Airworthiness Directives; The Boeing Company Airplanes, 36139-36143 [2012-14373]
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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations
21019 Somma Lombardo (VA) Italy, ATTN:
Giovanni Cecchelli; telephone 39–0331–
711133; fax 39 0331 711180; or at https://
www.agustawestland.com/technicalbullettins.
(5) You may review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas 76137 or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Fort Worth, Texas, on May 30,
2012.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2012–14385 Filed 6–15–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1255; Directorate
Identifier 2010–NM–182–AD; Amendment
39–17084; AD 2012–12–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding two
existing airworthiness directives (ADs)
for certain Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
The first existing AD currently requires,
for certain airplanes, repetitive
inspections of the Station (STA) 348.2
frame to detect cracking under the stop
fittings and intercostal flanges at
stringers S–14L, S–15L, and S–16L, and
corrective action if necessary. The
second existing AD currently requires
repetitive inspections to detect cracking
of the intercostal webs, attachment
clips, and stringer splice channels, and
corrective action if necessary. This new
AD requires that the inspection for
cracking under the stop fittings be done
on additional airplanes; extends the
repetitive interval for certain airplanes;
adds a one-time inspection to detect
missing fasteners; and updates or adds
certain inspection and repair
instructions. This new AD also requires,
for certain airplanes, repetitive
inspections of the cargo barrier net
fitting for cracking, and repair if
necessary. This new AD also adds, for
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SUMMARY:
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16:18 Jun 15, 2012
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certain airplanes, repetitive inspections
for cracking of the stringer S–15L aft
intercostal, and repair if necessary. This
AD was prompted by reports of cracking
of the 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.
We have also received reports of
missing fasteners in the STA 348.2
frame inner chord. 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.
DATES: This AD is effective July 23,
2012.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of July 23, 2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of September 9, 2009 (74 FR 38901,
August 5, 2009).
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 1, 2005 (70 FR 56361,
September 27, 2005).
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of June 4, 2004 (69 FR 23646, April
30, 2004).
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
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36139
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone: (425)
917–6450; fax: (425) 917–6590; email:
Alan.Pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede airworthiness
directives 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).
Those ADs apply to the specified
products. The NPRM published in the
Federal Register on November 28, 2011
(76 FR 72858). The NPRM proposed to
retain certain requirements of AD 2004–
09–09 and AD 2009–16–14. The NPRM
proposed to also add airplanes to the
applicability for the high frequency
eddy current (HFEC) inspection for
cracking of the stop fittings at the shear
web at the STA 348.2 frame; extend the
repetitive interval for the HFEC
inspection of the STA 348.2 frame for
Model 737–200C airplanes; add an
inspection to detect missing fasteners of
the STA 348.2 frame inner chord; and
update or add certain inspection and
repair instructions.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the proposal (76 FR 72858,
November 28, 2011) and the FAA’s
response to each comment.
Support for NPRM (76 FR 72858,
November 28, 2011)
Boeing concurs with the contents of
the NPRM (76 FR 72858, November 28,
2011).
Requests To Remove or Revise
Exception to Certain Service
Information
Southwest Airlines (SWA) asked that
paragraph (r) of the NPRM (76 FR
72858, November 28, 2011) be removed,
or revised to provide clarification. SWA
stated that the exception specified in
paragraph (r) of the NPRM does not
allow the sequence of steps in the Work
Instructions of Boeing Alert Service
Bulletin 737–53A1240, Revision 1,
dated June 29, 2010, to be changed.
SWA added that it has serious concerns
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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations
that this paragraph effectively
eliminates all flexibility when
accomplishing open access, the order of
which locations get inspected, and close
access. SWA noted that this becomes
very difficult in a maintenance
environment where other activities may
be worked concurrently. SWA asked if
the intent of the exception in paragraph
(r) of the NPRM is to make removing the
windscreen before the lavatory and
removing the fasteners identified in
Circle Note 1 prior to removing the
fasteners identified in Circle Note 2
conditions of compliance. SWA
understands that certain steps contained
in Boeing Alert Service Bulletin 737–
53A1240, Revision 1, dated June 29,
2010, might have to be accomplished in
a specific order. However, SWA noted
that the umbrella restriction imposed by
paragraph (r) of the NPRM goes beyond
that intent and results in restrictions
when performing maintenance.
Scandanavian Airlines Systems (SAS)
asked that we include an option of
removing the shear web before
accomplishing the inspection specified
in Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24,
2010, as part of the access procedures
specified in the NPRM (76 FR 72858,
November 28, 2011). SAS stated that it
has previously accomplished the
inspections as an alternative method of
compliance (AMOC) to AD 2009–16–14,
Amendment 39–15987 (74 FR 38901,
August 5, 2009). SAS noted that it also
received clarification from the
manufacturer regarding the shear web
removal step in Parts 1 and 2 of the
Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010. SAS
stated that the shear web removal is not
part of the inspection procedures
specified in Boeing Alert Service
Bulletin 737–53A1204, Revision 1,
dated March 26, 2007.
We agree with the commenters for the
reasons provided. We have revised
paragraph (r) of this AD accordingly.
August 5, 2009), are still approved for
the corresponding requirements of this
AD. For clarity, we have added a new
paragraph (t)(5) to this AD to include
that information, and we reidentified
the existing paragraph (t)(5) of the
NPRM (76 FR 72858, November 28,
2011) as paragraph (t)(6) in this final
rule.
Request To Include Reference to
Previously Approved AMOCs
We have clarified the compliance
time in paragraph (q) of this AD by
adding the phrase ‘‘whichever occurs
later.’’
We have updated certain headings
throughout this AD.
Explanation of Additional Changes
Made to This AD
SWA asked that we include a
reference to AMOCs approved for AD
2005–20–03, Amendment 39–14296 (70
FR 56361, September 27, 2005) in the
NPRM (76 FR 72858, November 28,
2011). SWA pointed out that paragraph
(m)(4) of AD 2009–16–14, Amendment
39–15987 (74 FR 38901, August 5,
2009), stated that ‘‘AMOCs approved
previously in accordance with AD
2005–20–03 are approved as AMOCs for
the corresponding provisions of this AD,
provided the repetitive inspection
intervals (if any) do not exceed 6,000
flight cycles.’’ SWA specified that
paragraph (t)(5) of the NPRM can be
interpreted to mean that an AMOC
issued for AD 2005–20–03, which was
approved as an AMOC to AD 2009–16–
14, will be considered as an AMOC to
the NPRM.
We agree with the commenter that
AMOCs approved for AD 2005–20–03,
Amendment 39–14296 (70 FR 56361,
September 27, 2005), as specified in
paragraph (m)(4) of AD 2009–16–14,
Amendment 39–15987 (74 FR 38901,
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously—
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (76 FR
72858, November 28, 2011) for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (76 FR 72858,
November 28, 2011).
Costs of Compliance
We estimate that this AD affects 581
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Labor cost
Inspections for cracking under the
stop fittings and intercostal flanges
[retained from AD 2004–09–09,
Amendment 39–13598 (69 FR
23646, April 30, 2004)].
Inspection of areas forward of the aft
entry door [retained from AD 2009–
16–14, Amendment 39–15987 (74
FR 38901, August 5, 2009)].
Inspection of areas aft of the forward
entry door [retained from AD 2009–
16–14, Amendment 39–15987 (74
FR 38901, August 5, 2009)].
Inspection for missing fasteners [new
action].
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Action
18 work-hours × $85 per hour =
$1,530 per inspection cycle.
$0
2 work-hours × $85 per hour = $170
per inspection cycle.
16:18 Jun 15, 2012
Cost per product
Cost on U.S. operators
$1,530 per inspection cycle.
$888,930 per inspection
cycle.
0
$170 per inspection cycle.
$98,770 per inspection
cycle.
1 work-hour × $85 per hour = $85 per
inspection cycle.
0
$85 per inspection
cycle.
$49,385 per inspection
cycle.
1 work-hour × $85 per hour = $85 .....
476
$561 .....................
$325,941.
We estimate the following costs to do
any necessary repairs that would be
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Parts cost
Jkt 226001
required based on the results of the
inspections. We have no way of
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determining the number of aircraft that
might need these repairs:
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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations
36141
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Repair of cracking if done in accordance with a method approved by the FAA.
Repair of cracking if done in accordance with Boeing Alert Service Bulletin 737–53A1240, Revision 1, dated June 29, 2010.
Unknown ...................................
Unknown ...................................
Unknown.
24 work-hours ...........................
$11,856 .....................................
$13,896.
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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.
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Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
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); and adding
the following new AD:
■
2012–12–05 The Boeing Company:
Amendment 39–17084; Docket No.
FAA–2011–1255; Directorate Identifier
2010–NM–182–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective July 23, 2012.
(b) Affected ADs
This AD supersedes 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).
(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
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
cracking of the 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.
We have also received reports of missing
fasteners in the STA 348.2 frame inner chord.
We are issuing this AD to detect and correct
fatigue cracking of the intercostals on the
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Fmt 4700
Sfmt 4700
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 and Repetitive
Inspections at STA 348.2 for Model 737–
200C Series Airplanes
This paragraph restates the requirements of
paragraph (a) of AD 2004–09–09,
Amendment 39–13598 (69 FR 23646, April
30, 2004), with revised service information.
For Model 737–200C series airplanes: Except
as provided by paragraph (h) of this AD, prior
to the accumulation of 46,000 total flight
cycles, or within 2,250 flight cycles after June
4, 2004 (the effective date of AD 2004–09–
09), whichever occurs later, do detailed and
eddy current inspections of the STA 348.2
frame for cracking under the stop fittings and
intercostal flanges at stringers 14L, 15L, and
16L by accomplishing paragraphs 3.A and
3.B.1 through 3.B.7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1240, dated April 10, 2003; or by
accomplishing Part 1 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1240, Revision 1, dated June 29,
2010. Do the actions in accordance with
Boeing Alert Service Bulletin 737–53A1240,
dated April 10, 2003; or Boeing Alert Service
Bulletin 737–53A1240, Revision 1, dated
June 29, 2010. Any applicable repair must be
accomplished prior to further flight. Repeat
the inspections thereafter at intervals not to
exceed 6,000 flight cycles. As of the effective
date of this AD, only Boeing Alert Service
Bulletin 737–53A1240, Revision 1, dated
June 29, 2010, may be used to accomplish the
actions required by this paragraph.
(h) Retained Corrective Action for Paragraph
(g) of This AD
This paragraph restates the requirements of
paragraph (b) of AD 2004–09–09,
Amendment 39–13598 (69 FR 23646, April
30, 2004), with revised service information.
If any crack is found during any inspection
required by paragraph (g) of this AD, and
Boeing Alert Service Bulletin 737–53A1240,
dated April 10, 2003; or Boeing Alert Service
Bulletin 737–53A1240, Revision 1, dated
June 29, 2010; specifies to contact Boeing for
appropriate action: Before further flight,
repair in accordance with a method approved
by the Manager, Seattle Aircraft Certification
Office (ACO), FAA; or using a method
approved in accordance with the procedures
specified in paragraph (t) of this AD.
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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations
(i) Retained Initial Compliance Time for
Model 737–100, –200, –200C, –300, –400, and
–500 Series Airplanes
(l) Retained Initial Inspection for Cargo
Configuration Airplanes (Forward of the
Forward Entry Door)
This paragraph restates the requirements of
paragraph (f) of AD 2009–16–14, Amendment
39–15987 (74 FR 38901, August 5, 2009). 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)), whichever occurs later:
Do the inspections required by paragraphs (k)
and (l) of this AD.
This paragraph restates the requirements of
paragraph (i) of AD 2009–16–14, Amendment
39–15987 (74 FR 38901, August 5, 2009),
with revised service information. 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,
Amendment 39–15987 (74 FR 38901, August
5, 2009), and until the effective date of this
AD, 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 the effective
date of this AD, 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 Compliance Time for
Model 737–200C Series Airplanes
This paragraph restates the requirements of
paragraph (g) of AD 2009–16–14,
Amendment 39–15987 (74 FR 38901, August
5, 2009). 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),
whichever occurs later, do the inspection
required by paragraph (m) of this AD.
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(k) Retained Initial Inspection for Group 1
Configuration Airplanes
This paragraph restates the requirements of
paragraph (h) of AD 2009–16–14,
Amendment 39–15987 (74 FR 38901, August
5, 2009), with revised service information.
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
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, Amendment 39–15987 (74
FR 38901, August 5, 2009), and until the
effective date of this AD, 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 the effective date of this AD,
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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16:18 Jun 15, 2012
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(m) Retained Initial Inspection for Cargo
Configuration Airplanes (Aft of the Forward
Entry Door)
This paragraph restates the requirements of
paragraph (j) of AD 2009–16–14, Amendment
39–15987 (74 FR 38901, August 5, 2009),
with revised service information. 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 the
effective date of this AD, only Boeing Alert
Service Bulletin 737–53A1204, Revision 2,
dated June 24, 2010, may be used to
accomplish the actions required by this
paragraph.
(n) Retained Repeat Inspections
This paragraph restates the requirements of
paragraph (k) of AD 2009–16–14,
Amendment 39–15987 (74 FR 38901, August
5, 2009). Repeat the inspections required by
paragraphs (k), (l), and (m) 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 (the effective date of AD 2009–1614),
whichever occurs later.
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(o) Retained Exceptions to Boeing Special
Attention Service Bulletin 737–53–1204
This paragraph restates the requirements of
paragraph (l) of AD 2009–16–14, Amendment
39–15987 (74 FR 38901, August 5, 2009),
with revised service information. Do the
actions required by paragraphs (i), (j), (k), (l),
(m), and (n) 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 (o)(1) and (o)(2) of this AD. After
September 9, 2009 (the effective date of AD
2009–16–14), and until the effective date of
this AD, 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 the effective
date of this AD, 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 (t) 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,
Amendment 39–15987 (74 FR 38901, August
5, 2009). 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, Amendment 39–14296 (70 FR
56361, September 27, 2005)).
(p) New One-Time Inspection for Missing
Fasteners at STA 348.2
For Groups 2 and 3 airplanes identified in
Boeing Alert Service Bulletin 737–53A1240,
Revision 1, dated June 29, 2010: Within 4,500
flight cycles after the effective date of this
AD, do a detailed inspection to detect
missing fasteners of the STA 348.2 frame, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1240, Revision 1, dated June 29,
2010, except as required by paragraph (r) of
this AD. If any fastener is missing, before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (t) of this AD.
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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations
(q) New Initial and Repetitive Inspections at
STA 348.2 for Model 737–100, –200, –300,
–400, and –500 Series Airplanes
For Groups 2 and 3 airplanes identified in
Boeing Alert Service Bulletin 737–53A1240,
Revision 1, dated June 29, 2010: Before the
accumulation of 15,000 total flight cycles, or
within 4,500 flight cycles after the effective
date of this AD, whichever occurs later, do
HFEC and surface eddy current inspections
for cracking of the frame, HFEC inspections
for cracking of the reinforcement angle and
shear web, and a detailed inspection for
cracking of the STA 348.2 frame outer chord,
inner chord, and reinforcement angle, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1240, Revision 1, dated June 29,
2010, except as required by paragraph (r) of
this AD. If any crack is found during any
inspection required by this paragraph, before
further flight, do all applicable corrective
actions in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1240, Revision 1,
dated June 29, 2010, except as required by
paragraph (r) of this AD, and except where
that service bulletin specifies to contact
Boeing, before further flight, repair using a
method approved in accordance with the
procedures specified in paragraph (t) of this
AD. Repeat the inspections thereafter at
intervals not to exceed 6,000 flight cycles.
srobinson on DSK4SPTVN1PROD with RULES
(r) New Exceptions to Boeing Alert Service
Bulletins 737–53A1204 and 737–53A1240
(1) Note 1 of paragraph 3.A of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1240, Revision 1,
dated June 29, 2010, is to be disregarded
when accomplishing the actions required by
this AD.
(2) The access and restoration instructions
identified in the Work Instructions of Boeing
Alert Service Bulletin 737–53A1204,
Revision 2, dated June 24, 2010; and Boeing
Alert Service Bulletin 737–53A1240,
Revision 1, dated June 29, 2010; are not
required by this AD. Operators may perform
those actions in accordance with approved
maintenance procedures.
(3) 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; and Boeing Alert Service
Bulletin 737–53A1240, Revision 1, dated
June 29, 2010.
(s) New Initial and Repetitive Inspections of
the S–15L Aft Intercostal and Cargo Barrier
Net Fitting for Model 737–200C Series
Airplanes
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 the effective
date of this AD, 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
VerDate Mar<15>2010
16:18 Jun 15, 2012
Jkt 226001
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 (t) of
this AD. Repeat the inspections thereafter at
intervals not to exceed 6,000 flight cycles.
(t) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, it may be emailed
to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
to make those findings. For a repair method
to be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 2004–09–09,
Amendment 39–13598 (69 FR 23646, April
30, 2004), are approved as AMOCs for the
corresponding requirements of this AD.
(5) AMOCs approved previously in
accordance with AD 2005–20–03,
Amendment 39–14296 (70 FR 56361,
September 27, 2005), are approved as
AMOCs for the corresponding requirements
of this AD, provided the repetitive inspection
intervals (if any) do not exceed 6,000 flight
cycles.
(6) AMOCs approved previously in
accordance with AD 2009–16–14,
Amendment 39–15987 (74 FR 38901, August
5, 2009), are approved as AMOCs for the
corresponding requirements of this AD.
(u) Related Information
For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; phone (425) 917–
6450; fax (425) 917–6590; email:
Alan.Pohl@faa.gov.
(v) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) under 5 U.S.C. 552(a) and 1 CFR part
51.
(2) You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on July 23, 2012.
(i) Boeing Alert Service Bulletin 737–
53A1240, Revision 1, dated June 29, 2010.
(ii) Boeing Alert Service Bulletin 737–
53A1204, Revision 2, dated June 24, 2010.
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
36143
(4) The following service information was
approved for IBR on September 9, 2009 (74
FR 38901, August 5, 2009).
(i) Boeing Alert Service Bulletin 737–
53A1204, Revision 1, dated March 26, 2007.
(5) The following service information was
approved for IBR on November 1, 2005 (70
FR 56361, September 27, 2005).
(i) Boeing Special Attention Service
Bulletin 737–53–1204, dated June 19, 2003.
(6) The following service information was
approved for IBR on June 4, 2004 (69 FR
23646, April 30, 2004).
(i) Boeing Alert Service Bulletin 737–
53A1240, dated April 10, 2003.
(7) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, Washington 98124–2207; telephone
206–544–5000, extension 1; fax 206–766–
5680; Internet https://
www.myboeingfleet.com.
(8) You may review copies of the
referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221.
(9) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr_locations.html.
Issued in Renton, Washington, on June 4,
2012.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2012–14373 Filed 6–15–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–1415; Directorate
Identifier 2011–NM–145–AD; Amendment
39–17089; AD 2012–12–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 717–200
airplanes. This AD was prompted by
reports of cracks found on the center
section ribs of the horizontal stabilizers.
This AD requires repetitive inspections
for cracking of the aft face of the left and
right rib hinge bearing lugs of the center
SUMMARY:
E:\FR\FM\18JNR1.SGM
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Agencies
[Federal Register Volume 77, Number 117 (Monday, June 18, 2012)]
[Rules and Regulations]
[Pages 36139-36143]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-14373]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1255; Directorate Identifier 2010-NM-182-AD;
Amendment 39-17084; AD 2012-12-05]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding two existing airworthiness directives (ADs)
for certain Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. The first existing AD currently requires, for certain
airplanes, repetitive inspections of the Station (STA) 348.2 frame to
detect cracking under the stop fittings and intercostal flanges at
stringers S-14L, S-15L, and S-16L, and corrective action if necessary.
The second existing AD currently requires repetitive inspections to
detect cracking of the intercostal webs, attachment clips, and stringer
splice channels, and corrective action if necessary. This new AD
requires that the inspection for cracking under the stop fittings be
done on additional airplanes; extends the repetitive interval for
certain airplanes; adds a one-time inspection to detect missing
fasteners; and updates or adds certain inspection and repair
instructions. This new AD also requires, for certain airplanes,
repetitive inspections of the cargo barrier net fitting for cracking,
and repair if necessary. This new AD also adds, for certain airplanes,
repetitive inspections for cracking of the stringer S-15L aft
intercostal, and repair if necessary. This AD was prompted by reports
of cracking of the 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. We have also received reports of
missing fasteners in the STA 348.2 frame inner chord. 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.
DATES: This AD is effective July 23, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of July 23, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of September 9,
2009 (74 FR 38901, August 5, 2009).
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 1,
2005 (70 FR 56361, September 27, 2005).
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of June 4, 2004
(69 FR 23646, April 30, 2004).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, Washington. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 917-
6450; fax: (425) 917-6590; email: Alan.Pohl@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede airworthiness directives 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). Those ADs apply to the
specified products. The NPRM published in the Federal Register on
November 28, 2011 (76 FR 72858). The NPRM proposed to retain certain
requirements of AD 2004-09-09 and AD 2009-16-14. The NPRM proposed to
also add airplanes to the applicability for the high frequency eddy
current (HFEC) inspection for cracking of the stop fittings at the
shear web at the STA 348.2 frame; extend the repetitive interval for
the HFEC inspection of the STA 348.2 frame for Model 737-200C
airplanes; add an inspection to detect missing fasteners of the STA
348.2 frame inner chord; and update or add certain inspection and
repair instructions.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(76 FR 72858, November 28, 2011) and the FAA's response to each
comment.
Support for NPRM (76 FR 72858, November 28, 2011)
Boeing concurs with the contents of the NPRM (76 FR 72858, November
28, 2011).
Requests To Remove or Revise Exception to Certain Service Information
Southwest Airlines (SWA) asked that paragraph (r) of the NPRM (76
FR 72858, November 28, 2011) be removed, or revised to provide
clarification. SWA stated that the exception specified in paragraph (r)
of the NPRM does not allow the sequence of steps in the Work
Instructions of Boeing Alert Service Bulletin 737-53A1240, Revision 1,
dated June 29, 2010, to be changed. SWA added that it has serious
concerns
[[Page 36140]]
that this paragraph effectively eliminates all flexibility when
accomplishing open access, the order of which locations get inspected,
and close access. SWA noted that this becomes very difficult in a
maintenance environment where other activities may be worked
concurrently. SWA asked if the intent of the exception in paragraph (r)
of the NPRM is to make removing the windscreen before the lavatory and
removing the fasteners identified in Circle Note 1 prior to removing
the fasteners identified in Circle Note 2 conditions of compliance. SWA
understands that certain steps contained in Boeing Alert Service
Bulletin 737-53A1240, Revision 1, dated June 29, 2010, might have to be
accomplished in a specific order. However, SWA noted that the umbrella
restriction imposed by paragraph (r) of the NPRM goes beyond that
intent and results in restrictions when performing maintenance.
Scandanavian Airlines Systems (SAS) asked that we include an option
of removing the shear web before accomplishing the inspection specified
in Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June
24, 2010, as part of the access procedures specified in the NPRM (76 FR
72858, November 28, 2011). SAS stated that it has previously
accomplished the inspections as an alternative method of compliance
(AMOC) to AD 2009-16-14, Amendment 39-15987 (74 FR 38901, August 5,
2009). SAS noted that it also received clarification from the
manufacturer regarding the shear web removal step in Parts 1 and 2 of
the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1204, Revision 2, dated June 24, 2010. SAS stated that the shear web
removal is not part of the inspection procedures specified in Boeing
Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007.
We agree with the commenters for the reasons provided. We have
revised paragraph (r) of this AD accordingly.
Request To Include Reference to Previously Approved AMOCs
SWA asked that we include a reference to AMOCs approved for AD
2005-20-03, Amendment 39-14296 (70 FR 56361, September 27, 2005) in the
NPRM (76 FR 72858, November 28, 2011). SWA pointed out that paragraph
(m)(4) of AD 2009-16-14, Amendment 39-15987 (74 FR 38901, August 5,
2009), stated that ``AMOCs approved previously in accordance with AD
2005-20-03 are approved as AMOCs for the corresponding provisions of
this AD, provided the repetitive inspection intervals (if any) do not
exceed 6,000 flight cycles.'' SWA specified that paragraph (t)(5) of
the NPRM can be interpreted to mean that an AMOC issued for AD 2005-20-
03, which was approved as an AMOC to AD 2009-16-14, will be considered
as an AMOC to the NPRM.
We agree with the commenter that AMOCs approved for AD 2005-20-03,
Amendment 39-14296 (70 FR 56361, September 27, 2005), as specified in
paragraph (m)(4) of AD 2009-16-14, Amendment 39-15987 (74 FR 38901,
August 5, 2009), are still approved for the corresponding requirements
of this AD. For clarity, we have added a new paragraph (t)(5) to this
AD to include that information, and we reidentified the existing
paragraph (t)(5) of the NPRM (76 FR 72858, November 28, 2011) as
paragraph (t)(6) in this final rule.
Explanation of Additional Changes Made to This AD
We have clarified the compliance time in paragraph (q) of this AD
by adding the phrase ``whichever occurs later.''
We have updated certain headings throughout this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously--and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (76 FR 72858, November 28, 2011) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (76 FR 72858, November 28, 2011).
Costs of Compliance
We estimate that this AD affects 581 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections for cracking 18 work-hours x $0 $1,530 per $888,930 per inspection cycle.
under the stop fittings and $85 per hour = inspection
intercostal flanges $1,530 per cycle.
[retained from AD 2004-09- inspection
09, Amendment 39-13598 (69 cycle.
FR 23646, April 30, 2004)].
Inspection of areas forward 2 work-hours x 0 $170 per $98,770 per inspection cycle.
of the aft entry door $85 per hour = inspection
[retained from AD 2009-16- $170 per cycle.
14, Amendment 39-15987 (74 inspection
FR 38901, August 5, 2009)]. cycle.
Inspection of areas aft of 1 work-hour x 0 $85 per $49,385 per inspection cycle.
the forward entry door $85 per hour = inspection
[retained from AD 2009-16- $85 per cycle.
14, Amendment 39-15987 (74 inspection
FR 38901, August 5, 2009)]. cycle.
Inspection for missing 1 work-hour x 476 $561........... $325,941.
fasteners [new action]. $85 per hour =
$85.
----------------------------------------------------------------------------------------------------------------
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 36141]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair of cracking if done in Unknown................. Unknown................. Unknown.
accordance with a method approved by
the FAA.
Repair of cracking if done in 24 work-hours........... $11,856................. $13,896.
accordance with Boeing Alert Service
Bulletin 737-53A1240, Revision 1,
dated June 29, 2010.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
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); and
adding the following new AD:
2012-12-05 The Boeing Company: Amendment 39-17084; Docket No. FAA-
2011-1255; Directorate Identifier 2010-NM-182-AD.
(a) Effective Date
This airworthiness directive (AD) is effective July 23, 2012.
(b) Affected ADs
This AD supersedes 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).
(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
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking of the 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. We have also received reports of missing fasteners
in the STA 348.2 frame inner chord. 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 and Repetitive Inspections at STA 348.2 for Model
737-200C Series Airplanes
This paragraph restates the requirements of paragraph (a) of AD
2004-09-09, Amendment 39-13598 (69 FR 23646, April 30, 2004), with
revised service information. For Model 737-200C series airplanes:
Except as provided by paragraph (h) of this AD, prior to the
accumulation of 46,000 total flight cycles, or within 2,250 flight
cycles after June 4, 2004 (the effective date of AD 2004-09-09),
whichever occurs later, do detailed and eddy current inspections of
the STA 348.2 frame for cracking under the stop fittings and
intercostal flanges at stringers 14L, 15L, and 16L by accomplishing
paragraphs 3.A and 3.B.1 through 3.B.7 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1240, dated
April 10, 2003; or by accomplishing Part 1 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1240, Revision
1, dated June 29, 2010. Do the actions in accordance with Boeing
Alert Service Bulletin 737-53A1240, dated April 10, 2003; or Boeing
Alert Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010.
Any applicable repair must be accomplished prior to further flight.
Repeat the inspections thereafter at intervals not to exceed 6,000
flight cycles. As of the effective date of this AD, only Boeing
Alert Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010,
may be used to accomplish the actions required by this paragraph.
(h) Retained Corrective Action for Paragraph (g) of This AD
This paragraph restates the requirements of paragraph (b) of AD
2004-09-09, Amendment 39-13598 (69 FR 23646, April 30, 2004), with
revised service information. If any crack is found during any
inspection required by paragraph (g) of this AD, and Boeing Alert
Service Bulletin 737-53A1240, dated April 10, 2003; or Boeing Alert
Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010;
specifies to contact Boeing for appropriate action: Before further
flight, repair in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or using a method
approved in accordance with the procedures specified in paragraph
(t) of this AD.
[[Page 36142]]
(i) Retained Initial Compliance Time for Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes
This paragraph restates the requirements of paragraph (f) of AD
2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009). 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)), whichever occurs later: Do
the inspections required by paragraphs (k) and (l) of this AD.
(j) Retained Initial Compliance Time for Model 737-200C Series
Airplanes
This paragraph restates the requirements of paragraph (g) of AD
2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009). 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), whichever occurs later, do the inspection required
by paragraph (m) of this AD.
(k) Retained Initial Inspection for Group 1 Configuration Airplanes
This paragraph restates the requirements of paragraph (h) of AD
2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009), with
revised service information. 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 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, Amendment 39-15987 (74 FR 38901,
August 5, 2009), and until the effective date of this AD, 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 the effective date of this AD, 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 Initial Inspection for Cargo Configuration Airplanes
(Forward of the Forward Entry Door)
This paragraph restates the requirements of paragraph (i) of AD
2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009), with
revised service information. 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, Amendment
39-15987 (74 FR 38901, August 5, 2009), and until the effective date
of this AD, 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 the effective date of this
AD, only Boeing Alert Service Bulletin 737-53A1204, Revision 2,
dated June 24, 2010, may be used to accomplish the actions required
by this paragraph.
(m) Retained Initial Inspection for Cargo Configuration Airplanes (Aft
of the Forward Entry Door)
This paragraph restates the requirements of paragraph (j) of AD
2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009), with
revised service information. 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 the effective
date of this AD, only Boeing Alert Service Bulletin 737-53A1204,
Revision 2, dated June 24, 2010, may be used to accomplish the
actions required by this paragraph.
(n) Retained Repeat Inspections
This paragraph restates the requirements of paragraph (k) of AD
2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009). Repeat
the inspections required by paragraphs (k), (l), and (m) 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 (the effective date of AD 2009-1614), whichever occurs
later.
(o) Retained Exceptions to Boeing Special Attention Service Bulletin
737-53-1204
This paragraph restates the requirements of paragraph (l) of AD
2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009), with
revised service information. Do the actions required by paragraphs
(i), (j), (k), (l), (m), and (n) 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
(o)(1) and (o)(2) of this AD. After September 9, 2009 (the effective
date of AD 2009-16-14), and until the effective date of this AD,
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 the effective date of this AD, 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 (t) 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, Amendment 39-15987 (74 FR 38901, August 5, 2009). 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, Amendment 39-14296 (70 FR 56361, September 27, 2005)).
(p) New One-Time Inspection for Missing Fasteners at STA 348.2
For Groups 2 and 3 airplanes identified in Boeing Alert Service
Bulletin 737-53A1240, Revision 1, dated June 29, 2010: Within 4,500
flight cycles after the effective date of this AD, do a detailed
inspection to detect missing fasteners of the STA 348.2 frame, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010,
except as required by paragraph (r) of this AD. If any fastener is
missing, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (t) of this
AD.
[[Page 36143]]
(q) New Initial and Repetitive Inspections at STA 348.2 for Model 737-
100, -200, -300, -400, and -500 Series Airplanes
For Groups 2 and 3 airplanes identified in Boeing Alert Service
Bulletin 737-53A1240, Revision 1, dated June 29, 2010: Before the
accumulation of 15,000 total flight cycles, or within 4,500 flight
cycles after the effective date of this AD, whichever occurs later,
do HFEC and surface eddy current inspections for cracking of the
frame, HFEC inspections for cracking of the reinforcement angle and
shear web, and a detailed inspection for cracking of the STA 348.2
frame outer chord, inner chord, and reinforcement angle, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1240, Revision 1, dated June 29, 2010,
except as required by paragraph (r) of this AD. If any crack is
found during any inspection required by this paragraph, before
further flight, do all applicable corrective actions in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1240, Revision 1, dated June 29, 2010, except as
required by paragraph (r) of this AD, and except where that service
bulletin specifies to contact Boeing, before further flight, repair
using a method approved in accordance with the procedures specified
in paragraph (t) of this AD. Repeat the inspections thereafter at
intervals not to exceed 6,000 flight cycles.
(r) New Exceptions to Boeing Alert Service Bulletins 737-53A1204 and
737-53A1240
(1) Note 1 of paragraph 3.A of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1240, Revision 1, dated June
29, 2010, is to be disregarded when accomplishing the actions
required by this AD.
(2) The access and restoration instructions identified in the
Work Instructions of Boeing Alert Service Bulletin 737-53A1204,
Revision 2, dated June 24, 2010; and Boeing Alert Service Bulletin
737-53A1240, Revision 1, dated June 29, 2010; are not required by
this AD. Operators may perform those actions in accordance with
approved maintenance procedures.
(3) 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; and Boeing Alert Service Bulletin
737-53A1240, Revision 1, dated June 29, 2010.
(s) New Initial and Repetitive Inspections of the S-15L Aft Intercostal
and Cargo Barrier Net Fitting for Model 737-200C Series Airplanes
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 the effective date of this AD, 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 (t) of this AD. Repeat the inspections thereafter at
intervals not to exceed 6,000 flight cycles.
(t) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ACO, it may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 2004-09-09,
Amendment 39-13598 (69 FR 23646, April 30, 2004), are approved as
AMOCs for the corresponding requirements of this AD.
(5) AMOCs approved previously in accordance with AD 2005-20-03,
Amendment 39-14296 (70 FR 56361, September 27, 2005), are approved
as AMOCs for the corresponding requirements of this AD, provided the
repetitive inspection intervals (if any) do not exceed 6,000 flight
cycles.
(6) AMOCs approved previously in accordance with AD 2009-16-14,
Amendment 39-15987 (74 FR 38901, August 5, 2009), are approved as
AMOCs for the corresponding requirements of this AD.
(u) Related Information
For more information about this AD, contact Alan Pohl, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind
Avenue SW., Renton, Washington 98057-3356; phone (425) 917-6450; fax
(425) 917-6590; email: Alan.Pohl@faa.gov.
(v) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use the following service information to do the
actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
July 23, 2012.
(i) Boeing Alert Service Bulletin 737-53A1240, Revision 1, dated
June 29, 2010.
(ii) Boeing Alert Service Bulletin 737-53A1204, Revision 2,
dated June 24, 2010.
(4) The following service information was approved for IBR on
September 9, 2009 (74 FR 38901, August 5, 2009).
(i) Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated
March 26, 2007.
(5) The following service information was approved for IBR on
November 1, 2005 (70 FR 56361, September 27, 2005).
(i) Boeing Special Attention Service Bulletin 737-53-1204, dated
June 19, 2003.
(6) The following service information was approved for IBR on
June 4, 2004 (69 FR 23646, April 30, 2004).
(i) Boeing Alert Service Bulletin 737-53A1240, dated April 10,
2003.
(7) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(8) You may review copies of the referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, Washington. For information on the availability of this
material at the FAA, call 425-227-1221.
(9) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr_locations.html.
Issued in Renton, Washington, on June 4, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-14373 Filed 6-15-12; 8:45 am]
BILLING CODE 4910-13-P