AD 2016-16-13
Recurring
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 737-300 Series | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 737-400 Series | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 737-500 Series | Airworthiness Directives; The Boeing Company Airplanes |
Unsafe Condition
Fatigue cracking of the fuselage skin panels at the chem-mill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Accomplish repetitive external detailed inspections and nondestructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S-1 and S-2R, between STA 400 and STA 460, and repair if necessary. Perform a preventive modification of the fuselage skin at crown stringers S-1 and S-2R.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the compliance times specified in the referenced service information.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
The Boeing Company Model 737-300, -400, and -500 series airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
We are superseding Airworthiness Directive (AD) 2016-13-10, for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2016-13-10 required repetitive external detailed inspections and nondestructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S-1 and S-2R, between station (STA) 400 and STA 460, and repair if necessary. AD 2016-13-10 also required a preventive modification of the fuselage skin at crown stringers S-1 and S-2R. This AD requires the same actions as AD 2016-13-10, and clarifies certain regulatory text. This AD was prompted by the determination that certain regulatory text in AD 2016- 13-10 requires clarification. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chem-mill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane.
Applicability Source Text
Show captured applicability text from the source AD
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-300, -400,
and -500 series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 737-53A1293, Revision 3,
dated January 23, 2015.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se</a>)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 81, Number 157 (Monday, August 15, 2016)]
[Rules and Regulations]
[Pages 53908-53912]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-18952]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-8841; Directorate Identifier 2016-NM-115-AD;
Amendment 39-18611; AD 2016-16-13]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2016-13-10,
for certain The Boeing Company Model 737-300, -400, and -500 series
airplanes. AD 2016-13-10 required repetitive external detailed
inspections and nondestructive inspections to detect cracks in the
fuselage skin along the chem-mill steps at stringers S-1 and S-2R,
between station (STA) 400 and STA 460, and repair if necessary. AD
2016-13-10 also required a preventive modification of the fuselage skin
at crown stringers S-1 and S-2R. This AD requires the same actions as
AD 2016-13-10, and clarifies certain regulatory text. This AD was
prompted by the determination that certain regulatory text in AD 2016-
13-10 requires clarification. We are issuing this AD to detect and
correct fatigue cracking of the fuselage skin panels at the chem-mill
steps, which could result in sudden fracture and failure of the
fuselage skin panels, and consequent rapid decompression of the
airplane.
DATES: This AD is effective August 15, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 9,
2016 (81 FR 43483, July 5, 2016).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of July
23, 2012 (77 FR 36134, June 18, 2012).
We must receive any comments on this AD by September 29, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
<bullet> Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this final rule, contact
Boeing
[[Page 53909]]
Commercial Airplanes, Attention: Data & Services Management, P.O. Box
3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000,
extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
You may view this referenced service information at the FAA Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221. It
is also available on the Internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2016-8841.
Examining the AD Docket
You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
8841; 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 street address for the Docket Office (phone:
800-647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email:
<a href="/cdn-cgi/l/email-protection#9cf6f9f2f2f5faf9eeb2e8effdf7f3e9f1fdf7f5efdcfafdfdb2fbf3ea"><span class="__cf_email__" data-cfemail="81ebe4efefe8e7e4f3aff5f2e0eaeef4ece0eae8f2c1e7e0e0afe6eef7">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Discussion
On June 21, 2016, we issued AD 2016-13-10, Amendment 39-18574 (81
FR 43483, July 5, 2016) (``AD 2016-13-10''), for certain The Boeing
Company Model 737-300, -400, and -500 series airplanes. AD 2016-13-10
required repetitive external detailed inspections and nondestructive
inspections to detect cracks in the fuselage skin along the chem-mill
steps at stringers S-1 and S-2R, between STA 400 and STA 460, and
repair if necessary. AD 2016-13-10 also required a preventive
modification of the fuselage skin at crown stringers S-1 and S-2R. AD
2016-13-10 resulted from a determination that, for certain airplanes,
the skin pockets adjacent to the Air Traffic Control (ATC) antenna are
susceptible to widespread fatigue damage. We issued AD 2016-13-10 to
detect and correct fatigue cracking of the fuselage skin panels at the
chem-mill steps, which could result in sudden fracture and failure of
the fuselage skin panels, and consequent rapid decompression of the
airplane.
Actions Since AD 2016-13-10 Was Issued
Since we issued AD 2016-13-10, we have determined that certain
regulatory text in AD 2016-13-10 requires clarification:
<bullet> We have revised paragraphs (h)(3) and (i) of this AD to
refer to paragraph (l)(3) of this AD for the exception to the service
information.
<bullet> We have also removed the sentence from paragraph (h)(3) of
AD 2016-13-10 that provided existing repair information and instead we
have included existing repair information in the introductory text of
paragraph (h) of this AD.
<bullet> We have revised paragraph (j) of this AD to also refer to
Boeing Alert Service Bulletin 737-53A1293, Revision 3, dated January
23, 2015, for locations for the modification of the chem-mill steps.
<bullet> We have revised paragraphs (j) and (l)(3) of this AD to
refer to paragraph (n) of this AD for the appropriate procedures to
request approval of an alternative method of compliance.
We are issuing this AD to correct the unsafe condition on certain
The Boeing Company Model 737-300, -400, and -500 series airplanes.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1293, Revision 3,
dated January 23, 2015. The service information describes procedures
for repetitive external detailed inspections and non-destructive
inspections to detect cracks in the fuselage skin along the chem-mill
steps at stringers S-1 and S-2R, between STA 400 and STA 460, and
repair of any cracking. The service information also describes
procedures for a modification of the chem-mill steps at the locations
identified, including related investigative actions and corrective
actions, and repetitive post-mod inspections. This service information
is reasonably available because the interested parties have access to
it through their normal course of business or by the means identified
in the ADDRESSES section.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires accomplishing the actions specified in the service
information described previously.
FAA's Justification and Determination of the Effective Date
We are superseding AD 2016-13-10 to clarify certain regulatory
text. We have made no other changes to the requirements published in AD
2016-13-10. Therefore, we find that notice and opportunity for prior
public comment are unnecessary and that good cause exists for making
this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
Docket No. FAA-2016-8841; and Directorate Identifier 2016-NM-115-AD at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 186 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 53910]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD Between 7 and 15 $0 Between $595 and Between $110,670
2016-13-10. work-hours x $85 $1,275 per and $237,150 per
per hour, depending inspection cycle. inspection cycle.
on airplane
configuration =
between $595 and
$1,275 per
inspection cycle.
Retained modification from AD 236 work-hours x $85 (\1\) $20,060............. $3,731,160.
2016-13-10. per hour = $20,060.
----------------------------------------------------------------------------------------------------------------
\1\ We currently have no specific cost estimates associated with the parts necessary for the modification. We
cannot determine the cost of the materials because the modification parts must be sized at the time the
modification is installed, taking into account any existing repairs in the area.
We have received no definitive data that enables us to provide a
cost estimate for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
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 part 39 of the Federal Aviation
Regulations (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)
2016-13-10, Amendment 39-18574 (81 FR 43483, July 5, 2016), and adding
the following new AD:
2016-16-13 The Boeing Company: Amendment 39-18611; Docket No. FAA-
2016-8841; Directorate Identifier 2016-NM-115-AD.
(a) Effective Date
This AD is effective August 15, 2016.
(b) Affected ADs
This AD replaces AD 2016-13-10, Amendment 39-18574 (81 FR 43483,
July 5, 2016) (``AD 2016-13-10'').
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-300, -400,
and -500 series airplanes, certificated in any category, as
identified in Boeing Alert Service Bulletin 737-53A1293, Revision 3,
dated January 23, 2015.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/BE866B732F6CF31086257B9700692796?OpenDocument&Highlight=st01219se</a>)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracks found on the fuselage
skin at the chem-mill steps, and the determination that, for certain
airplanes, the skin pockets adjacent to the Air Traffic Control
antenna are susceptible to widespread fatigue damage. We are issuing
this AD to detect and correct fatigue cracking of the fuselage skin
panels at the chem-mill steps, which could result in sudden fracture
and failure of the fuselage skin panels, and consequent rapid
decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspections With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2016-13-10, with no changes. At the applicable time specified in
tables 1, 2, 3, and 5 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1293, Revision 3, dated January 23,
2015, except as required by paragraphs (l)(1) and (l)(2) of this AD:
Do the actions specified in paragraphs (g)(1) and (g)(2) of this AD,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1293, Revision 3, dated January 23, 2015,
except as required by paragraph (l)(3) of this AD. Repeat the
applicable inspections thereafter at the applicable times specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1293, Revision 3, dated January 23, 2015.
(1) Do an external detailed inspection for cracking of the
fuselage skin chem-mill steps.
(2) Do an external non-destructive (medium frequency eddy
current, magneto optical imaging, C-Scan, or ultrasonic phased
array) inspection for cracking of the fuselage skin chem-mill steps.
[[Page 53911]]
(h) Retained Repair With Clarification of Repair Information and
Service Information Exception
This paragraph restates the requirements of paragraph (h) of AD
2016-13-10, with clarification of repair information and service
information exception. If any cracking is found during any
inspection required by paragraph (g) of this AD, do the applicable
actions specified in paragraph (h)(1), (h)(2),or (h)(3) of this AD.
Installation of a repair prior to August 9, 2016 (the effective date
of AD 2016-13-10) that meets the conditions specified in Part 9 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1293, Revision 3, dated January 23, 2015, terminates the
inspections required by paragraph (g) of this AD for the area
covered by that repair only. Installation of a repair prior to
August 9, 2016, that meets the conditions specified in Part 9 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015, covers all eight chem-
mill step inspection areas between STA 410 and STA 450, and was done
using a method approved in accordance with the procedures specified
in paragraph (n) of this AD, terminates the inspections required by
paragraph (g) of this AD for the area covered by that repair only,
and terminates the preventive modification required by paragraph (i)
of this AD.
(1) Repair before further flight in accordance with Part 2 (for
Group 1 airplanes) or Part 7 (for Group 2 airplanes) of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1293, Revision 3, dated January 23, 2015; except as required by
paragraph (l)(3) of this AD. Installation of a repair that meets the
conditions specified in Note (a) of table 1, 2, 3, or 5 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293,
Revision 3, dated January 23, 2015, terminates the repetitive
inspections required by paragraph (g) of this AD for the area
covered by that repair only.
(2) For Group 1 airplanes: Accomplishing the modification
specified in paragraph (i) of this AD is a method of compliance with
paragraph (h)(1) of this AD.
(3) If any cracking is found in any area not covered by the
preventive modification doubler during any inspection required by
paragraph (g) of this AD: Repair before further flight, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1293, Revision 3, dated January 23,
2015, except as provided by paragraph (l)(3) of this AD.
Installation of this repair terminates the repetitive inspections
required by paragraph (g) of this AD for the area covered by that
repair only.
(i) Retained Preventive Modification With Clarification of Service
Information Exception and Method of Compliance Procedures
This paragraph restates the requirements of paragraph (i) of AD
2016-13-10, with clarification of service information exception and
method of compliance procedures. For Group 1 airplanes: At the
applicable time specified in tables 1, 2, and 3 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293,
Revision 3, dated January 23, 2015, except as required by paragraphs
(l)(1) and (l)(2) of this AD, do a preventive modification of the
fuselage skin at crown stringers S-1 and S-2R, including all
applicable related investigative actions, in accordance with Part 9
of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1293, Revision 3, dated January 23, 2015, except as provided
by paragraph (l)(3) of this AD. Do all applicable related
investigative actions concurrently with the modification.
Installation of a preventive modification terminates the repetitive
inspections required by paragraph (g) of this AD for the modified
area only. Thereafter, repeat the inspections specified in Part 3 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1293, Revision 3, dated January 23, 2015.
(j) Retained Optional Modification With Clarification of Service
Information
This paragraph restates the requirements of paragraph (j) of AD
2016-13-10, with clarification of service information. Accomplishing
a modification of the chem-mill steps at any location identified in
Boeing Service Bulletin 737-53A1293, Revision 2, dated August 10,
2011; or Boeing Alert Service Bulletin 737-53A1293, Revision 3,
dated January 23, 2015; using a method approved in accordance with
the procedures specified in paragraph (n) of this AD, terminates the
repetitive inspections required by paragraph (g) of this AD for the
modified area only.
(k) Retained Post-Repair/Post-Modification Inspections With No Changes
This paragraph restates the requirements of paragraph (k) of AD
2016-13-10, with no changes. Tables 4 and 6 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293,
Revision 3, dated January 23, 2015, specify post-repair/post-
modification airworthiness limitation inspections in compliance with
14 CFR 25.571(a)(3) at the modified locations, which support
compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As
airworthiness limitations, these inspections are required by
maintenance and operational rules. It is therefore unnecessary to
mandate them in this AD. Deviations from these inspections require
FAA approval, but do not require an alternative method of
compliance.
(l) Retained Exceptions to Service Bulletin Specifications With
Clarification of Method of Compliance Procedures
This paragraph restates the requirements of paragraph (l) of AD
2016-13-10, With clarification of method of compliance procedures.
(1) Where Boeing Alert Service Bulletin 737-53A1293, Revision 3,
dated January 23, 2015, specifies a compliance time ``after the
Revision 3 date of this service bulletin,'' this AD requires
compliance within the specified compliance time after August 9, 2016
(the effective date of AD 2016-13-10).
(2) Where the Condition column of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1293,
Revision 3, dated January 23, 2015, specifies a condition based on
when an airplane has or has not been inspected, this AD bases the
condition on whether an airplane has or has not been inspected on
August 9, 2016 (the effective date of AD 2016-13-10).
(3) Where Boeing Alert Service Bulletin 737-53A1293, Revision 3,
dated January 23, 2015, specifies to contact Boeing for repair or
preventive modification instructions: Before further flight, do the
repair or preventive modification, as applicable, using a method
approved in accordance with the procedures specified in paragraph
(n) of this AD.
(m) Retained Credit for Previous Actions With No Changes
This paragraph restates the requirements of paragraph (m) of AD
2016-13-10, with no changes.
(1) This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before July 23, 2012 (the effective date of AD 2012-12-04, Amendment
39-17093 (77 FR 36134, June 18, 2012) (``AD 2012-12-04'')), using
Boeing Alert Service Bulletin 737-53A1293, Revision 1, dated July 7,
2010, which is not incorporated by reference in this AD.
(2) This paragraph provides credit for actions required by
paragraphs (g) and (h) of this AD, if those actions were performed
before August 9, 2016 (the effective date of AD 2016-13-10), using
Boeing Service Bulletin 737-53A1293, Revision 2, dated August 10,
2011, which was incorporated by reference in AD 2012-12-04.
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (o)(1) of this AD.
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#89b0a4c8c7c4a4c5c8c8cac6a4c8c4c6caa4dbecf8fcecfafdfac9efe8e8a7eee6ff"><span class="__cf_email__" data-cfemail="e7decaa6a9aacaaba6a6a4a8caa6aaa8a4cab582969282949394a7818686c9808891">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Los Angeles ACO, to make those findings. To be approved,
the repair method, modification deviation, or alteration deviation
method must meet the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2012-12-04 are approved as AMOCs for
the corresponding provisions of this AD.
[[Page 53912]]
(o) Related Information
(1) For more information about this AD, contact Jennifer
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5264; fax: 562-627-5210; email:
<a href="/cdn-cgi/l/email-protection#98f2fdf6f6f1fefdeab6ecebf9f3f7edf5f9f3f1ebd8fef9f9b6fff7ee"><span class="__cf_email__" data-cfemail="85efe0ebebece3e0f7abf1f6e4eeeaf0e8e4eeecf6c5e3e4e4abe2eaf3">[email protected]</span></a>.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (p)(5) and (p)(6) of this AD.
(p) 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
August 9, 2016 (81 FR 43483, July 5, 2016).
(i) Boeing Alert Service Bulletin 737-53A1293, Revision 3, dated
January 23, 2015.
(ii) Reserved.
(4) The following service information was approved for IBR on
July 23, 2012 (77 FR 36134, June 18, 2012).
(i) Boeing Service Bulletin 737-53A1293, Revision 2, dated
August 10, 2011.
(ii) Reserved.
(5) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(6) You may view this 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued in Renton, Washington, on August 4, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-18952 Filed 8-12-16; 8:45 am]
BILLING CODE 4910-13-P
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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