Airworthiness Directives; The Boeing Company Airplanes, 38637-38641 [2017-16776]
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Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules
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
certification office, send it to the attention of
the person identified in paragraph (k)(1) of
this AD. Information may be emailed to: 9ANM-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,
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, Seattle ACO
Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously for AD
2015–19–12 are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD.
(5) Except as required by paragraph (h)(1)
of this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (j)(5)(i) and (j)(5)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
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(k) Related Information
(1) For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6447; fax: 425–917–
6590; email: wayne.lockett@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; Internet https://
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Transport Standards Branch, 1601 Lind
Avenue SW., Renton, WA. For information
on the availability of this material at the
FAA, call 425–227–1221.
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Issued in Renton, Washington, on July 28,
2017.
John P. Piccola, Jr.,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–16578 Filed 8–14–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0774; Product
Identifier 2017–NM–036–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2012–12–
05, which applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
AD 2012–12–05 currently requires
repetitive inspections for cracking under
the stop fittings and intercostal flanges
and for cracking of the intercostal web,
attachment clips, stringer splice
channels, frame, reinforcement angle,
shear web, frame outer chord and inner
chord; a one-time inspection to detect
missing fasteners; repetitive inspections
of the cargo barrier net fitting for
cracking; repetitive inspections for
cracking of the stringer S–15L aft
intercostal; and repair or corrective
action if necessary. Since we issued AD
2012–12–05, we have received reports
of additional cracking in locations not
covered by the inspections in that AD.
For certain airplanes, this proposed AD
would add new repetitive inspections of
certain areas of the frame inner chord,
and applicable on-condition actions. We
are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by September 29,
2017.
SUMMARY:
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
ADDRESSES:
PO 00000
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38637
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster
Blvd., MC 110–SK57, Seal Beach, CA
90740; telephone 562–797–1717;
Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Standards Branch,
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 https://www.regulations.gov by
searching for and locating Docket No.
FAA–2017–0774.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0774; 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 proposed 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:
Galib Abumeri, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
Aircraft Certification Office (ACO)
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5324; fax: 562–627–5210;
email: galib.abumeri@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2017–0774; Product Identifier
2017–NM–036–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
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www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On June 4, 2012, we issued AD 2012–
12–05, Amendment 39–17084 (77 FR
36139, June 18, 2012) (‘‘AD 2012–12–
05’’), for all The Boeing Company Model
737–100, –200, –200C, –300, –400, and
–500 series airplanes. AD 2012–12–05
superseded AD 2004–09–09,
Amendment 39–13598 (69 FR 23646,
April 30, 2004); and AD 2009–16–14,
Amendment 39–15987 (74 FR 38901,
August 5, 2009). AD 2012–12–05
requires repetitive inspections for
cracking under the stop fittings and
intercostal flanges and for cracking of
the intercostal web, attachment clips,
stringer splice channels, frame,
reinforcement angle, shear web, frame
outer chord and inner chord; a one-time
inspection to detect missing fasteners;
repetitive inspections of the cargo
barrier net fitting for cracking; repetitive
inspections for cracking of the stringer
S–15L aft intercostal; and repair or
corrective action if necessary. AD 2012–
12–05 resulted from reports of cracking
of the station (STA) 348.2 frame above
the two outboard fasteners attaching the
frame inner chord and door stop fittings,
and in the outboard chord at stringer S–
16L. AD 2012–12–05 also resulted from
reports of missing fasteners in the STA
348.2 frame inner chord. We issued AD
2012–12–05 to detect and correct fatigue
cracking of the intercostals on the
forward and aft sides of the forward
entry door cutout, which could result in
loss of the forward entry door and rapid
decompression of the airplane.
described previously is likely to exist or
develop in other products of the same
type design.
Actions Since AD 2012–12–05 Was
Issued
Since we issued AD 2012–12–05, we
have received reports of additional
cracking in the STA 351.2 frame inner
chord at stringer S–17L, at the fastener
hole location common to the frame
inner chord, door sill, and shear web.
The cracks were reported on Model
737–300 and –500 airplanes that had
accumulated between 40,600 and 65,500
total flight cycles. The STA 351.2 frame
inner chord at stringer S–17L is hidden
under the shear web and the door sill;
therefore, any cracking at this location
cannot be visually detected.
Proposed AD Requirements
This proposed AD would retain all
requirements of AD 2012–12–05.
Although this proposed AD does not
explicitly restate the actions in Boeing
Alert Service Bulletin 737–53A1240,
Revision 1, dated June 29, 2010, that are
part of the requirements of AD 2012–
12–05, this proposed AD would retain
those requirements. Those requirements
are referenced in the service information
identified previously, which, in turn, is
referenced in paragraph (p) of this
proposed AD. Paragraph (p) of this
proposed AD would require
accomplishment of the actions
identified as ‘‘RC’’ (required for
compliance) in the Accomplishment
Instructions of Boeing Alert Service
Bulletin 737–53A1240, Revision 2,
dated November 2, 2016, except for any
differences identified as exceptions in
the regulatory text of this proposed AD.
For information on the procedures
and compliance times for Boeing Alert
Service Bulletin 737–53A1240, Revision
2, dated November 2, 2016, see this
service information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0774.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–53A1240, Revision 2,
dated November 2, 2016. The service
information describes procedures for,
among other actions, repetitive
inspections of the fastener holes in the
STA 351.2 frame inner chord at stringer
17L, and applicable on-condition
actions. 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.
Costs of Compliance
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
We estimate that this proposed AD
affects 411 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS
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Labor cost
Inspections for cracking under the stop
fittings and intercostal flanges [retained actions from AD 2012–12–05]
(411 airplanes).
Inspection of areas forward of the aft
entry door [retained actions from AD
2012–12–05] (411 airplanes).
Inspection of areas aft of the forward
entry door [retained actions from AD
2012–12–05] (411 airplanes).
Inspection for missing fasteners [retained actions from AD 2012–12–05]
(411 airplanes).
Inspection of fastener holes (new proposed action) (160 airplanes).
18 work-hours × $85 per hour = $1,530
per inspection cycle.
$0
$1,530 per inspection cycle.
$628,830 per inspection cycle.
2 work-hours × $85 per hour = $170
per inspection cycle.
0
$170 per inspection
cycle.
$69,870 per inspection cycle.
1 work-hour × $85 per hour = $85 per
inspection cycle.
0
$85 per inspection
cycle.
$34,935 per inspection cycle.
1 work-hour × $85 per hour = $85 ........
476
$561 .......................
$230,571.
27 work-hours × $85 per hour = $2,295
per inspection cycle.
0
$2,295 per inspection cycle.
$367,200 per inspection cycle.
We estimate the following costs to do
any necessary repairs that would be
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Parts cost
required based on the results of the
inspections. We have no way of
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Cost per product
Cost on U.S.
operators
Action
determining the number of aircraft that
might need these repairs:
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38639
ON-CONDITION COSTS
Action
Labor cost
Repair of cracking done in accordance with Boeing
Alert Service Bulletin 737–53A1240.
24 work-hours × $85 per hour = $2,040 ......................
We have received no definitive data
that would enable us to provide cost
estimates for the other on-condition
corrective actions specified in this
proposed 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.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes to the Director of the
System Oversight Division.
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Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
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(2) Is not a ‘‘significant rule’’ under
the 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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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)
2012–12–05, Amendment 39–17084 (77
FR 36139, June 18, 2012), and adding
the following new AD:
■
The Boeing Company: Docket No. FAA–
2017–0774; Product Identifier 2017–
NM–036–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by September 29, 2017.
(b) Affected ADs
This AD replaces AD 2012–12–05,
Amendment 39–17084 (77 FR 36139, June
18, 2012) (‘‘AD 2012–12–05’’).
(c) Applicability
This AD applies to all The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(d) Subject
(d) Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
cracking of the station (STA) 348.2 frame
above the two outboard fasteners attaching
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Parts cost
$11,856
Cost per
product
$13,896
the frame inner chord and door stop fittings,
and in the outboard chord at stringer S–16L;
missing fasteners in the STA 348.2 frame
inner chord; and additional cracking in
locations not covered by the inspections in
AD 2012–12–05. We are issuing this AD to
detect and correct fatigue cracking of the
intercostals on the forward and aft sides of
the forward entry door cutout, which could
result in loss of the forward entry door and
rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Initial Compliance Time for
Model 737–100, –200, –200C, –300, –400, and
–500 Series Airplanes, With No Changes
This paragraph restates the requirements of
paragraph (i) of AD 2012–12–05, with no
changes. For all Model 737–100, –200,
–200C, –300, –400, and –500 series airplanes,
as identified in Boeing Alert Service Bulletin
737–53A1204, Revision 1, dated March 26,
2007: Before the accumulation of 15,000 total
flight cycles, or within 4,500 flight cycles
after November 1, 2005 (the effective date of
AD 2005–20–03, Amendment 39–14296 (70
FR 56361, September 27, 2005) (‘‘AD 2005–
20–03’’)), whichever occurs later: Do the
inspections required by paragraphs (i) and (j)
of this AD.
(h) Retained Initial Compliance Time for
Model 737–200C Series Airplanes, With No
Changes
This paragraph restates the requirements of
paragraph (j) of AD 2012–12–05, with no
changes. For all Model 737–200C series
airplanes, as identified in Boeing Alert
Service Bulletin 737–53A1204, Revision 1,
dated March 26, 2007: Before the
accumulation of 15,000 total flight cycles, or
within 4,500 flight cycles after September 9,
2009 (the effective date of AD 2009–16–14,
Amendment 39–15987 (74 FR 38901, August
5, 2009) (‘‘AD 2009–16–14’’)), whichever
occurs later, do the inspection required by
paragraph (k) of this AD.
(i) Retained Initial Inspection for Group 1
Configuration Airplanes, With No Changes
This paragraph restates the requirements of
paragraph (k) of AD 2012–12–05, with no
changes. For Group 1 airplanes identified in
Boeing Alert Service Bulletin 737–53A1204,
Revision 1, dated March 26, 2007: Perform a
detailed inspection for cracking of the
intercostal web, attachment clips, and
stringer splice channels; and a high
frequency eddy current (HFEC) inspection for
cracking of the stringer splice channels
located forward and aft of the forward entry
door; and do all applicable corrective actions
before further flight; in accordance with Parts
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1 and 2 of the Work Instructions of Boeing
Special Attention Service Bulletin 737–53–
1204, dated June 19, 2003, or Boeing Alert
Service Bulletin 737–53A1204, Revision 1,
dated March 26, 2007; or in accordance with
Parts 1, 2, 4, and 5 of the Work Instructions
of Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24, 2010.
After September 9, 2009 (the effective date of
AD 2009–16–14), and until July 23, 2012 (the
effective date of AD 2012–12–05), Boeing
Alert Service Bulletin 737–53A1204,
Revision 1, dated March 26, 2007; or Boeing
Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010; may be used
to accomplish the actions required by this
paragraph. As of July 23, 2012, only Boeing
Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010, may be used
to accomplish the actions required by this
paragraph.
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(j) Retained Initial Inspection for Cargo
Configuration Airplanes (Forward of the
Forward Entry Door), With No Changes
This paragraph restates the requirements of
paragraph (l) of AD 2012–12–05, with no
changes. For Group 2 cargo airplanes
identified in Boeing Alert Service Bulletin
737–53A1204, Revision 1, dated March 26,
2007: Perform a detailed inspection for
cracking of the intercostal webs and
attachment clips located forward of the
forward entry door, and do all applicable
corrective actions before further flight, in
accordance with Part 3 of the Work
Instructions of Boeing Special Attention
Service Bulletin 737–53–1204, dated June 19,
2003, or Boeing Alert Service Bulletin 737–
53A1204, Revision 1, dated March 26, 2007;
or in accordance with Part 3 of Boeing Alert
Service Bulletin 737–53A1204, Revision 2,
dated June 24, 2010. After September 9, 2009
(the effective date of AD 2009–16–14), and
until July 23, 2012 (the effective date of AD
2012–12–05), Boeing Alert Service Bulletin
737–53A1204, Revision 1, dated March 26,
2007; or Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24, 2010;
may be used to accomplish the actions
required by this paragraph. As of July 23,
2012, only Boeing Alert Service Bulletin
737–53A1204, Revision 2, dated June 24,
2010, may be used to accomplish the actions
required by this paragraph.
(k) Retained Initial Inspection for Cargo
Configuration Airplanes (Aft of the Forward
Entry Door), With No Changes
This paragraph restates the requirements of
paragraph (m) of AD 2012–12–05, with no
changes. For Group 2 cargo airplanes
identified in Boeing Alert Service Bulletin
737–53A1204, Revision 1, dated March 26,
2007: Perform a detailed inspection for
cracking of the intercostal webs and
attachment clips located aft of the forward
entry door, and do all applicable corrective
actions before further flight, in accordance
with Part 4 of the Work Instructions of
Boeing Alert Service Bulletin 737–53A1204,
Revision 1, dated March 26, 2007; or in
accordance with Part 3 of Boeing Alert
Service Bulletin 737–53A1204, Revision 2,
dated June 24, 2010. As of July 23, 2012 (the
effective date of AD 2012–12–05), only
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Boeing Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010, may be used
to accomplish the actions required by this
paragraph.
(l) Retained Repetitive Inspections, With No
Changes
This paragraph restates the requirements of
paragraph (n) of AD 2012–12–05, with no
changes. Repeat the inspections required by
paragraphs (i), (j), and (k) of this AD
thereafter at intervals not to exceed 6,000
flight cycles after the previous inspection, or
within 3,000 flight cycles after September 9,
2009, whichever occurs later.
(m) Retained Exceptions to Boeing Special
Attention Service Bulletin 737–53–1204,
With No Changes
This paragraph restates the requirements of
paragraph (o) of AD 2012–12–05, with no
changes. Do the actions required by
paragraphs (g), (h), (i), (j), (k), and (l) of this
AD by accomplishing all the applicable
actions specified in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–53–1204, dated June 19,
2003; Boeing Alert Service Bulletin 737–
53A1204, Revision 1, dated March 26, 2007;
or Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24, 2010;
except as provided by paragraphs (m)(1) and
(m)(2) of this AD. After September 9, 2009
(the effective date of AD 2009–16–14), and
until July 23, 2012 (the effective date of AD
2012–12–05), Boeing Alert Service Bulletin
737–53A1204, Revision 1, dated March 26,
2007; or Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24, 2010;
may be used to accomplish the actions
required by this paragraph. As of July 23,
2012, only Boeing Alert Service Bulletin
737–53A1204, Revision 2, dated June 24,
2010, may be used to accomplish the actions
required by this paragraph.
(1) Where Boeing Special Attention Service
Bulletin 737–53–1204, dated June 19, 2003;
Boeing Alert Service Bulletin 737–53A1204,
Revision 1, dated March 26, 2007; or Boeing
Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010, specifies to
contact Boeing for repair instructions: Before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (s) of this AD.
(2) Where Boeing Special Attention Service
Bulletin 737–53–1204, dated June 19, 2003;
or Boeing Alert Service Bulletin 737–
53A1204, Revision 1, dated March 26, 2007;
specifies a compliance time relative to the
date of a service bulletin, this AD requires
compliance relative to September 9, 2009
(the effective date of AD 2009–16–14). Where
Boeing Special Attention Service Bulletin
737–53–1204, dated June 19, 2003; or Boeing
Alert Service Bulletin 737–53A1204,
Revision 1, dated March 26, 2007; specifies
a compliance time relative to the date of the
initial release of a service bulletin, this AD
requires compliance relative to November 1,
2005 (the effective date of AD 2005–20–03).
(n) Retained Exceptions to Boeing Alert
Service Bulletin 737–53A1204, With No
Changes
This paragraph restates exceptions to
Boeing Alert Service Bulletin 737–53A1204
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Sfmt 4702
specified in paragraph (r) of AD 2012–12–05,
with no changes.
(1) The access and restoration instructions
identified in the Work Instructions of Boeing
Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010, are not
required by this AD. Operators may perform
those actions in accordance with approved
maintenance procedures.
(2) The use of Boeing Drawing 65–88700 is
not allowed when accomplishing the actions
required by this AD in accordance with the
Work Instructions of Boeing Alert Service
Bulletin 737–53A1204, Revision 2, dated
June 24, 2010.
(o) Retained Initial and Repetitive
Inspections of the S–15L Aft Intercostal and
Cargo Barrier Net Fitting for Model 737–
200C Series Airplanes, With No Changes
This paragraph restates the requirements of
paragraph (s) of AD 2012–12–05, with no
changes. For Group 2 airplanes identified in
Boeing Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010: Before the
accumulation of 15,000 total flight cycles, or
within 4,500 flight cycles after July 23, 2012
(the effective date of AD 2012–12–05),
whichever occurs later, do initial detailed
and HFEC inspections for cracking of the S–
15L aft intercostal between BS 348.2 and BS
360, and do a detailed inspection of the cargo
barrier net fitting at the intercostal, in
accordance with Figure 3 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1204, Revision 2,
dated June 24, 2010. If any cracking is found,
before further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (s) of this AD. Repeat
the inspections thereafter at intervals not to
exceed 6,000 flight cycles.
(p) Actions for Boeing Alert Service Bulletin
737–53A1240, Including New Repetitive
Inspections of Certain Fastener Holes
(1) For airplanes identified as Group 1 and
Group 3 in Boeing Alert Service Bulletin
737–53A1240, Revision 2, dated November 2,
2016: Except as required by paragraph (q) of
this AD, at the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1240,
Revision 2, dated November 2, 2016, do all
applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1240, Revision 2, dated November 2,
2016.
(2) For airplanes identified as Group 2 in
Boeing Alert Service Bulletin 737–53A1240,
Revision 2, dated November 2, 2016: Within
120 days after the effective date of this AD,
do actions to correct the unsafe condition
using a method approved in accordance with
the procedures specified in paragraph (s) of
this AD.
(q) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
737–53A1240, Revision 2, dated November 2,
2016, uses the phrase ‘‘after the Revision 2
date of this service bulletin,’’ for purposes of
determining compliance with the
E:\FR\FM\15AUP1.SGM
15AUP1
Federal Register / Vol. 82, No. 156 / Tuesday, August 15, 2017 / Proposed Rules
requirements of this AD, the phrase ‘‘after the
effective date of this AD’’ must be used.
(2) Where Boeing Alert Service Bulletin
737–53A1240, Revision 2, dated November 2,
2016, specifies contacting Boeing, and
specifies that action as RC: This AD requires
using a method approved in accordance with
the procedures specified in paragraph (s) of
this AD.
mstockstill on DSK30JT082PROD with PROPOSALS
(r) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (p) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 737–53A1240, Revision 1,
dated June 29, 2010, provided the conditions
specified in paragraphs (r)(1) and (r)(2) of this
AD are met and except as provided by
paragraph (r)(3) of this AD. Boeing Alert
Service Bulletin 737–53A1240, Revision 1,
dated June 29, 2010, was incorporated by
reference in AD 2012–12–05.
(1) Note 1 of paragraph 3.A of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1240, Revision 1,
dated June 29, 2010, was disregarded when
accomplishing the actions.
(2) Boeing Drawing 65–88700 was not used
when accomplishing the actions in
accordance with the Work Instructions of
Boeing Alert Service Bulletin 737–53A1240,
Revision 1, dated June 29, 2010.
(3) The access and restoration instructions
identified in the Work Instructions of Boeing
Alert Service Bulletin 737–53A1240,
Revision 1, dated June 29, 2010, are not
required. Operators are allowed to perform
those actions in accordance with approved
maintenance procedures.
(s) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO) Branch, 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 certification office,
send it to the attention of the person
identified in paragraph (t)(1) of this AD.
Information may be emailed to: 9-ANMLAACO-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,
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 Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (q)(2)
of this AD: For service information that
contains steps that are labeled as Required
VerDate Sep<11>2014
16:14 Aug 14, 2017
Jkt 241001
for Compliance (RC), the provisions of
paragraphs (s)(4)(i) and (s)(4)(ii) of this AD
apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
38641
airplanes. This proposed AD was
prompted by reports of cracks found in
the lower chord of the left wing rear
spar. This proposed AD would require
repetitive inspections for cracking of the
lower chord of the rear spar and lower
aft skin at wing buttock line (WBL) 157
and applicable on-condition actions. We
are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on
this proposed AD by September 29,
2017.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
(t) Related Information
https://www.regulations.gov. Follow the
instructions for submitting comments.
(1) For more information about this AD,
• Fax: 202–493–2251.
contact Galib Abumeri, Aerospace Engineer,
• Mail: U.S. Department of
Airframe Branch, ANM–120L, FAA, Los
Transportation, Docket Operations, M–
Angeles Aircraft Certification Office (ACO)
Branch, 3960 Paramount Boulevard,
30, West Building Ground Floor, Room
Lakewood, CA 90712–4137; phone: 562–627– W12–140, 1200 New Jersey Avenue SE.,
5324; fax: 562–627–5210; email:
Washington, DC 20590.
galib.abumeri@faa.gov.
• Hand Delivery: Deliver to Mail
(2) For service information identified in
address above between 9 a.m. and 5
this AD, contact Boeing Commercial
p.m., Monday through Friday, except
Airplanes, Attention: Contractual & Data
Federal holidays.
Services (C&DS), 2600 Westminster Blvd.,
For service information identified in
MC 110–SK57, Seal Beach, CA 90740;
this NPRM, contact Boeing Commercial
telephone 562–797–1717; Internet https://
Airplanes, Attention: Contractual & Data
www.myboeingfleet.com. You may view this
referenced service information at the FAA,
Services (C&DS), 2600 Westminster
Transport Standards Branch, 1601 Lind
Blvd., MC 110–SK57, Seal Beach, CA
Avenue SW., Renton, WA. For information
90740–5600; telephone 562–797–1717;
on the availability of this material at the
Internet https://
FAA, call 425–227–1221.
www.myboeingfleet.com. You may view
Issued in Renton, Washington, on August
this referenced service information at
2, 2017.
the FAA, Transport Standards Branch,
Jeffrey E. Duven,
1601 Lind Avenue SW., Renton, WA.
Director, System Oversight Division, Aircraft
For information on the availability of
Certification Service.
this material at the FAA, call 425–227–
[FR Doc. 2017–16776 Filed 8–14–17; 8:45 am]
1221. It is also available on the Internet
at https://www.regulations.gov by
BILLING CODE 4910–13–P
searching for and locating Docket No.
FAA–2017–0773.
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
You may examine the AD docket on
the Internet at https://
14 CFR Part 39
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
[Docket No. FAA–2017–0773; Product
0773; or in person at the Docket
Identifier 2017–NM–067–AD]
Management Facility between 9 a.m.
RIN 2120–AA64
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
Airworthiness Directives; The Boeing
contains this NPRM, the regulatory
Company Airplanes
evaluation, any comments received, and
other information. The street address for
AGENCY: Federal Aviation
the Docket Office (phone: 800–647–
Administration (FAA), DOT.
5527) is in the ADDRESSES section.
ACTION: Notice of proposed rulemaking
Comments will be available in the AD
(NPRM).
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
SUMMARY: We propose to adopt a new
Payman Soltani, Aerospace Engineer,
airworthiness directive (AD) for all The
Boeing Company Model 737–100, –200, Airframe Section, FAA, Los Angeles
Aircraft Certification Office (ACO)
–200C, –300, –400, and –500 series
PO 00000
Frm 00029
Fmt 4702
Sfmt 4702
E:\FR\FM\15AUP1.SGM
15AUP1
Agencies
[Federal Register Volume 82, Number 156 (Tuesday, August 15, 2017)]
[Proposed Rules]
[Pages 38637-38641]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16776]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0774; Product Identifier 2017-NM-036-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-12-
05, which applies to all The Boeing Company Model 737-100, -200, -200C,
-300, -400, and -500 series airplanes. AD 2012-12-05 currently requires
repetitive inspections for cracking under the stop fittings and
intercostal flanges and for cracking of the intercostal web, attachment
clips, stringer splice channels, frame, reinforcement angle, shear web,
frame outer chord and inner chord; a one-time inspection to detect
missing fasteners; repetitive inspections of the cargo barrier net
fitting for cracking; repetitive inspections for cracking of the
stringer S-15L aft intercostal; and repair or corrective action if
necessary. Since we issued AD 2012-12-05, we have received reports of
additional cracking in locations not covered by the inspections in that
AD. For certain airplanes, this proposed AD would add new repetitive
inspections of certain areas of the frame inner chord, and applicable
on-condition actions. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by September 29,
2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
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.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone
562-797-1717; Internet https://www.myboeingfleet.com. You may view this
referenced service information at the FAA, Transport Standards Branch,
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 https://www.regulations.gov by searching for and
locating Docket No. FAA-2017-0774.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0774; 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 proposed 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: Galib Abumeri, Aerospace Engineer,
Airframe Section, FAA, Los Angeles Aircraft Certification Office (ACO)
Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5324; fax: 562-627-5210; email: galib.abumeri@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0774;
Product Identifier 2017-NM-036-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed
AD because of those comments.
We will post all comments we receive, without change, to https://
[[Page 38638]]
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On June 4, 2012, we issued AD 2012-12-05, Amendment 39-17084 (77 FR
36139, June 18, 2012) (``AD 2012-12-05''), for all The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD
2012-12-05 superseded AD 2004-09-09, Amendment 39-13598 (69 FR 23646,
April 30, 2004); and AD 2009-16-14, Amendment 39-15987 (74 FR 38901,
August 5, 2009). AD 2012-12-05 requires repetitive inspections for
cracking under the stop fittings and intercostal flanges and for
cracking of the intercostal web, attachment clips, stringer splice
channels, frame, reinforcement angle, shear web, frame outer chord and
inner chord; a one-time inspection to detect missing fasteners;
repetitive inspections of the cargo barrier net fitting for cracking;
repetitive inspections for cracking of the stringer S-15L aft
intercostal; and repair or corrective action if necessary. AD 2012-12-
05 resulted from reports of cracking of the station (STA) 348.2 frame
above the two outboard fasteners attaching the frame inner chord and
door stop fittings, and in the outboard chord at stringer S-16L. AD
2012-12-05 also resulted from reports of missing fasteners in the STA
348.2 frame inner chord. We issued AD 2012-12-05 to detect and correct
fatigue cracking of the intercostals on the forward and aft sides of
the forward entry door cutout, which could result in loss of the
forward entry door and rapid decompression of the airplane.
Actions Since AD 2012-12-05 Was Issued
Since we issued AD 2012-12-05, we have received reports of
additional cracking in the STA 351.2 frame inner chord at stringer S-
17L, at the fastener hole location common to the frame inner chord,
door sill, and shear web. The cracks were reported on Model 737-300 and
-500 airplanes that had accumulated between 40,600 and 65,500 total
flight cycles. The STA 351.2 frame inner chord at stringer S-17L is
hidden under the shear web and the door sill; therefore, any cracking
at this location cannot be visually detected.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1240, Revision 2,
dated November 2, 2016. The service information describes procedures
for, among other actions, repetitive inspections of the fastener holes
in the STA 351.2 frame inner chord at stringer 17L, and applicable on-
condition actions. 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 proposing 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.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 2012-12-05.
Although this proposed AD does not explicitly restate the actions in
Boeing Alert Service Bulletin 737-53A1240, Revision 1, dated June 29,
2010, that are part of the requirements of AD 2012-12-05, this proposed
AD would retain those requirements. Those requirements are referenced
in the service information identified previously, which, in turn, is
referenced in paragraph (p) of this proposed AD. Paragraph (p) of this
proposed AD would require accomplishment of the actions identified as
``RC'' (required for compliance) in the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November
2, 2016, except for any differences identified as exceptions in the
regulatory text of this proposed AD.
For information on the procedures and compliance times for Boeing
Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016,
see this service information at https://www.regulations.gov by searching
for and locating Docket No. FAA-2017-0774.
Costs of Compliance
We estimate that this proposed AD affects 411 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections for cracking 18 work-hours x $85 $0 $1,530 per $628,830 per inspection
under the stop fittings and per hour = $1,530 inspection cycle.
intercostal flanges per inspection cycle. cycle.
[retained actions from AD
2012-12-05] (411 airplanes).
Inspection of areas forward 2 work-hours x $85 0 $170 per $69,870 per inspection
of the aft entry door per hour = $170 per inspection cycle.
[retained actions from AD inspection cycle. cycle.
2012-12-05] (411 airplanes).
Inspection of areas aft of 1 work-hour x $85 per 0 $85 per $34,935 per inspection
the forward entry door hour = $85 per inspection cycle.
[retained actions from AD inspection cycle. cycle.
2012-12-05] (411 airplanes).
Inspection for missing 1 work-hour x $85 per 476 $561............ $230,571.
fasteners [retained actions hour = $85.
from AD 2012-12-05] (411
airplanes).
Inspection of fastener holes 27 work[dash]hours x 0 $2,295 per $367,200 per inspection
(new proposed action) (160 $85 per hour = inspection cycle.
airplanes). $2,295 per cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs 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
repairs:
[[Page 38639]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Repair of cracking done in accordance with 24 work-hours x $85 per hour = $11,856 $13,896
Boeing Alert Service Bulletin 737-53A1240. $2,040.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the other on-condition corrective actions specified
in this proposed 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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes to the Director of the System Oversight
Division.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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)
2012-12-05, Amendment 39-17084 (77 FR 36139, June 18, 2012), and adding
the following new AD:
The Boeing Company: Docket No. FAA-2017-0774; Product Identifier
2017-NM-036-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by September 29,
2017.
(b) Affected ADs
This AD replaces AD 2012-12-05, Amendment 39-17084 (77 FR 36139,
June 18, 2012) (``AD 2012-12-05'').
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.
(d) Subject
(d) Air Transport Association (ATA) of America Code 53,
Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking of the station (STA)
348.2 frame above the two outboard fasteners attaching the frame
inner chord and door stop fittings, and in the outboard chord at
stringer S-16L; missing fasteners in the STA 348.2 frame inner
chord; and additional cracking in locations not covered by the
inspections in AD 2012-12-05. We are issuing this AD to detect and
correct fatigue cracking of the intercostals on the forward and aft
sides of the forward entry door cutout, which could result in loss
of the forward entry door and rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Initial Compliance Time for Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2012-12-05, with no changes. For all Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes, as identified in Boeing Alert
Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007:
Before the accumulation of 15,000 total flight cycles, or within
4,500 flight cycles after November 1, 2005 (the effective date of AD
2005-20-03, Amendment 39-14296 (70 FR 56361, September 27, 2005)
(``AD 2005-20-03'')), whichever occurs later: Do the inspections
required by paragraphs (i) and (j) of this AD.
(h) Retained Initial Compliance Time for Model 737-200C Series
Airplanes, With No Changes
This paragraph restates the requirements of paragraph (j) of AD
2012-12-05, with no changes. For all Model 737-200C series
airplanes, as identified in Boeing Alert Service Bulletin 737-
53A1204, Revision 1, dated March 26, 2007: Before the accumulation
of 15,000 total flight cycles, or within 4,500 flight cycles after
September 9, 2009 (the effective date of AD 2009-16-14, Amendment
39-15987 (74 FR 38901, August 5, 2009) (``AD 2009-16-14'')),
whichever occurs later, do the inspection required by paragraph (k)
of this AD.
(i) Retained Initial Inspection for Group 1 Configuration Airplanes,
With No Changes
This paragraph restates the requirements of paragraph (k) of AD
2012-12-05, with no changes. For Group 1 airplanes identified in
Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March
26, 2007: Perform a detailed inspection for cracking of the
intercostal web, attachment clips, and stringer splice channels; and
a high frequency eddy current (HFEC) inspection for cracking of the
stringer splice channels located forward and aft of the forward
entry door; and do all applicable corrective actions before further
flight; in accordance with Parts
[[Page 38640]]
1 and 2 of the Work Instructions of Boeing Special Attention Service
Bulletin 737-53-1204, dated June 19, 2003, or Boeing Alert Service
Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or in
accordance with Parts 1, 2, 4, and 5 of the Work Instructions of
Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June
24, 2010. After September 9, 2009 (the effective date of AD 2009-16-
14), and until July 23, 2012 (the effective date of AD 2012-12-05),
Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March
26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2,
dated June 24, 2010; may be used to accomplish the actions required
by this paragraph. As of July 23, 2012, only Boeing Alert Service
Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used
to accomplish the actions required by this paragraph.
(j) Retained Initial Inspection for Cargo Configuration Airplanes
(Forward of the Forward Entry Door), With No Changes
This paragraph restates the requirements of paragraph (l) of AD
2012-12-05, with no changes. For Group 2 cargo airplanes identified
in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated
March 26, 2007: Perform a detailed inspection for cracking of the
intercostal webs and attachment clips located forward of the forward
entry door, and do all applicable corrective actions before further
flight, in accordance with Part 3 of the Work Instructions of Boeing
Special Attention Service Bulletin 737-53-1204, dated June 19, 2003,
or Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated
March 26, 2007; or in accordance with Part 3 of Boeing Alert Service
Bulletin 737-53A1204, Revision 2, dated June 24, 2010. After
September 9, 2009 (the effective date of AD 2009-16-14), and until
July 23, 2012 (the effective date of AD 2012-12-05), Boeing Alert
Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or
Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June
24, 2010; may be used to accomplish the actions required by this
paragraph. As of July 23, 2012, only Boeing Alert Service Bulletin
737-53A1204, Revision 2, dated June 24, 2010, may be used to
accomplish the actions required by this paragraph.
(k) Retained Initial Inspection for Cargo Configuration Airplanes (Aft
of the Forward Entry Door), With No Changes
This paragraph restates the requirements of paragraph (m) of AD
2012-12-05, with no changes. For Group 2 cargo airplanes identified
in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated
March 26, 2007: Perform a detailed inspection for cracking of the
intercostal webs and attachment clips located aft of the forward
entry door, and do all applicable corrective actions before further
flight, in accordance with Part 4 of the Work Instructions of Boeing
Alert Service Bulletin 737-53A1204, Revision 1, dated March 26,
2007; or in accordance with Part 3 of Boeing Alert Service Bulletin
737-53A1204, Revision 2, dated June 24, 2010. As of July 23, 2012
(the effective date of AD 2012-12-05), only Boeing Alert Service
Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used
to accomplish the actions required by this paragraph.
(l) Retained Repetitive Inspections, With No Changes
This paragraph restates the requirements of paragraph (n) of AD
2012-12-05, with no changes. Repeat the inspections required by
paragraphs (i), (j), and (k) of this AD thereafter at intervals not
to exceed 6,000 flight cycles after the previous inspection, or
within 3,000 flight cycles after September 9, 2009, whichever occurs
later.
(m) Retained Exceptions to Boeing Special Attention Service Bulletin
737-53-1204, With No Changes
This paragraph restates the requirements of paragraph (o) of AD
2012-12-05, with no changes. Do the actions required by paragraphs
(g), (h), (i), (j), (k), and (l) of this AD by accomplishing all the
applicable actions specified in the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 737-53-1204, dated June
19, 2003; Boeing Alert Service Bulletin 737-53A1204, Revision 1,
dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204,
Revision 2, dated June 24, 2010; except as provided by paragraphs
(m)(1) and (m)(2) of this AD. After September 9, 2009 (the effective
date of AD 2009-16-14), and until July 23, 2012 (the effective date
of AD 2012-12-05), Boeing Alert Service Bulletin 737-53A1204,
Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin
737-53A1204, Revision 2, dated June 24, 2010; may be used to
accomplish the actions required by this paragraph. As of July 23,
2012, only Boeing Alert Service Bulletin 737-53A1204, Revision 2,
dated June 24, 2010, may be used to accomplish the actions required
by this paragraph.
(1) Where Boeing Special Attention Service Bulletin 737-53-1204,
dated June 19, 2003; Boeing Alert Service Bulletin 737-53A1204,
Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin
737-53A1204, Revision 2, dated June 24, 2010, specifies to contact
Boeing for repair instructions: Before further flight, repair using
a method approved in accordance with the procedures specified in
paragraph (s) of this AD.
(2) Where Boeing Special Attention Service Bulletin 737-53-1204,
dated June 19, 2003; or Boeing Alert Service Bulletin 737-53A1204,
Revision 1, dated March 26, 2007; specifies a compliance time
relative to the date of a service bulletin, this AD requires
compliance relative to September 9, 2009 (the effective date of AD
2009-16-14). Where Boeing Special Attention Service Bulletin 737-53-
1204, dated June 19, 2003; or Boeing Alert Service Bulletin 737-
53A1204, Revision 1, dated March 26, 2007; specifies a compliance
time relative to the date of the initial release of a service
bulletin, this AD requires compliance relative to November 1, 2005
(the effective date of AD 2005-20-03).
(n) Retained Exceptions to Boeing Alert Service Bulletin 737-53A1204,
With No Changes
This paragraph restates exceptions to Boeing Alert Service
Bulletin 737-53A1204 specified in paragraph (r) of AD 2012-12-05,
with no changes.
(1) The access and restoration instructions identified in the
Work Instructions of Boeing Alert Service Bulletin 737-53A1204,
Revision 2, dated June 24, 2010, are not required by this AD.
Operators may perform those actions in accordance with approved
maintenance procedures.
(2) The use of Boeing Drawing 65-88700 is not allowed when
accomplishing the actions required by this AD in accordance with the
Work Instructions of Boeing Alert Service Bulletin 737-53A1204,
Revision 2, dated June 24, 2010.
(o) Retained Initial and Repetitive Inspections of the S-15L Aft
Intercostal and Cargo Barrier Net Fitting for Model 737-200C Series
Airplanes, With No Changes
This paragraph restates the requirements of paragraph (s) of AD
2012-12-05, with no changes. For Group 2 airplanes identified in
Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June
24, 2010: Before the accumulation of 15,000 total flight cycles, or
within 4,500 flight cycles after July 23, 2012 (the effective date
of AD 2012-12-05), whichever occurs later, do initial detailed and
HFEC inspections for cracking of the S-15L aft intercostal between
BS 348.2 and BS 360, and do a detailed inspection of the cargo
barrier net fitting at the intercostal, in accordance with Figure 3
of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1204, Revision 2, dated June 24, 2010. If any cracking is
found, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (s) of this
AD. Repeat the inspections thereafter at intervals not to exceed
6,000 flight cycles.
(p) Actions for Boeing Alert Service Bulletin 737-53A1240, Including
New Repetitive Inspections of Certain Fastener Holes
(1) For airplanes identified as Group 1 and Group 3 in Boeing
Alert Service Bulletin 737-53A1240, Revision 2, dated November 2,
2016: Except as required by paragraph (q) of this AD, at the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated
November 2, 2016, do all applicable actions identified as ``RC''
(required for compliance) in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1240, Revision 2, dated November 2, 2016.
(2) For airplanes identified as Group 2 in Boeing Alert Service
Bulletin 737-53A1240, Revision 2, dated November 2, 2016: Within 120
days after the effective date of this AD, do actions to correct the
unsafe condition using a method approved in accordance with the
procedures specified in paragraph (s) of this AD.
(q) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 737-53A1240, Revision 2,
dated November 2, 2016, uses the phrase ``after the Revision 2 date
of this service bulletin,'' for purposes of determining compliance
with the
[[Page 38641]]
requirements of this AD, the phrase ``after the effective date of
this AD'' must be used.
(2) Where Boeing Alert Service Bulletin 737-53A1240, Revision 2,
dated November 2, 2016, specifies contacting Boeing, and specifies
that action as RC: This AD requires using a method approved in
accordance with the procedures specified in paragraph (s) of this
AD.
(r) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraph (p) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 737-
53A1240, Revision 1, dated June 29, 2010, provided the conditions
specified in paragraphs (r)(1) and (r)(2) of this AD are met and
except as provided by paragraph (r)(3) of this AD. Boeing Alert
Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010, was
incorporated by reference in AD 2012-12-05.
(1) Note 1 of paragraph 3.A of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1240, Revision 1, dated June
29, 2010, was disregarded when accomplishing the actions.
(2) Boeing Drawing 65-88700 was not used when accomplishing the
actions in accordance with the Work Instructions of Boeing Alert
Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010.
(3) The access and restoration instructions identified in the
Work Instructions of Boeing Alert Service Bulletin 737-53A1240,
Revision 1, dated June 29, 2010, are not required. Operators are
allowed to perform those actions in accordance with approved
maintenance procedures.
(s) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office (ACO)
Branch, 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 certification office,
send it to the attention of the person identified in paragraph
(t)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-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, 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 Branch, to make those findings. To be
approved, the repair method, modification deviation, or alteration
deviation must meet the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (q)(2) of this AD: For
service information that contains steps that are labeled as Required
for Compliance (RC), the provisions of paragraphs (s)(4)(i) and
(s)(4)(ii) of this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(t) Related Information
(1) For more information about this AD, contact Galib Abumeri,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office (ACO) Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-
627-5210; email: galib.abumeri@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740;
telephone 562-797-1717; Internet https://www.myboeingfleet.com. You
may view this referenced service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on August 2, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-16776 Filed 8-14-17; 8:45 am]
BILLING CODE 4910-13-P