AD 2013-13-12

[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Rules and Regulations]
[Pages 47549-47555]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2013-18765]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1156; Directorate Identifier 2011-NM-205-AD; 
Amendment 39-17500; AD 2013-13-12]
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) 2000-06-13 R1, 
which applied to certain The Boeing Company Model 737-200, -200C, -300, 
and -400 series airplanes. AD 2000-06-13 R1 required repetitively 
inspecting for cracking of the corners of the door frame and the cross 
beams of the aft cargo door, and corrective actions if necessary. AD 
2000-06-13 R1 also required modifying the aft cargo door, which 
terminates the repetitive inspections. This new AD adds airplanes to 
the applicability, adds inspections and related investigative and 
corrective actions, revises certain inspection types, and reduces a 
certain compliance time for modifying the doors. This AD was prompted 
by reports of cracking in the forward and aft corner frames of the aft 
cargo door and in the lower cross beam. We are issuing this AD to 
prevent fatigue cracking of the corners of the door frame and the cross 
beams of the aft cargo door, which could result in rapid 
depressurization of the airplane.

DATES: This AD is effective September 10, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of September 10, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of May 9, 
2000 (65 FR 17583, April 4, 2000).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
December 24, 1998 (63 FR 67769, December 9, 1998).

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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington 98057-3356. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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: Alan Pohl, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton,

[[Page 47550]]

Washington 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: 
<a href="/cdn-cgi/l/email-protection#ec8d808d82c29c838480ac8a8d8dc28b839a"><span class="__cf_email__" data-cfemail="f3929f929ddd839c9b9fb3959292dd949c85">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, 
July 11, 2001), which revised AD 2000-06-13, Amendment 39-11654 (65 FR 
17583, April 4, 2000). AD 2000-06-13 superseded AD 98-25-06, Amendment 
39-10931 (63 FR 67769, December 9, 1998). AD 2000-06-13 R1 applied to 
the specified products. The NPRM published in the Federal Register on 
December 4, 2012 (77 FR 71723). The NPRM proposed to continue to 
require repetitively inspecting for cracking of the corners of the door 
frame and the cross beams of the aft cargo door; doing corrective 
actions if necessary; and modifying the aft cargo door, which 
terminates the repetitive inspections. The NPRM also proposed to add 
airplanes to the applicability, add inspections and related 
investigative and corrective actions, revise certain inspection types, 
and reduce a certain compliance time for modifying the doors.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 71723, December 4, 2012) and the FAA's response to each comment.

Request To Revise Compliance Time

    Boeing requested that we revise paragraph (o) of the NPRM (77 FR 
71723, December 4, 2012), which specified the compliance time by 
referring to paragraph 1.E. of Boeing Alert Service Bulletin 737-
52A1153, dated July 13, 2011. Boeing requested that we change this 
compliance time to ``4,500 door flight cycles after the effective date 
of this AD'' to avoid a potential conflict with other compliance times 
in the NPRM. Boeing explained a scenario in which an operator could 
comply with paragraph (o) of the NPRM within the required compliance 
time, but then be immediately out of compliance with the proposed 
inspection in paragraphs (p) and (q) of the NPRM.
    We partially agree with the request. As written, the compliance 
time in paragraph (o) of the NPRM (77 FR 71723, December 4, 2012) could 
result in a compliance conflict with other requirements of this AD for 
doors subject to Boeing Alert Service Bulletin 737-52A1079, Revision 7, 
dated December 17, 2010. We disagree, however, with Boeing's requested 
compliance time, which would be unnecessarily more restrictive on 
operators. Also, the referenced doors that have accumulated fewer than 
27,000 total flight cycles should be provided the same compliance time 
as doors subject to Boeing Alert Service Bulletin 737-52A1153, dated 
July 13, 2011. We have therefore revised paragraphs (p) and (q) in this 
final rule to change the compliance time to a threshold of 27,000 total 
flight cycles on the door, with a grace period of 4,500 flight cycles. 
Since paragraph (u)(4) of the NPRM is therefore no longer necessary, we 
have removed that paragraph from this final rule.

Request To Revise Requirement To Determine Door Configuration

    Southwest Airlines (SWA) requested that we revise paragraph (o) of 
the NPRM (77 FR 71723, December 4, 2012), which specified to ``Inspect 
the door to determine the configuration, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1153, dated July 13, 2011.'' SWA considered that the intent of this 
proposed requirement could be accomplished by records research instead 
of a physical inspection. The commenter noted that the Accomplishment 
Instructions of this service bulletin specify only identifying the part 
number of the aft cargo door assembly, and does not specify a method of 
accomplishment.
    We agree with the commenter that a records review is acceptable in 
lieu of accomplishing an inspection to determine the configuration of 
the door. We have changed paragraph (o) accordingly in this final rule.

Request To Refer To Revised Service Information

    All Nippon Airways (ANA) and Boeing requested that we revise the 
NPRM (77 FR 71723, December 4, 2012) to also refer to Boeing Special 
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 
2011, in all locations where Boeing Service Bulletin 737-52-1154, dated 
December 17, 2010, is cited. The commenters noted that some locations 
of the NPRM referred to only the original version, but other paragraphs 
referred to the original version ``as revised by Boeing Special 
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 
2011.''
    We agree with the commenter and have revised paragraphs (r)(2) and 
(u)(2) in this final rule to also add ``as revised by Boeing Special 
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 
2011,'' after the original service bulletin citation.

Request To Clarify Access Procedures

    ANA noted that paragraph (s) of the NPRM (77 FR 71723, December 4, 
2012) identified certain Parts in the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, for 
compliance with the proposed requirements. ANA stated that Part 2, 
which was not identified in paragraph (s) of the NPRM, provides access 
procedures. ANA questioned whether the AD required specific procedures 
for access.
    We agree, and have added new paragraph (u)(4) in this final rule to 
clarify that the access and restoration procedures specified in the 
referenced service information are not required by this AD.

Request To Clarify Required Part References for Compliance

    ANA noted that paragraph (t) of the NPRM (77 FR 71723, December 4, 
2012) referred to Parts 1, 3, 4, 7, and 8 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-52A1153, dated July 
13, 2011. Table 3 and Table 4 of that service bulletin also refer to 
Parts 5 and 6 of that service bulletin. ANA questioned whether 
operators might do Part 5 and Part 6, which describe the preventive 
modification procedures, if no cracks are found. To avoid the need for 
requests for alternative methods of compliance (AMOCs) regarding this 
proposed requirement, ANA requested that we revise paragraph (t) of the 
NPRM to clarify that compliance is ``in accordance with Parts 1, 2, 3, 
4, 5, 6, 7, and 8'' of that service bulletin.
    We disagree with the commenter. Paragraph (s) requires actions in 
accordance with Parts 5 and 6 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011. 
Paragraph (t) of this AD requires other actions, done in accordance 
with Parts 1, 3, 4, 7, and 8 of that service bulletin. We find it 
unnecessary to change this AD regarding this issue.

Request To Exclude Certain Supplemental Structural Inspections

    Paragraph (v) of the NPRM (77 FR 71723, December 4, 2012) would 
provide relief from certain supplemental structural inspections 
specified in Boeing Alert Service Bulletin 737-52A1153, dated July 13, 
2011, and Boeing Alert Service Bulletin 737-52A1079, Revision 7, dated 
December

[[Page 47551]]

17, 2010. Boeing requested that we revise paragraph (v) of the NPRM to 
also provide relief from the supplemental structural inspections 
specified in Table 5 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 737-52-1154, dated December 17, 2010. Boeing noted 
that the NPRM would require inspection of the adjacent cross beam if 
cracks are found in the lower cross beam, and repair of any cracked 
adjacent cross beam, in accordance with Boeing Service Bulletin 737-52-
1154, dated December 17, 2010, but the damage-tolerance inspections 
associated with that repair are not mentioned.
    We agree with the request. We have revised paragraph (v) in this 
final rule to also include reference to Table 5 of Boeing Service 
Bulletin 737-52-1154, dated December 17, 2010.

Request To Delay Final Rule Pending Revised Service Information

    ANA stated that Boeing was in the process of revising Boeing 
Service Bulletins 737-52-1153 and 737-52-1154 based on ANA's 
validation. ANA requested that we cite the revised service information, 
if it is available before the final rule is issued, to reduce 
additional burden for Boeing and the operators. Boeing reported that 
Boeing Service Bulletin 737-52-1154 was being revised to add extra 
material to the repair parts to address issues regarding repair kits 
found during the validation of the bulletin.
    We disagree to delay issuance of the final rule pending issuance of 
revised service information. Accomplishing the service information 
specified in this AD addresses the identified unsafe condition. When 
the revised service bulletins are presented to us for review, however, 
we might consider approving them as AMOCs for this AD. We have not 
changed this final rule regarding this issue.

Additional Changes Made to This AD

    We have revised paragraph (v) and Note 2 to paragraph (v) of this 
final rule. We have designated paragraph (v) as paragraph (v)(1) of 
this final rule, and have reidentified Note 2 to paragraph (v) as 
paragraph (v)(2) of this final rule.

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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (77 FR 71723, December 4, 2012) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 71723, December 4, 2012).
    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 581 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Number of
            Action                Labor cost      Parts cost        Cost per      airplanes of     Cost on U.S.
                                                                    product       U.S. registry     operators
----------------------------------------------------------------------------------------------------------------
Detailed inspection (retained  2 work-hours x               $0  $170 per                    494  $83,890 per
 action).                       $85 per hour =                   inspection                       inspection
                                $170 per                         cycle.                           cycle.
                                inspection
                                cycle.
High frequency eddy current    4 work-hours x                0  $340 per                    494  $167,960 per
 inspection (retained action).  $85 per hour =                   inspection                       inspection
                                $340 per                         cycle.                           cycle.
                                inspection
                                cycle.
Modification (retained         144 work-hours            5,430  $17,670........             494  $8,728,980.
 action).                       x $85 per hour
                                = $12,240.
Determination of door          1 work-hour x                 0  $85............             581  $49,385.
 configuration (new action).    $85 per hour =
                                $85.
Inspections (new action).....  6 work-hours x                0  $510 per                    581  $296,310 per
                                $85 per hour =                   inspection                       inspection
                                $510 per                         cycle.                           cycle.
                                inspection
                                cycle.
Modification (new action)....  59 work-hours x          30,536  $35,551........             \*\  Unknown.
                                $85 per hour =
                                $5,015.
----------------------------------------------------------------------------------------------------------------
* The number of airplanes that require this modification depends on no cracking being found during a certain
  inspection.

    We estimate the following costs to do any necessary related 
investigative and corrective actions that would be required based on 
the results of the inspections. We have no way of determining the 
number of aircraft that might need these actions:

                                               On-condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Related investigative and corrective actions..  59 work-hours x $85 per hour =           $30,536         $35,551
                                                 $5,015.
----------------------------------------------------------------------------------------------------------------

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,

[[Page 47552]]

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) 
2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001), and 
adding the following new AD:

2013-13-12 The Boeing Company: Amendment 39-17500 ; Docket No. FAA-
2012-1156; Directorate Identifier 2011-NM-205-AD.

(a) Effective Date

    This AD is effective September 10, 2013.

(b) Affected ADs

    This AD supersedes AD 2000-06-13 R1, Amendment 39-12317 (66 FR 
36146, July 11, 2001).

(c) Applicability

    This AD applies to all The Boeing Company Model 737-200, -200C, 
-300, -400, and -500 series airplanes, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 52, Doors.

(e) Unsafe Condition

    This AD was prompted by reports of cracking in the forward and 
aft corner frame of the aft cargo door and in the lower cross beam. 
We are issuing this AD to prevent fatigue cracking of the corners of 
the door frame and the cross beams of the aft cargo door, which 
could result in rapid depressurization of the airplane.

(f) Compliance

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

(g) Affected Airplanes for Retained Paragraphs

    Paragraphs (h), (i), (j), (k), and (l) of this AD are restated 
from AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 
2001). These paragraphs apply to Model 737-200 and -200C series 
airplanes, line numbers 6 through 873 inclusive; and Model 737-200, 
-200C, -300, and -400 series airplanes, line numbers 874 through 
1642 inclusive; equipped with an aft cargo door having Boeing part 
number (P/N) 65-47952-1 or P/N 65-47952-524, excluding airplanes 
identified in paragraphs (g)(1) and (g)(2) of this AD.
    (1) Those airplanes on which that door has been modified as 
specified in Boeing Service Bulletin 737-52-1079. Or,
    (2) Those airplanes on which the door assembly having P/N 65-
47952-524 includes four straps (P/Ns 65-47952-139, 65-47952-140, 65-
47952-141, and 65-47952-142) and a thicker lower cross beam web (P/N 
65-47952-157).

(h) Retained Inspections and Corrective Actions

    This paragraph restates the actions required by paragraph (a) of 
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001), 
with revised service information. For airplanes identified in 
paragraph (g) of this AD: Within 90 days or 700 flight cycles after 
December 24, 1998 (the effective date of AD 98-25-06, Amendment 39-
10931 (63 FR 67769, December 9, 1998)), whichever occurs later, 
perform an internal detailed visual inspection to detect cracking of 
the corners of the door frame and the cross beams of the aft cargo 
door, in accordance with Boeing Service Bulletin 737-52-1079, 
Revision 5, dated May 16, 1996; Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Boeing Alert 
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010. 
Accomplishment of the modification required by paragraph (l) of this 
AD constitutes terminating action for the repetitive inspection 
requirements of this paragraph. Doing the inspections required by 
paragraph (p) or (s) of this AD terminates the inspections required 
by this paragraph.
    (1) If no cracking is detected, accomplish the requirements of 
either paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
    (i) Repeat the internal visual inspection thereafter at 
intervals not to exceed 4,500 flight cycles. Or
    (ii) Prior to further flight, modify the corners of the door 
frame and the cross beams of the aft cargo door, in accordance with 
Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996; 
Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated 
November 18, 1999; or Boeing Alert Service Bulletin 737-52A1079, 
Revision 7, dated December 17, 2010. Accomplishment of such 
modification constitutes terminating action for the repetitive 
inspection requirements of paragraph (h)(1)(i) of this AD.
    (2) If any cracking is detected in the upper or lower cross 
beams, prior to further flight, modify the cracked beam, in 
accordance with Part I of the Accomplishment Instructions of Boeing 
Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996; Part I 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-52A1079, Revision 6, dated November 18, 1999; or Part II of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Accomplishment of such 
modification constitutes terminating action for the repetitive 
inspection requirements of paragraph (h)(1)(i) of this AD for the 
modified beam.
    (3) If any cracking is detected in the forward or aft upper door 
frame, prior to further flight, repair the frame and modify the 
corners of the door frame of the aft cargo door, in accordance with 
Part I of the Accomplishment Instructions of Boeing Service Bulletin 
737-52-1079, Revision 5, dated May 16, 1996; Part I of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Part II of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010; except as provided by 
paragraph (i) of this AD. Accomplishment of such modification 
constitutes terminating action for the repetitive inspection 
requirements of paragraph (h)(1)(i) of this AD for the upper door 
frame.
    (4) If any cracking is detected in the forward or aft lower door 
frame, prior to further flight, replace the damaged frame with a new 
frame, and modify the corners of the door frame of the aft cargo 
door, in accordance with Part I of the Accomplishment Instructions 
of Boeing Service Bulletin 737-52-1079, Revision 5, dated May 16, 
1996; Part I of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-52A1079, Revision 6, dated November 18, 1999; 
or Part II of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010. 
Accomplishment of such modification constitutes terminating

[[Page 47553]]

action for the repetitive inspection requirements of paragraph 
(h)(1)(i) of this AD for the lower door frame.

(i) Retained Exception for Certain Actions Specified in Paragraphs (h) 
and (l) of This AD

    This paragraph restates the requirement of paragraph (b) of AD 
2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001). For 
actions required by paragraphs (h) and (l) of this AD: Where Boeing 
Service Bulletin 737-52-1079, Revision 5, dated May 16, 1996; Boeing 
Alert Service Bulletin 737-52A1079, Revision 6, dated November 18, 
1999; or Boeing Alert Service Bulletin 737-52A1079, Revision 7, 
dated December 17, 2010; specifies that certain repairs are to be 
accomplished in accordance with instructions received from Boeing, 
this AD requires that, prior to further flight, such repairs be 
accomplished in accordance with a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA; or using a method 
approved in accordance with the procedures specified in paragraph 
(x) of this AD.

(j) Retained Corrective Actions for Certain Cracking Found During 
Inspection Required by Paragraph (h) of This AD

    This paragraph restates the corrective action required by 
paragraph (c) of AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, 
July 11, 2001), with revised service information. If any cracking of 
the outer chord of the upper or lower cross beams of the aft cargo 
door is detected during any inspection required by paragraph (h) of 
this AD, prior to further flight, accomplish the repair specified in 
paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD. For a repair 
method to be approved, as required by paragraphs (j)(1), (j)(3), and 
(j)(4) of this AD, the approval letter must specifically reference 
this AD.
    (1) Repair in accordance with a method approved by the Manager, 
Seattle ACO.
    (2) Repair in accordance with Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Boeing Alert 
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
    (3) Repair in accordance with data meeting the type 
certification basis of the airplane approved by a Boeing Company 
Designated Engineering Representative who has been authorized by the 
FAA to make such findings.
    (4) Repair in accordance with a method approved by the Boeing 
Commercial Airplanes Organization Designation Authorization (ODA) 
whom we have authorized to make those findings.

(k) Retained Inspections and Corrective Actions for Airplanes 
Identified in Paragraph (g) of This AD

    This paragraph restates the actions required by paragraph (d) of 
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001), 
with revised service information. For airplanes identified in 
paragraph (g) of this AD: Within 4,500 flight cycles or 1 year after 
May 9, 2000 (the effective date of AD 2000-06-13, Amendment 39-11654 
(65 FR 17583, April 4, 2000), whichever occurs later, perform a high 
frequency eddy current inspection (HFEC) to detect cracking of the 
four corners of the door frame of the aft cargo door, using a method 
approved in accordance with the procedures specified in paragraph 
(x) of this AD, or in accordance with Boeing Alert Service Bulletin 
737-52A1079, Revision 6, dated November 18, 1999; or Boeing Alert 
Service Bulletin 737-52A1079, Revision 7, dated December 17, 2010. 
Accomplishment of the modification required by paragraph (l) of this 
AD constitutes terminating action for the repetitive inspection 
requirements of this paragraph. Doing the inspections required by 
paragraph (p) or (s) of this AD terminates the inspections required 
by this paragraph.

    Note 1 to paragraph (k) of this AD:  Additional guidance for the 
inspection can be found in Boeing 737 Nondestructive Test Manual, 
Part 6, Chapter 51-00-00 (Figure 4 or Figure 23).

    (1) If no cracking of the corners of the door frame of the aft 
cargo door is detected, repeat the HFEC inspections thereafter at 
intervals not to exceed 4,500 flight cycles until accomplishment of 
the modification specified in paragraph (l) of this AD.
    (2) If any cracking of the corners of the door frame of the aft 
cargo door is detected, prior to further flight, replace the damaged 
frame with a new frame, and modify the four corners of the door 
frame, in accordance with Part II and Part III of the Accomplishment 
Instructions of Boeing Service Bulletin 737-52-1079, Revision 5, 
dated May 16, 1996; Part II and Part III of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision 
6, dated November 18, 1999; or Part III and Part IV of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Accomplishment of such 
modification constitutes terminating action for the repetitive 
inspection requirements of paragraph (k)(1) of this AD for that door 
frame.

(l) Retained Terminating Action for Inspections Specified in Paragraphs 
(h) and (k) of This AD

    This paragraph restates the action required by paragraph (e) of 
AD 2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001), 
with revised service information. For airplanes identified in 
paragraph (g) of this AD: Within 4 years or 12,000 flight cycles 
after August 15, 2001 (the effective date of AD 2000-06-13 R1), 
whichever occurs later, modify the four corners of the door frame 
and the cross beams of the aft cargo door, in accordance with Part 
II of the Accomplishment Instructions of Boeing Service Bulletin 
737-52-1079, Revision 5, dated May 16, 1996; Part II of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 6, dated November 18, 1999; or Part III of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Accomplishment of that 
modification constitutes terminating action for the repetitive 
inspection requirements of paragraphs (h) and (k) of this AD.

(m) Retained Method of Compliance

    This paragraph restates the method of compliance of Note 3 of AD 
2000-06-13 R1, Amendment 39-12317 (66 FR 36146, July 11, 2001). 
Accomplishment of the modification required by paragraph (a) of AD 
90-06-02, Amendment 39-6489 (55 FR 8372, March 7, 1990), is 
considered acceptable for compliance with the requirements of 
paragraph (l) of this AD.

(n) Retained Credit for Previous Actions

    This paragraph restates the credit given for service information 
specified in Note 4 of AD 2000-06-13 R1, Amendment 39-12317 (66 FR 
36146, July 11, 2001). This paragraph provides credit for the 
modification of the corners of the door frame and the cross beams of 
the aft cargo door required by paragraph (l) of this AD, if the 
modification was accomplished prior to August 15, 2001 (the 
effective date of AD 2000-06-13 R1), using Boeing Service Bulletin 
737-52-1079, dated December 16, 1983; Revision 1, dated December 15, 
1988; Revision 2, dated July 20, 1989; Revision 3, dated May 17, 
1990; or Revision 4, dated February 21, 1991.

(o) New Requirement for Determining Door Configuration

    At the applicable time specified in Table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1153, dated 
July 13, 2011, except as provided by paragraph (u)(1) of this AD: 
Inspect to determine the configuration of the aft cargo door, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-52A1153, dated July 13, 2011. A review of 
airplane maintenance records is acceptable in lieu of this 
inspection if the configuration of the cargo door can be 
conclusively determined from that review.

(p) New Requirements for Certain Doors Subject to Boeing Alert Service 
Bulletin 737-52A1079, Revision 7, Dated December 17, 2010

    If, during the inspection required by paragraph (o) of this AD, 
any door is determined to be from any airplane having line numbers 6 
through 873 inclusive, and neither the modification nor the repair 
specified in any service bulletin identified in paragraphs (p)(1) 
through (p)(7) of this AD has been done as of the effective date of 
this AD: Do a one-time HFEC and a one-time ultrasonic inspection for 
cracking of the upper and lower corner frames and the upper and 
lower cross beams, and do all applicable related investigative and 
corrective actions, in accordance with Parts II, III, IV, and VI of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-52A1079, Revision 7, dated December 17, 2010; and, as 
applicable, the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 737-52-1154, dated December 17, 2010, as 
revised by Boeing Special Attention Service Bulletin 737-52-1154, 
Revision 1, dated August 3, 2011; except as provided by paragraphs 
(u)(2) and (u)(3) of this AD. Do the inspections before the 
accumulation of 27,000 total flight cycles on the door, or within 
4,500 door flight cycles after the

[[Page 47554]]

effective date of this AD, whichever occurs later (for airplanes on 
which the door flight cycles are known); or within 4,500 flight 
cycles after the effective date of this AD (for airplanes on which 
door flight cycles are not known). Do all applicable related 
investigative and corrective actions before further flight. If no 
cracking is found during the initial inspections, before further 
flight, do the modification in accordance with Part III of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1079, Revision 7, dated December 17, 2010. Doing the inspection 
specified in this paragraph terminates the inspections required by 
paragraphs (h) and (k) of this AD.
    (1) Boeing Service Bulletin 737-52-1079, dated December 16, 
1983.
    (2) Boeing Service Bulletin 737-52-1079, Revision 1, dated 
December 15, 1988.
    (3) Boeing Service Bulletin 737-52-1079, Revision 2, dated July 
20, 1989.
    (4) Boeing Service Bulletin 737-52-1079, Revision 3, dated May 
17, 1990.
    (5) Boeing Service Bulletin 737-52-1079, Revision 4, dated 
February 21, 1991.
    (6) Boeing Service Bulletin 737-52-1079, Revision 5, dated May 
16, 1996.
    (7) Boeing Service Bulletin 737-52A1079, Revision 6, dated 
November 18, 1999.

(q) Requirements for All Doors Subject to Boeing Alert Service Bulletin 
737-52A1079, Revision 7, Dated December 17, 2010

    If, during the inspection required by paragraph (o) of this AD, 
any door is determined to be from any airplane having line numbers 6 
through 873 inclusive: Before the accumulation of 27,000 total 
flight cycles on the door, or within 4,500 door flight cycles after 
the effective date of this AD, whichever occurs later, (for 
airplanes on which the door flight cycles are known); or within 
4,500 flight cycles after the effective date of this AD (for 
airplanes on which door flight cycles are not known); inspect the 
lower corner frames to determine if the door has reinforcement 
angles, P/N 65C25180-9, -43, -10, -11, or -12, that were installed 
as specified in any service bulletin identified in paragraphs (q)(1) 
through (q)(5) of this AD. If any affected reinforcement angle is 
found, do a one-time general visual inspection for edge margin and 
do a detailed inspection for cracks; in accordance with Part V of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-52A1079, Revision 7, dated December 17, 2010.
    (1) Boeing Service Bulletin 737-52-1079, dated December 16, 
1983.
    (2) Boeing Service Bulletin 737-52-1079, Revision 1, dated 
December 15, 1988.
    (3) Boeing Service Bulletin 737-52-1079, Revision 2, dated July 
20, 1989.
    (4) Boeing Service Bulletin 737-52-1079, Revision 3, dated May 
17, 1990.
    (5) Boeing Service Bulletin 737-52-1079, Revision 4, dated 
February 21, 1991.

(r) Corrective Actions for Inspections Specified in Paragraph (q) of 
This AD

    If, during any inspection required by paragraph (q) of this AD, 
any crack is found, or if any edge margin does not meet the 
specification identified in Part V of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-52A1079, Revision 
7, dated December 17, 2010, before further flight, do the actions 
specified in paragraphs (r)(1), (r)(2), and (r)(3) of this AD.
    (1) Replace the corner reinforcement angle, in accordance with 
Part III of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-52A1079, Revision 7, dated December 17, 2010.
    (2) Do a one-time detailed inspection or HFEC inspection for 
cracking at the forward and aft ends of cross beam D, in accordance 
with Part 1 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 737-52-1154, dated December 17, 2010; or 
Boeing Special Attention Service Bulletin 737-52-1154, dated 
December 17, 2010, as revised by Boeing Special Attention Service 
Bulletin 737-52-1154, Revision 1, dated August 3, 2011. If any 
cracking is found, before further flight, do all applicable repairs 
in accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 737-52-1154, dated December 17, 2010; or 
Boeing Special Attention Service Bulletin 737-52-1154, dated 
December 17, 2010, as revised by Boeing Special Attention Service 
Bulletin 737-52-1154, Revision 1, dated August 3, 2011, except as 
provided by paragraph (u)(2) of this AD.
    (3) Do a one-time detailed inspection or ultrasonic inspection 
for cracking on the frames, in accordance with Part 2 (detailed 
inspection) or Part 8 (ultrasonic inspection) of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 737-52-
1154, dated December 17, 2010, as revised by Boeing Special 
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 
2011. If any cracking is found, before further flight, replace the 
frame in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 
2010.

(s) Requirements for Doors Subject to Boeing Alert Service Bulletin 
737-52A1153, Dated July 13, 2011

    If, during the action required by paragraph (o) of this AD, a 
door is determined to be from an airplane having line numbers 874 
and subsequent: At the applicable time specified in Tables 1 and 2 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-52A1153, dated July 13, 2011, except as provided by paragraph 
(u)(1) of this AD, do high frequency and detailed inspections for 
cracks in the forward and aft ends of cross beam E, and do all 
applicable related investigative and corrective actions, in 
accordance with Parts 1, 3, 4, 5, and 6 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-52A1153, dated 
July 13, 2011; and, as applicable, the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 737-52-1154, dated 
December 17, 2010, as revised by Boeing Special Attention Service 
Bulletin 737-52-1154, Revision 1, dated August 3, 2011; except as 
provided by paragraph (u)(2) of this AD. Do all applicable related 
investigative and corrective actions at the applicable time 
specified in Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, 
except as provided by paragraph (u)(1) of this AD. If no cracking is 
found during the inspections specified in Boeing Alert Service 
Bulletin 737-52A1153, dated July 13, 2011, at the applicable time 
specified in Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-52A1153, dated July 13, 2011, 
except as provided by paragraph (u)(1) of this AD, do the 
modification in accordance with Parts 5 and 6, as applicable, of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
52A1153, dated July 13, 2011. Repeat the inspections thereafter at 
the times specified in Tables 1 and 2 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-52A1153, dated 
July 13, 2011, until the preventative modification or repair is done 
to both ends of cross beam E in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-52A1153, dated 
July 13, 2011. Doing the inspection specified in this paragraph 
terminates the inspections required by paragraphs (h) and (k) of 
this AD.

(t) One Time Inspections for Doors Subject to Boeing Alert Service 
Bulletin 737-52A1153, Dated July 13, 2011

    If, during the actions required by paragraph (o) of this AD, a 
door is determined to be from an airplane having line numbers 874 
and subsequent: At the applicable time specified in Tables 3 and 4 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-52A1153, dated July 13, 2011, except as provided by paragraph 
(u)(1) of this AD, do a one-time ultrasonic inspection of the frame 
and a detailed inspection of the reinforcing angle for cracks of the 
forward and aft ends of cross beam E, and do all applicable related 
investigative and corrective actions, in accordance with Parts 1, 3, 
4, 7, and 8 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-52A1153, dated July 13, 2011; and, as 
applicable; the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 737-52-1154, dated December 17, 2010, as 
revised by Boeing Special Attention Service Bulletin 737-52-1154, 
Revision 1, dated August 3, 2011; except as provided by paragraph 
(u)(2) of this AD. Do all applicable related investigative and 
corrective actions before further flight.

(u) Service Information Exceptions

    The following exceptions apply to this AD.
    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-52A1153, dated July 13, 2011, specifies a 
compliance time ``after the original issue date of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (2) Where Boeing Special Attention Service Bulletin 737-52-1154, 
dated December 17, 2010; and Boeing Special Attention Service 
Bulletin 737-52-1154, dated December 17, 2010, as revised by Boeing 
Special Attention Service Bulletin 737-52-1154, Revision 1, dated 
August 3, 2011, specify to contact Boeing for repair, before further 
flight, repair using a method approved in accordance with the 
procedures specified in paragraph (x) of this AD.

[[Page 47555]]

    (3) Where Boeing Alert Service Bulletin 737-52A1079, Revision 7, 
dated December 17, 2010, specifies to contact Boeing for repair, 
before further flight, repair using a method approved in accordance 
with the procedures specified in paragraph (x) of this AD.
    (4) This AD does not require accomplishment of the access and 
restoration procedures identified in the Work Instructions of Boeing 
Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 
2010; Boeing Alert Service Bulletin 737-52A1153, dated July 13, 
2011; Boeing Special Attention Service Bulletin 737-52-1154, dated 
December 17, 2010; and Boeing Special Attention Service Bulletin 
737-52-1154, dated December 17, 2010, as revised by Boeing Special 
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 
2011.

(v) Supplemental Structural Inspections

    (1) The supplemental structural inspections specified in Tables 
5 and 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 737-52A1153, dated July 13, 2011; and Tables 3 and 4 of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-52A1079, Revision 7, dated December 17, 2010; and Table 5 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-52-
1154, dated December 17, 2010, as revised by Boeing Special 
Attention Service Bulletin 737-52-1154, Revision 1, dated August 3, 
2011, are not required by this AD.
    (2) The damage tolerance inspections specified in Tables 5 and 6 
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-52A1153, dated July 13, 2011; and Tables 3 and 4 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-52A1079, 
Revision 7, dated December 17, 2010; and Table 5 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-52-1154, dated 
December 17, 2010, as revised by Boeing Special Attention Service 
Bulletin 737-52-1154, Revision 1, dated August 3, 2011; may be used 
in support of compliance with section 121.1109(c)(2) or 
129.109(b)(2) of the Federal Aviation Regulations (14 CFR 
121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions 
specified in the Accomplishment Instructions and figures of Boeing 
Alert Service Bulletin 737-52A1153, dated July 13, 2011; and Boeing 
Alert Service Bulletin 737-52A1079, Revision 7, dated December 17, 
2010; are not required by this AD.

(w) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (p), (q), and (r) of this AD, if the actions were 
accomplished before the effective date of this AD using any service 
information specified in paragraph (w)(1)(i), (w)(1)(ii), 
(w)(1)(iii), (w)(1)(iv), (w)(1)(v), (w)(1)(vi), or (w)(1)(vii) of 
this AD.
    (i) Boeing Service Bulletin 737-52-1079, dated December 16, 
1983.
    (ii) Boeing Service Bulletin 737-52-1079, Revision 1, dated 
December 15, 1988.
    (iii) Boeing Service Bulletin 737-52-1079, Revision 2, dated 
July 20, 1989.
    (iv) Boeing Service Bulletin 737-52-1079, Revision 3, dated May 
17, 1990.
    (v) Boeing Service Bulletin 737-52-1079, Revision 4, dated 
February 21, 1991.
    (vi) Boeing Service Bulletin 737-52-1079, Revision 5, dated May 
16, 1996.
    (vii) Boeing Alert Service Bulletin 737-52A1079, Revision 6, 
dated November 18, 1999.
    (2) This paragraph provides credit for actions required by 
paragraphs (s) and (t) of this AD, if the actions were accomplished 
before the effective date of this AD using Boeing Service Bulletin 
737-52-1154, dated December 17, 2010, provided that any alternative 
detailed inspections specified in Part 17 of the Accomplishment 
Instructions of Boeing Service Bulletin 737-52-1154, dated December 
17, 2010, were done in accordance with Part 11 of the Accomplishment 
Instructions of Boeing Service Bulletin 737-52-1154, dated December 
17, 2010.

(x) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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: <a href="/cdn-cgi/l/email-protection#c8f1e5898685e59bada9bcbca4ade5898b87e58985878be59aadb9bdadbbbcbb88aea9a9e6afa7be"><span class="__cf_email__" data-cfemail="3c05117d7271116f595d48485059117d7f73117d71737f116e594d49594f484f7c5a5d5d125b534a">[email&#160;protected]</span></a>.
    (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 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 previously in accordance with AD 2000-06-13, 
Amendment 39-11654 (65 FR 17583, April 4, 2000); and AD 2000-06-13 
R1, Amendment 39-12317 (66 FR 36146, July 11, 2001); are approved as 
AMOCs for the corresponding requirements of this AD.

(y) Related Information

    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, Washington 
98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: 
<a href="/cdn-cgi/l/email-protection#2d4c414c43035d4245416d4b4c4c034a425b"><span class="__cf_email__" data-cfemail="61000d000f4f110e090d210700004f060e17">[email&#160;protected]</span></a>.

(z) 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.
    (3) The following service information was approved for IBR on 
September 10, 2013.
    (i) Boeing Alert Service Bulletin 737-52A1153, dated July 13, 
2011.
    (ii) Boeing Alert Service Bulletin 737-52A1079, Revision 7, 
dated December 17, 2010.
    (iii) Boeing Special Attention Service Bulletin 737-52-1154, 
dated December 17, 2010.
    (iv) Boeing Special Attention Service Bulletin 737-52-1154, 
Revision 1, dated August 3, 2011.
    (4) The following service information was approved for IBR on 
May 9, 2000 (65 FR 17583, April 4, 2000).
    (i) Boeing Alert Service Bulletin 737-52A1079, Revision 6, dated 
November 18, 1999.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
December 24, 1998 (63 FR 67769, December 9, 1998).
    (i) Boeing Service Bulletin 737-52-1079, Revision 5, dated May 
16, 1996.
    (ii) Reserved.
    (6) 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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (7) You may view this service information at FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 
98057-3356. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (8) 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 <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on June 18, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-18765 Filed 8-5-13; 8:45 am]
BILLING CODE 4910-13-P