (h) of AD 2002-07-08, Amendment 39-12702 (67 FR 
17917, April 12, 2002), should not be subject to the lap joint 
inspections required by this AD. We have added references to paragraphs 
(g) and (h) of AD 2002-07-08 to paragraph (n)(4) of this AD.

STC Winglet Comment

    Aviation Partners Boeing stated that the installation of winglets 
per STC ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) does 
not affect the accomplishment of the manufacturer's service 
instructions.
    We have added paragraph (c)(2) to this AD to state that 
installation of STC ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) 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'' AMOC approval request is not necessary to comply 
with the requirements of 14 CFR 39.17. For all other AMOC requests, the 
operator must request approval for an AMOC in accordance with the 
procedures specified in paragraph (n) of this AD.

Request To Clarify Locations of Optional Internal Inspections

    Boeing requested that we include further clarification in paragraph 
(h) of the NPRM (77 FR 66757, November 7, 2012) indicating that the 
optional internal inspections are for cracks between tear straps only. 
Boeing stated that paragraph (g) of the NPRM inspects for cracking at 
tear strap locations and

[[Page 27003]]

between tear straps. Boeing also stated that paragraph (h) of the NPRM 
provides an optional inspection for the inspections required by 
paragraph (g), but only for cracking between tear straps. Boeing added 
that it is important to clarify that the inspections required by 
paragraph (h) of the NPRM are only applicable at locations between tear 
straps.
    We agree that the requested wording will further clarify the 
location for the optional internal inspections specified in paragraph 
(h) of this AD. We have added the phrase ``between tear straps'' to the 
beginning of the first sentence of paragraph (h) of this AD.
    Boeing also requested that we clarify paragraph (j) of the NPRM (77 
FR 66757, November 7, 2012) to indicate that the optional internal 
inspections are for cracks at tear strap locations. Boeing added that 
the wording in the NPRM only allows this confirmation when 
accomplishing the internal inspections specified in paragraph (i) of 
the NPRM. Boeing stated that Boeing Alert Service Bulletin 737-53A1255, 
Revision 2, dated August 7, 2012, specifies that this optional 
inspection at tear strap locations is for cracks found during either 
the external inspection specified in paragraph (g) of the NPRM, or the 
internal inspections specified in paragraph (i) of the NPRM.
    We agree that adding a reference to the tear strap location near 
the beginning of the first sentence of paragraph (j) of this AD will 
clarify the requirement. We have revised paragraph (j) of this AD 
accordingly. We have also added a reference to paragraph (g) of this 
AD, as requested by the commenter.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the 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 (77 FR 66757, November 7, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 66757, November 7, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 307 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                             Cost per        Number of     Cost on U.S.
                     Action                                     Labor cost                  Parts cost        product        airplanes       operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Internal inspection............................  Up to 303 work-hours x $85 per hour =                $0         $25,755             307      $7,906,785
                                                  $25,755.
External inspection............................  Up to 10 work-hours x $85 per hour =                  0             850             307         260,950
                                                  $850.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

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) 
2003-08-15, Amendment 39-13128 (68 FR 20341, April 25, 2003), and 
adding the following new AD:

2013-09-01 The Boeing Company: Amendment 39-17442; Docket No. FAA-
2012-1161; Directorate Identifier 2011-NM-277-AD.

(a) Effective Date

    This AD is effective June 13, 2013.

(b) Affected ADs

    This AD supersedes AD 2003-08-15, Amendment 39-13128 (68 FR 
20341, April 25, 2003).

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-200, -200C, 
-300, -400, and -500 series airplanes; certificated in any category; 
as specified in Boeing Alert Service Bulletin 737-53A1255, Revision 
2, dated August 7, 2012.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) 
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

[[Page 27004]]

request is not necessary to comply with the requirements of 14 CFR 
39.17.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracking of the lap joint 
lower row. We are issuing this AD to detect and correct cracking of 
the fuselage lap joints, which could result in sudden decompression 
of the airplane.

(f) Compliance

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

(g) External Crown Lap Joint Inspection and Repair

    For airplanes on which the lap splice modification specified in 
AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002), has 
not been accomplished, except as required by paragraphs (l)(1) and 
(l)(2) of this AD: At the applicable times specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1255, 
Revision 2, dated August 7, 2012, do an external eddy current 
inspection for cracking in the crown lap joints, except as provided 
by paragraphs (h) and (j) of this AD, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1255, Revision 2, dated August 7, 2012. At the intervals 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-53A1255, Revision 2, dated August 7, 2012, repeat the 
inspections, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated August 
7, 2012. If any cracking is found in a lap joint, before further 
flight, repair, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated 
August 7, 2012.

(h) Optional Internal Inspections for Mid-bay Fastener Locations

    As an option to confirm cracks found between tear straps during 
the inspections required by paragraph (g) of this AD, do an internal 
mid-frequency eddy current (MFEC) inspection for cracking in the lap 
joint fastener row between tear straps of the crown lap and do a 
detailed inspection of the lap joint lower fastener row for 
cracking, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated August 
7, 2012.

(i) Internal Crown Lap Joint Inspection and Repair

    For airplanes on which the lap splice modification specified in 
AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002), has 
not been accomplished: At the times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1255, 
Revision 2, dated August 7, 2012, except as required by paragraphs 
(l)(1) and (l)(2) of this AD, do an internal MFEC, low frequency 
eddy current (LFEC), and detailed inspection for cracking in the 
crown lap joints and stringer clips, except as provided by paragraph 
(j) of this AD, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated 
August 7, 2012.
    (1) If any cracking is found in any lap joint, before further 
flight, repair, in accordance with the Accomplishment Instructions 
of Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated 
August 7, 2012.
    (2) If any cracking is found in any stringer clip, before 
further flight, replace the stringer clip with a new stringer clip, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1255, Revision 2, dated August 7, 2012.

(j) Optional Inspections for Tear Strap Locations Only

    As an option to confirm cracks found at tear strap locations 
while doing the inspections required by paragraph (g) or (i) of this 
AD, do an open-hole inspection for cracking at the tear strap 
locations, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated August 
7, 2012.

(k) Terminating Action

    (1) Accomplishing a repair of a crown lap joint in accordance 
with Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated 
August 7, 2012, terminates the inspections required by paragraphs 
(g) and (i) of this AD for the repaired area only.
    (2) Accomplishing the modification of the crown lap joints in 
accordance with any of the service bulletins specified in paragraphs 
(k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD terminates the 
inspections required by paragraphs (g) and (i) of this AD for the 
modified area only.
    (i) Boeing Service Bulletin 737-53A1177, Revision 4, dated 
September 2, 1999.
    (ii) Boeing Service Bulletin 737-53A1177, Revision 5, dated 
February 15, 2001.
    (iii) Boeing Service Bulletin 737-53A1177, Revision 6, dated May 
31, 2001.

(l) Exceptions to Service Information

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-53A1255, Revision 2, dated August 7, 2012, 
specifies a compliance time ``from the Revision 1 date of this 
service bulletin,'' this AD requires a compliance time ``after the 
effective date of this AD.''
    (2) Where the ``Condition'' column, in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1255, 
Revision 2, dated August 7, 2012, specifies airplanes with certain 
flight cycles ``at the Revision 1 date of this service bulletin,'' 
for this AD the condition is for airplanes with corresponding flight 
cycles ``as of the effective date of this AD.''

(m) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g), (h), (i), and (j) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Alert 
Service Bulletin 737-53A1255, Revision 1, dated November 7, 2011, 
which is not incorporated by reference in this AD.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved for paragraphs (a), (b), (c), (d), (e), (g), 
and (h) of AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 
2002), before the effective date of this AD, are approved for the 
corresponding requirements of paragraphs (g), (i), and (k) of this 
AD.
    (5) As of the effective date of this AD, any AMOCs approved for 
paragraphs (g) and (i) of this AD are approved as AMOCs for the 
corresponding requirements of paragraphs (a), (b), (c), (d), and (e) 
of AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002).
    (6) As of the effective date of this AD, installation of STC 
SA2969SO (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2A10F5D4090A534686257A79006F0F97?OpenDocument&Highlight=stc 
sa2969so) is approved as an AMOC for the corresponding requirements 
of paragraphs (g) and (i) of this AD from stringer S-3R to S-23L 
between body station (BS) 312 and BS 500B only.

(o) Related Information

    (1) For more information about this AD, contact Wayne Lockett, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6447; fax: 425-917-6590; email: 
[email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference

[[Page 27005]]

(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.
    (3) The following service information was approved for IBR on 
June 13, 2013.
    (i) Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated 
August 7, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
May 17, 2002 (67 FR 17917, April 12, 2002).
    (i) Boeing Service Bulletin 737-53A1177, Revision 4, dated 
September 2, 1999.
    (ii) Boeing Service Bulletin 737-53A1177, Revision 5, dated 
February 15, 2001.
    (iii) Boeing Service Bulletin 737-53A1177, Revision 6, dated May 
31, 2001.
    (5) 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.
    (6) You may review copies of the referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (7) 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 April 18, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-10005 Filed 5-8-13; 8:45 am]
BILLING CODE 4910-13-P