Airworthiness Directives; The Boeing Company Airplanes, 47549-47555 [2013-18765]
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
of the effective date of this AD, Gulfstream
Service Bulletin 100–31–284, Revision 1,
dated May 27, 2011, must be used to
accomplish the actions required by this
paragraph.
(4) Within 250 flight hours after June 25,
2010 (the effective date of AD 2010–11–02,
Amendment 39–16307 (75 FR 28485, May 21,
2010)), but no later than within 6 months
after the effective date of this AD: Verify that
the log of modification of the relevant AFM
includes a reference to MOD G1–20052, and,
if no reference is found, revise the log of
modification of the AFM to include a
reference to the modification.
(5) Doing the modifications specified in
paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of
this AD terminates the requirements of
paragraph (g) of this AD. After the
modifications have been done, the AFM
limitation required by paragraph (g) of this
AD may be removed from the AFM.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 International Branch, send it to ATTN:
Tom Stafford, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227–1622; fax (425) 227–
1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
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. The AMOC
approval letter must specifically reference
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
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(j) Material Incorporated by Reference
17:14 Aug 05, 2013
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Issued in Renton, Washington, on July 9,
2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–18768 Filed 8–5–13; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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
SUMMARY:
(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) Gulfstream Service Bulletin 100–31–
284, Revision 1, dated May 27, 2011.
(ii) Reserved.
VerDate Mar<15>2010
(4) The following service information was
approved for IBR on June 25, 2010 (75 FR
28485, May 21, 2010).
(i) Gulfstream Service Bulletin 100–31–
284, dated August 17, 2006.
(ii) Honeywell Service Bulletin 80–0548–
31–0001, dated April 1, 2006.
(iii) Honeywell Service Bulletin 80–0548–
31–0002, dated March 1, 2006.
(iv) Honeywell Service Bulletin 80–5090–
31–0001, dated March 1, 2006.
(5) For service information identified in
this AD, contact Gulfstream Aerospace
Corporation, P.O. Box 2206, Mail Station D–
25, Savannah, Georgia 31402–2206;
telephone 800–810–4853; fax 912–965–3520;
email pubs@gulfstream.com; Internet https://
www.gulfstream.com/product_support/
technical_pubs/pubs/index.htm.
(6) You may review copies of the 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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47549
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 https://
www.myboeingfleet.com. 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 https://
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:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
Washington 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 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.
tkelley on DSK3SPTVN1PROD with RULES
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
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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
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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
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
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 damagetolerance 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.
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.
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
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.
47551
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 (77 FR
71723, December 4, 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 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
Action
Labor cost
Detailed inspection (retained action).
High frequency eddy current inspection (retained
action).
Modification (retained action).
Determination of door
configuration (new action).
Inspections (new action) ..
Modification (new action)
Parts cost
2 work-hours × $85 per
hour = $170 per inspection cycle.
4 work-hours × $85 per
hour = $340 per inspection cycle.
144 work-hours × $85
per hour = $12,240.
1 work-hour × $85 per
hour = $85.
Number of airplanes of U.S.
registry
Cost per product
Cost on U.S. operators
$0
494
$83,890 per inspection
cycle.
0
$340 per inspection cycle
494
$167,960 per inspection
cycle.
5,430
$17,670 ...........................
494
$8,728,980.
0
$85 ..................................
581
$49,385.
0
$510 per inspection cycle
581
$296,310 per inspection
cycle.
30,536
6 work-hours × $85 per
hour = $510 per inspection cycle.
59 work-hours × $85 per
hour = $5,015.
$170 per inspection cycle
$35,551 ...........................
*
Unknown.
* 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
Labor cost
Related investigative and corrective actions ................
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Action
59 work-hours × $85 per hour = $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,
VerDate Mar<15>2010
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Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
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Parts cost
$30,536
Cost per
product
$35,551
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations
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.
(b) Affected ADs
This AD supersedes AD 2000–06–13 R1,
Amendment 39–12317 (66 FR 36146, July 11,
2001).
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.
(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.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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:
tkelley on DSK3SPTVN1PROD with RULES
■
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.
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(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.
(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
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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
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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.
tkelley on DSK3SPTVN1PROD with RULES
(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
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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.
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Fmt 4700
Sfmt 4700
47553
(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
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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.
tkelley on DSK3SPTVN1PROD with RULES
(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
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17:14 Aug 05, 2013
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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
PO 00000
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Fmt 4700
Sfmt 4700
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.
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(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.
tkelley on DSK3SPTVN1PROD with RULES
(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.
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(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: 9-ANMSeattle-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 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: alan.pohl@faa.gov.
47555
(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 https://www.myboeingfleet.com.
(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 https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Parts 100 and 165
[Docket No. USCG–2012–1057]
(z) Material Incorporated by Reference
RIN 1625–AA08; AA00
(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.
Special Local Regulations and Safety
Zones; Recurring Events in Northern
New England
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[Federal Register Volume 78, Number 151 (Tuesday, August 6, 2013)]
[Rules and Regulations]
[Pages 47549-47555]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[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 https://www.myboeingfleet.com. 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 https://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: 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:
alan.pohl@faa.gov.
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:
Are consistent with the intent that was proposed in the
NPRM (77 FR 71723, December 4, 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 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: 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 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:
alan.pohl@faa.gov.
(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 https://www.myboeingfleet.com.
(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 https://www.archives.gov/federal-register/cfr/ibr-locations.html.
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
