Airworthiness Directives; The Boeing Company Airplanes, 57990-57994 [2012-22334]
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57990
Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations
pounds; turkeys and all other poultry—
3 pounds.
*
*
*
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Dated: September 13, 2012.
David R. Shipman,
Administrator, Agricultural Marketing
Service.
[FR Doc. 2012–23083 Filed 9–18–12; 8:45 am]
BILLING CODE 3410–02–P
NATIONAL CREDIT UNION
ADMINISTRATION
12 CFR Part 741
RIN 3133–AD66
Interest Rate Risk Policy and Program
Correction
In rule document 2012–02091,
appearing on pages 55155–5167 in the
issue of Thursday, February 2, 2012,
make the following corrections:
1. On page 5157, in the second
column, in the first line, the text entry
‘‘by asset size cohort at year-end 2010,
as depicted in Table 1:’’ is deleted.
2. On page 5164, in the second
column, under the heading ‘‘Account
Attributes’’ on the second line,
‘‘P\principal’’ should read ‘‘Principal’’.
[FR Doc. C1–2012–2091 Filed 9–18–12; 8:45 am]
BILLING CODE 1505–01–D
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0645; Directorate
Identifier 2011–NM–052–AD; Amendment
39–17190; AD 2012–18–13]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
all The Boeing Company Model 737–
100, –200, –200C, –300, –400, and –500
SUMMARY:
series airplanes. That AD currently
requires repetitive inspections to detect
cracking in the web of the aft pressure
bulkhead at body station 1016 at the aft
fastener row attachment to the ‘‘Y’’
chord, and corrective actions if
necessary. This new AD adds various
inspections for discrepancies at the aft
pressure bulkhead, and related
investigative and corrective actions if
necessary. This AD was prompted by
several reports of fatigue cracking at that
location. We are issuing this AD to
detect and correct such fatigue cracking,
which could result in rapid
decompression of the fuselage.
DATES: This AD is effective October 24,
2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 24, 2012.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of May 10, 1999 (64 FR
19879, April 23, 1999).
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.
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 AD 99–08–23,
Amendment 39–11132 (64 FR 19879,
April 23, 1999). That AD applies to the
specified products. The NPRM
published in the Federal Register on
June 28, 2012 (77 FR 38547). That
NPRM proposed to continue to require
repetitive inspections to detect cracking
in the web of the aft pressure bulkhead
at body station 1016 at the aft fastener
row attachment to the ‘‘Y’’ chord, and
corrective actions if necessary. That
NPRM also proposed to require adding
various inspections for discrepancies at
the aft pressure bulkhead, and related
investigative and corrective actions if
necessary.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comments received.
Boeing supports the NPRM (77 FR
38547, June 28, 2012). Aviation Partners
Boeing stated that it has reviewed the
NPRM and has determined that the
installation of winglets per
supplemental type certificate
ST01219SE does not affect the NPRM.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
We estimate that this AD affects 566
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Low frequency eddy current (LFEC) inspection [retained actions from AD
99-08–23, Amendment 39–11132 (64
FR 19879, April 23, 1999)].
8 work-hours × $85 per hour = $680 .....
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19:23 Sep 18, 2012
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Parts cost
Sfmt 4700
Cost per product
$0
$680 .......................
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Cost on U.S.
operators
$384,880.
Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations
57991
ESTIMATED COSTS—Continued
Labor cost
Detailed visual inspection [retained actions from AD 99-08-23, Amendment
39–11132 (64 FR 19879, April 23,
1999)].
Detailed, high frequency eddy current
inspection, and LFEC inspections of
the web at the ‘‘Y’’ chord of the bulkhead, the web located under the
outer circumferential tear strap, the
‘‘Z’’ stiffeners at the dome cap, and
existing repairs [new action].
2 work-hours × $85 per hour = $170 .....
0
170 .........................
96,220.
Up to 60 work-hours × $85 per hour =
$5,100 per inspection cycle.
0
5,100 per inspection cycle.
2,886,600 per inspection cycle.
We estimate the following costs to do
any necessary on-condition inspections
that would be required based on the
Parts cost
Cost on U.S.
operators
Action
results of the initial inspection. We have
no way of determining the number of
Cost per product
aircraft that might need these
inspections:
ON-CONDITION COSTS
Action
Labor cost
Detailed and HFEC inspections for oil-canning ...........
LFEC or HFEC inspections for cracking ......................
1 work-hour × $85 per hour = $85 ...............................
2 work-hours × $85 per hour = $170 ...........................
We have received no definitive data
that would enable us to provide cost
estimates for the crack repairs specified
in this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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Regulatory Findings
19:23 Sep 18, 2012
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:
■
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
VerDate Mar<15>2010
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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Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
99–08–23, Amendment 39–11132 (64
■
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Cost per
product
Parts cost
$0
0
$85
170
FR 19879, April 23, 1999), and adding
the following new AD:
2012–18–13 The Boeing Company:
Amendment 39–17190; Docket No.
FAA–2012–0645; Directorate Identifier
2011–NM–052–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective October 24, 2012.
(b) Affected ADs
This AD supersedes AD 99–08–23,
Amendment 39–11132 (64 FR 19879, April
23, 1999).
(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 several reports
of fatigue cracks in the aft pressure bulkhead.
We are issuing this AD to detect and correct
such fatigue cracking, which could result in
rapid decompression of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Initial Inspection
This paragraph restates the initial
inspection required by paragraph (a) of AD
99–08–23, Amendment 39–11132 (64 FR
19879, April 23, 1999). Perform either
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Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations
inspection specified by paragraph (g)(1) or
(g)(2) of this AD at the time specified in
paragraph (h) of this AD.
(1) Perform a low frequency eddy current
(LFEC) inspection from the aft side of the aft
pressure bulkhead to detect discrepancies
(including cracking, misdrilled fastener
holes, and corrosion) of the web of the upper
section of the aft pressure bulkhead at body
station 1016 at the aft fastener row
attachment to the ‘‘Y’’ chord, from stringer 15
left (S–15L) to stringer 15 right (S–15R), in
accordance with Boeing 737 Nondestructive
Test Manual D6–37239, Part 6, Section 53–
10–54, dated December 5, 1998.
(2) Perform a detailed visual inspection of
the aft fastener row attachment to the ‘‘Y’’
chord from the forward side of the aft
pressure bulkhead to detect discrepancies
(including cracking, misdrilled fastener
holes, and corrosion) of the entire web of the
aft pressure bulkhead at body station 1016.
(h) Retained Compliance Times
This paragraph restates the compliance
times specified in paragraph (b) of AD 99–
08–23, Amendment 39–11132 (64 FR 19879,
April 23, 1999). Perform the inspection
required by paragraph (g) of this AD at the
time specified in paragraph (h)(1), (h)(2), or
(h)(3) of this AD, as applicable.
(1) For airplanes that have accumulated
40,000 or more total flight cycles as of May
10, 1999 (the effective date of AD 99–08–23,
Amendment 39–11132 (64 FR 19879, April
23, 1999)): Inspect within 375 flight cycles or
60 days after May 10, 1999 (the effective date
of AD 99–08–23), whichever occurs later.
(2) For airplanes that have accumulated
25,000 or more total flight cycles and fewer
than 40,000 total flight cycles as of May 10,
1999 (the effective date of AD 99–08–23,
Amendment 39–11132 (64 FR 19879, April
23, 1999)): Inspect within 750 flight cycles or
90 days after May 10, 1999 (the effective date
of AD 99–08–23), whichever occurs later.
(3) For airplanes that have accumulated
fewer than 25,000 total flight cycles as of
May 10, 1999 (the effective date of AD 99–
08–23, Amendment 39–11132 (64 FR 19879,
April 23, 1999)): Inspect prior to the
accumulation of 25,750 total flight cycles.
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(i) Retained Repetitive Inspections
This paragraph restates the repetitive
inspections required by paragraph (c) of AD
99–08–23, Amendment 39–11132 (64 FR
19879, April 23, 1999). Within 1,200 flight
cycles after performing the initial inspection
required by paragraph (g) of this AD, and
thereafter at intervals not to exceed 1,200
flight cycles: Perform either inspection
specified by paragraph (g)(1) or (g)(2) of this
AD.
(j) Retained Corrective Actions
This paragraph restates the corrective
actions required by paragraph (d) of AD 99–
08–23, Amendment 39–11132 (64 FR 19879,
April 23, 1999). If any discrepancy is
detected during any inspection required by
paragraph (g), (h), or (i) of this AD: Prior to
further flight, accomplish the actions
specified by paragraphs (j)(1) and (j)(3) of this
AD, and paragraph (j)(2) of this AD, if
applicable.
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19:23 Sep 18, 2012
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(1) Perform a high frequency eddy current
inspection from the forward side of the
bulkhead to detect cracking of the web at the
‘‘Y’’ chord attachment, around the entire
periphery of the ‘‘Y’’ chord, in accordance
with Boeing 737 Nondestructive Test Manual
D6–37239, Part 6, Section 51–00–00, Figure
23, dated November 5, 1995.
(2) If the most recent inspection performed
in accordance with paragraph (g) of this AD
was not a detailed visual inspection:
Accomplish the actions specified by
paragraph (g)(2) of this AD. If the inspection
was a detailed visual inspection, it is not
necessary to repeat that inspection prior to
further flight.
(3) Repair any discrepancy such as
cracking or corrosion or misdrilled fastener
holes using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(k) New Requirements: Inspections of the
Web at the ‘‘Y’’ Chord Upper Bulkhead From
S–15L to S–15R
At the later of the times specified in
paragraphs (k)(1) and (k)(2) of this AD: Do
detailed and LFEC inspections of the aft side
of the bulkhead web, or do detailed and
HFEC inspections from the forward side of
the bulkhead, and do all applicable related
investigative and corrective actions; in
accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011, except as required
by paragraphs (r)(1) and (r)(3) of this AD.
Inspect for cracks, incorrectly drilled fastener
holes, and elongated fastener holes. Do all
applicable related investigative and
corrective actions before further flight.
Repeat the inspections at the applicable
times specified in table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
(1) Prior to the accumulation of 25,000
total flight cycles.
(2) Except as required by paragraphs (r)(2)
and (r)(4) of this AD, at the later of the times
specified in the ‘‘Compliance Time’’ column
in table 1 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011.
(l) New Requirements: Inspections of the
Web at the ‘‘Y’’ Chord in the Lower
Bulkhead From S–15L to S–15R
Except as required by paragraphs (r)(2) and
(r)(5) of this AD, at the applicable time
specified in table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do detailed and eddy
current inspections of the web from the
forward or aft side of the bulkhead for cracks,
incorrectly drilled fasteners, and elongated
fasteners, in accordance with Part III of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011, except as required
by paragraphs (r)(1) and (r)(3) of this AD. If
any crack, incorrectly drilled fastener,
elongated fastener, or corrosion is found,
before further flight, repair the web using a
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method approved in accordance with the
procedures specified in paragraph (u) of this
AD. Repeat the inspections at the applicable
times specified in table 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
(m) New Requirements: One-Time Inspection
Under the Tear Strap
Except as required by paragraphs (r)(2) and
(r)(5) of this AD, at the applicable time
specified in table 3 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do a one-time LFEC
inspection for cracks on the aft side of the
bulkhead of the web located under the outer
circumferential tear strap, or do a one-time
HFEC inspection for cracks from the forward
side of the bulkhead of the web located under
the outer circumferential tear strap, in
accordance with Part II of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011, except as required
by paragraph (r)(1) of this AD. If any cracking
is found, before further flight, repair the
bulkhead using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(n) New Requirements: Inspection for OilCanning
Except as required by paragraph (r)(2) of
this AD, at the applicable time specified in
table 4 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011: Do a
detailed inspection from the aft side of the
bulkhead for oil-canning and do all
applicable related investigative and
corrective actions, in accordance with Part II
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, except
as required by paragraph (r)(1) of this AD. Do
all related investigative and corrective
actions before further flight. Thereafter,
repeat the inspection at the applicable times
specified in table 4 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011. For oil-cans found
within the limits specified in Part II of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011: In lieu of installing
the repair before further flight, at the
applicable times specified in table 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, do
initial and repetitive detailed and HFEC
inspections for cracks of the oil-canning and
install the repair, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011. If any crack is
found, before further flight, repair the
cracking using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD. Installing the repair
terminates the repetitive inspections for
cracks.
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(o) New Requirements: Inspection of the
Dome Cap at the Center of the Bulkhead
Except as required by paragraphs (r)(2) and
(r)(5) of this AD, at the applicable time
specified in table 5 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do an eddy current
inspection to detect any cracking of the dome
cap at the center of the bulkhead, and do all
applicable corrective actions, in accordance
with Part IV of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011. Do all corrective actions before
further flight. Repeat the inspection at the
times specified in table 5 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
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(p) New Requirements: Inspection of the
Forward Flange of the ‘‘Z’’ Stiffeners at the
Dome Cap
Except as required by paragraphs (r)(2) and
(r)(5) of this AD, at the applicable time
specified in table 6 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Do an HFEC inspection
to detect any cracking of the ‘‘Z’’ stiffener
flanges at the dome cap in the center of the
bulkhead, in accordance with Part V of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1214, Revision 4,
dated December 16, 2011, except as required
by paragraph (r)(1) of this AD. If any crack
is found, before further flight, repair the
flanges using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD. Repeat the
inspection at the applicable times specified
in table 6 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011.
(q) New Requirements: Inspection for
Existing Repairs on the Bulkhead
Except as required by paragraph (r)(2) of
this AD, at the applicable time specified in
table 7 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011: Do a
detailed inspection of the bulkhead web and
stiffeners for existing repairs, in accordance
with Part VI of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, except as required by paragraph
(r)(1) of this AD.
(1) If any repair identified in the
‘‘Condition’’ column of table 8 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, is found and the
‘‘Reference’’ column refers to Appendix A, B,
C, or D of that service bulletin: At the
applicable times specified in table 8 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011, except
as required by paragraph (r)(2) of this AD, do
a HFEC inspection or a LFEC inspection of
the web for cracking, in accordance with
Appendix A, B, C, or D, as applicable, of
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Boeing Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011. If any
cracking is found, before further flight, repair
using a method approved in accordance with
the procedures specified in paragraph (u) of
this AD. Repeat the inspections, thereafter, at
the applicable intervals specified in table 8
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1214,
Revision 4, dated December 16, 2011.
(2) If any repair identified in the
‘‘Condition’’ column of table 8 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, is found and the
‘‘Reference’’ column refers to Appendix E of
that service bulletin: At the applicable times
specified in table 8 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, except as required by
paragraph (r)(2) of this AD, remove the repair
and replace with a new repair, in accordance
with Appendix E of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011.
(3) If any non-SRM (structural repair
manual) repair is found and the repair does
not have FAA-approved damage tolerance
inspections, except as required by paragraph
(r)(2) of this AD, at the applicable time
specified in table 7 of Paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011: Contact the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
Aircraft Certification Office, for damage
tolerance inspections. Do those damage
tolerance inspections at the times given using
a method approved in accordance with the
procedures specified in paragraph (u) of this
AD.
(r) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, specifies to contact Boeing for
repair instructions: Before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (u) of this AD.
(2) Where Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, specifies a compliance time ‘‘after
the date of Revision 1 to this service
bulletin,’’ ‘‘from the date of Revision 3 of this
service bulletin,’’ ‘‘after the date of Revision
3 to this service bulletin,’’ or ‘‘of the effective
date of AD 99–08–23,’’ this AD requires
compliance within the specified compliance
time after the effective date of this AD.
(3) Access and restoration procedures
specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1214, Revision 4, dated December
16, 2011, are not required by this AD.
Operators may do those procedures following
their maintenance practices.
(4) Where table 1 of paragraph 1.E.,
‘‘Compliance’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, specifies a compliance
time relative to actions done ‘‘in accordance
with paragraph (a)(2) of AD 99–08–23,’’ this
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57993
AD requires compliance within the specified
compliance time relative to actions specified
in paragraph (g)(2) of this AD.
(5) Where the Condition columns in tables
2, 3, 5, and 6 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1214, Revision 4, dated
December 16, 2011, refer to total flight cycles,
this AD applies to the airplanes with the
specified total flight cycles as of the effective
date of this AD.
(s) Terminating Action
Accomplishment of the requirements of
paragraphs (k) through (q) of this AD
terminates the requirements of paragraphs (g)
through (j) of this AD.
(t) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (k) through (s)
of this AD, if the actions were performed
before the effective date of this AD using the
service bulletins specified in paragraphs
(t)(1) through (t)(4) of this AD.
(1) Boeing Alert Service Bulletin 737–
53A1214, dated June 17, 1999.
(2) Boeing Alert Service Bulletin 737–
53A1214, Revision 1, dated June 22, 2000.
(3) Boeing Alert Service Bulletin 737–
53A1214, Revision 2, dated May 24, 2001.
(4) Boeing Alert Service Bulletin 737–
53A1214, Revision 3, dated January 19, 2011.
(u) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in the
Related Information section of this AD.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes ODA that has
been authorized by the Manager, Seattle ACO
to make those findings. For a repair method
to be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously in
accordance with AD 99–08–23, Amendment
39–11132 (64 FR 19879, April 23, 1999), are
approved as AMOCs for the corresponding
provisions of this AD.
(v) Related Information
For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; phone: (425) 917–6440; fax: (425) 917–
6590; email: alan.pohl@faa.gov.
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19SER1
57994
Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations
(w) Material Incorporated by Reference
DEPARTMENT OF TRANSPORTATION
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(3) The following service information was
approved for IBR on October 24, 2012.
(i) Boeing Alert Service Bulletin 737–
53A1214, Revision 4, dated December 16,
2011.
(ii) Reserved.
(4) The following service information was
approved for IBR on May 10, 1999 (64 FR
19879, April 23, 1999).
(i) Boeing 737 Nondestructive Test Manual
D6–37239, Part 6, Section 53–10–54, dated
December 5, 1998.
(ii) Boeing 737 Nondestructive Test
Manual D6–37239, Part 6, Section 51–00–00,
Figure 23, dated November 5, 1995.
(5) For The Boeing Company 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.
(6) 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August
31, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–22334 Filed 9–18–12; 8:45 am]
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0644; Directorate
Identifier 2012–NM–011–AD; Amendment
39–17193; AD 2012–18–16]
RIN 2120–AA64
Airworthiness Directives; The Cessna
Aircraft Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Cessna Aircraft Company Model
750 airplanes. This AD was prompted
by reports of direct current (DC)
generator overvoltage events. This AD
requires replacing the auxiliary power
unit (APU) generator control unit (GCU).
We are issuing this AD to prevent DC
generator overvoltage events, which
could result in smoke in the cockpit and
loss of avionics and electrical systems.
DATES: This AD is effective October 24,
2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of October 24, 2012.
ADDRESSES: For service information
identified in this AD, contact Cessna
Aircraft Co., P.O. Box 7706, Wichita,
Kansas 67277; telephone 316–517–6215;
fax 316–517–5802; email
citationpubs@cessna.textron.com;
Internet https://
www.cessnasupport.com/newlogin.html.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA.
For information on the availability of
this material at the FAA, call 425–227–
1221.
SUMMARY:
Examining the AD Docket
BILLING CODE 4910–13–P
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:
Christine Abraham, Aerospace Engineer,
Electrical Systems and Avionics Branch,
ACE–119W, FAA, Wichita Aircraft
Certification Office, 1801 Airport Road,
Room 100, Mid-Continent Airport,
Wichita, Kansas 67209; telephone: 316–
946–4165; fax: 316–946–4107; email:
christine.abraham@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM published in the Federal
Register on June 25, 2012 (77 FR 37827).
That NPRM proposed to require
replacing the auxiliary power unit
(APU) generator control unit (GCU).
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (77
FR 37827, June 25, 2012) or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Costs of Compliance
We estimate that this AD affects 58
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Labor cost
Replacement .......................................
srobinson on DSK4SPTVN1PROD with RULES
Action
2 work-hours × $85 per hour = $170 .........................
According to the manufacturer, all 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
VerDate Mar<15>2010
19:23 Sep 18, 2012
Jkt 226001
Parts cost
affected individuals. As a result, we
have included all costs in our cost
estimate.
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
$2,400
Cost per
product
Cost on U.S.
operators
$2,570
$149,060
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
E:\FR\FM\19SER1.SGM
19SER1
]]>Agencies
[Federal Register Volume 77, Number 182 (Wednesday, September 19, 2012)]
[Rules and Regulations]
[Pages 57990-57994]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-22334]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0645; Directorate Identifier 2011-NM-052-AD;
Amendment 39-17190; AD 2012-18-13]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and
-500 series airplanes. That AD currently requires repetitive
inspections to detect cracking in the web of the aft pressure bulkhead
at body station 1016 at the aft fastener row attachment to the ``Y''
chord, and corrective actions if necessary. This new AD adds various
inspections for discrepancies at the aft pressure bulkhead, and related
investigative and corrective actions if necessary. This AD was prompted
by several reports of fatigue cracking at that location. We are issuing
this AD to detect and correct such fatigue cracking, which could result
in rapid decompression of the fuselage.
DATES: This AD is effective October 24, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of October 24,
2012.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of May 10,
1999 (64 FR 19879, April 23, 1999).
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 AD 99-08-23, Amendment 39-11132 (64 FR 19879,
April 23, 1999). That AD applies to the specified products. The NPRM
published in the Federal Register on June 28, 2012 (77 FR 38547). That
NPRM proposed to continue to require repetitive inspections to detect
cracking in the web of the aft pressure bulkhead at body station 1016
at the aft fastener row attachment to the ``Y'' chord, and corrective
actions if necessary. That NPRM also proposed to require adding various
inspections for discrepancies at the aft pressure bulkhead, and related
investigative and corrective actions if necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comments received. Boeing supports the
NPRM (77 FR 38547, June 28, 2012). Aviation Partners Boeing stated that
it has reviewed the NPRM and has determined that the installation of
winglets per supplemental type certificate ST01219SE does not affect
the NPRM.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Costs of Compliance
We estimate that this AD affects 566 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Low frequency eddy current 8 work-hours x $85 per $0 $680.............. $384,880.
(LFEC) inspection [retained hour = $680.
actions from AD 99[dash]08-23,
Amendment 39-11132 (64 FR
19879, April 23, 1999)].
[[Page 57991]]
Detailed visual inspection 2 work-hours x $85 per 0 170............... 96,220.
[retained actions from AD hour = $170.
99[dash]08[dash]23, Amendment
39-11132 (64 FR 19879, April
23, 1999)].
Detailed, high frequency eddy Up to 60 work-hours x 0 5,100 per 2,886,600 per
current inspection, and LFEC $85 per hour = $5,100 inspection cycle. inspection cycle.
inspections of the web at the per inspection cycle.
``Y'' chord of the bulkhead,
the web located under the
outer circumferential tear
strap, the ``Z'' stiffeners at
the dome cap, and existing
repairs [new action].
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
inspections that would be required based on the results of the initial
inspection. We have no way of determining the number of aircraft that
might need these inspections:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Detailed and HFEC inspections for oil- 1 work-hour x $85 per hour = $85... $0 $85
canning.
LFEC or HFEC inspections for cracking...... 2 work-hours x $85 per hour = $170. 0 170
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the crack repairs specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
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)
99-08-23, Amendment 39-11132 (64 FR 19879, April 23, 1999), and adding
the following new AD:
2012-18-13 The Boeing Company: Amendment 39-17190; Docket No. FAA-
2012-0645; Directorate Identifier 2011-NM-052-AD.
(a) Effective Date
This airworthiness directive (AD) is effective October 24, 2012.
(b) Affected ADs
This AD supersedes AD 99-08-23, Amendment 39-11132 (64 FR 19879,
April 23, 1999).
(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 several reports of fatigue cracks in the
aft pressure bulkhead. We are issuing this AD to detect and correct
such fatigue cracking, which could result in rapid decompression of
the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Initial Inspection
This paragraph restates the initial inspection required by
paragraph (a) of AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999). Perform either
[[Page 57992]]
inspection specified by paragraph (g)(1) or (g)(2) of this AD at the
time specified in paragraph (h) of this AD.
(1) Perform a low frequency eddy current (LFEC) inspection from
the aft side of the aft pressure bulkhead to detect discrepancies
(including cracking, misdrilled fastener holes, and corrosion) of
the web of the upper section of the aft pressure bulkhead at body
station 1016 at the aft fastener row attachment to the ``Y'' chord,
from stringer 15 left (S-15L) to stringer 15 right (S-15R), in
accordance with Boeing 737 Nondestructive Test Manual D6-37239, Part
6, Section 53-10-54, dated December 5, 1998.
(2) Perform a detailed visual inspection of the aft fastener row
attachment to the ``Y'' chord from the forward side of the aft
pressure bulkhead to detect discrepancies (including cracking,
misdrilled fastener holes, and corrosion) of the entire web of the
aft pressure bulkhead at body station 1016.
(h) Retained Compliance Times
This paragraph restates the compliance times specified in
paragraph (b) of AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999). Perform the inspection required by paragraph (g) of this
AD at the time specified in paragraph (h)(1), (h)(2), or (h)(3) of
this AD, as applicable.
(1) For airplanes that have accumulated 40,000 or more total
flight cycles as of May 10, 1999 (the effective date of AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999)): Inspect within
375 flight cycles or 60 days after May 10, 1999 (the effective date
of AD 99-08-23), whichever occurs later.
(2) For airplanes that have accumulated 25,000 or more total
flight cycles and fewer than 40,000 total flight cycles as of May
10, 1999 (the effective date of AD 99-08-23, Amendment 39-11132 (64
FR 19879, April 23, 1999)): Inspect within 750 flight cycles or 90
days after May 10, 1999 (the effective date of AD 99-08-23),
whichever occurs later.
(3) For airplanes that have accumulated fewer than 25,000 total
flight cycles as of May 10, 1999 (the effective date of AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999)): Inspect prior to
the accumulation of 25,750 total flight cycles.
(i) Retained Repetitive Inspections
This paragraph restates the repetitive inspections required by
paragraph (c) of AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999). Within 1,200 flight cycles after performing the initial
inspection required by paragraph (g) of this AD, and thereafter at
intervals not to exceed 1,200 flight cycles: Perform either
inspection specified by paragraph (g)(1) or (g)(2) of this AD.
(j) Retained Corrective Actions
This paragraph restates the corrective actions required by
paragraph (d) of AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999). If any discrepancy is detected during any inspection
required by paragraph (g), (h), or (i) of this AD: Prior to further
flight, accomplish the actions specified by paragraphs (j)(1) and
(j)(3) of this AD, and paragraph (j)(2) of this AD, if applicable.
(1) Perform a high frequency eddy current inspection from the
forward side of the bulkhead to detect cracking of the web at the
``Y'' chord attachment, around the entire periphery of the ``Y''
chord, in accordance with Boeing 737 Nondestructive Test Manual D6-
37239, Part 6, Section 51-00-00, Figure 23, dated November 5, 1995.
(2) If the most recent inspection performed in accordance with
paragraph (g) of this AD was not a detailed visual inspection:
Accomplish the actions specified by paragraph (g)(2) of this AD. If
the inspection was a detailed visual inspection, it is not necessary
to repeat that inspection prior to further flight.
(3) Repair any discrepancy such as cracking or corrosion or
misdrilled fastener holes using a method approved in accordance with
the procedures specified in paragraph (u) of this AD.
(k) New Requirements: Inspections of the Web at the ``Y'' Chord Upper
Bulkhead From S-15L to S-15R
At the later of the times specified in paragraphs (k)(1) and
(k)(2) of this AD: Do detailed and LFEC inspections of the aft side
of the bulkhead web, or do detailed and HFEC inspections from the
forward side of the bulkhead, and do all applicable related
investigative and corrective actions; in accordance with Part 1 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011, except as required
by paragraphs (r)(1) and (r)(3) of this AD. Inspect for cracks,
incorrectly drilled fastener holes, and elongated fastener holes. Do
all applicable related investigative and corrective actions before
further flight. Repeat the inspections at the applicable times
specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011.
(1) Prior to the accumulation of 25,000 total flight cycles.
(2) Except as required by paragraphs (r)(2) and (r)(4) of this
AD, at the later of the times specified in the ``Compliance Time''
column in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
(l) New Requirements: Inspections of the Web at the ``Y'' Chord in the
Lower Bulkhead From S-15L to S-15R
Except as required by paragraphs (r)(2) and (r)(5) of this AD,
at the applicable time specified in table 2 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do detailed and eddy current
inspections of the web from the forward or aft side of the bulkhead
for cracks, incorrectly drilled fasteners, and elongated fasteners,
in accordance with Part III of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated
December 16, 2011, except as required by paragraphs (r)(1) and
(r)(3) of this AD. If any crack, incorrectly drilled fastener,
elongated fastener, or corrosion is found, before further flight,
repair the web using a method approved in accordance with the
procedures specified in paragraph (u) of this AD. Repeat the
inspections at the applicable times specified in table 2 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011.
(m) New Requirements: One-Time Inspection Under the Tear Strap
Except as required by paragraphs (r)(2) and (r)(5) of this AD,
at the applicable time specified in table 3 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do a one-time LFEC inspection
for cracks on the aft side of the bulkhead of the web located under
the outer circumferential tear strap, or do a one-time HFEC
inspection for cracks from the forward side of the bulkhead of the
web located under the outer circumferential tear strap, in
accordance with Part II of the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011, except as required by paragraph (r)(1) of this AD. If any
cracking is found, before further flight, repair the bulkhead using
a method approved in accordance with the procedures specified in
paragraph (u) of this AD.
(n) New Requirements: Inspection for Oil-Canning
Except as required by paragraph (r)(2) of this AD, at the
applicable time specified in table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do a detailed inspection from
the aft side of the bulkhead for oil-canning and do all applicable
related investigative and corrective actions, in accordance with
Part II of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, except as
required by paragraph (r)(1) of this AD. Do all related
investigative and corrective actions before further flight.
Thereafter, repeat the inspection at the applicable times specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
For oil-cans found within the limits specified in Part II of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011: In lieu of installing
the repair before further flight, at the applicable times specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011,
do initial and repetitive detailed and HFEC inspections for cracks
of the oil-canning and install the repair, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011. If any crack is found,
before further flight, repair the cracking using a method approved
in accordance with the procedures specified in paragraph (u) of this
AD. Installing the repair terminates the repetitive inspections for
cracks.
[[Page 57993]]
(o) New Requirements: Inspection of the Dome Cap at the Center of the
Bulkhead
Except as required by paragraphs (r)(2) and (r)(5) of this AD,
at the applicable time specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do an eddy current inspection
to detect any cracking of the dome cap at the center of the
bulkhead, and do all applicable corrective actions, in accordance
with Part IV of the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011.
Do all corrective actions before further flight. Repeat the
inspection at the times specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011.
(p) New Requirements: Inspection of the Forward Flange of the ``Z''
Stiffeners at the Dome Cap
Except as required by paragraphs (r)(2) and (r)(5) of this AD,
at the applicable time specified in table 6 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do an HFEC inspection to detect
any cracking of the ``Z'' stiffener flanges at the dome cap in the
center of the bulkhead, in accordance with Part V of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011, except as required by
paragraph (r)(1) of this AD. If any crack is found, before further
flight, repair the flanges using a method approved in accordance
with the procedures specified in paragraph (u) of this AD. Repeat
the inspection at the applicable times specified in table 6 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011.
(q) New Requirements: Inspection for Existing Repairs on the Bulkhead
Except as required by paragraph (r)(2) of this AD, at the
applicable time specified in table 7 of paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Do a detailed inspection of the
bulkhead web and stiffeners for existing repairs, in accordance with
Part VI of the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, except as
required by paragraph (r)(1) of this AD.
(1) If any repair identified in the ``Condition'' column of
table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, is found
and the ``Reference'' column refers to Appendix A, B, C, or D of
that service bulletin: At the applicable times specified in table 8
of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011, except as required
by paragraph (r)(2) of this AD, do a HFEC inspection or a LFEC
inspection of the web for cracking, in accordance with Appendix A,
B, C, or D, as applicable, of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011. If any cracking is
found, before further flight, repair using a method approved in
accordance with the procedures specified in paragraph (u) of this
AD. Repeat the inspections, thereafter, at the applicable intervals
specified in table 8 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011.
(2) If any repair identified in the ``Condition'' column of
table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1214, Revision 4, dated December 16, 2011, is found
and the ``Reference'' column refers to Appendix E of that service
bulletin: At the applicable times specified in table 8 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011, except as required by paragraph
(r)(2) of this AD, remove the repair and replace with a new repair,
in accordance with Appendix E of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011.
(3) If any non-SRM (structural repair manual) repair is found
and the repair does not have FAA-approved damage tolerance
inspections, except as required by paragraph (r)(2) of this AD, at
the applicable time specified in table 7 of Paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214,
Revision 4, dated December 16, 2011: Contact the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) that has been
authorized by the Manager, Seattle Aircraft Certification Office,
for damage tolerance inspections. Do those damage tolerance
inspections at the times given using a method approved in accordance
with the procedures specified in paragraph (u) of this AD.
(r) Exceptions to the Service Information
(1) Where Boeing Alert Service Bulletin 737-53A1214, Revision 4,
dated December 16, 2011, specifies to contact Boeing for repair
instructions: Before further flight, repair using a method approved
in accordance with the procedures specified in paragraph (u) of this
AD.
(2) Where Boeing Alert Service Bulletin 737-53A1214, Revision 4,
dated December 16, 2011, specifies a compliance time ``after the
date of Revision 1 to this service bulletin,'' ``from the date of
Revision 3 of this service bulletin,'' ``after the date of Revision
3 to this service bulletin,'' or ``of the effective date of AD 99-
08-23,'' this AD requires compliance within the specified compliance
time after the effective date of this AD.
(3) Access and restoration procedures specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1214, Revision 4, dated December 16, 2011, are not required by
this AD. Operators may do those procedures following their
maintenance practices.
(4) Where table 1 of paragraph 1.E., ``Compliance'' of Boeing
Alert Service Bulletin 737-53A1214, Revision 4, dated December 16,
2011, specifies a compliance time relative to actions done ``in
accordance with paragraph (a)(2) of AD 99-08-23,'' this AD requires
compliance within the specified compliance time relative to actions
specified in paragraph (g)(2) of this AD.
(5) Where the Condition columns in tables 2, 3, 5, and 6 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1214, Revision 4, dated December 16, 2011, refer to total
flight cycles, this AD applies to the airplanes with the specified
total flight cycles as of the effective date of this AD.
(s) Terminating Action
Accomplishment of the requirements of paragraphs (k) through (q)
of this AD terminates the requirements of paragraphs (g) through (j)
of this AD.
(t) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (k) through (s) of this AD, if the actions were performed
before the effective date of this AD using the service bulletins
specified in paragraphs (t)(1) through (t)(4) of this AD.
(1) Boeing Alert Service Bulletin 737-53A1214, dated June 17,
1999.
(2) Boeing Alert Service Bulletin 737-53A1214, Revision 1, dated
June 22, 2000.
(3) Boeing Alert Service Bulletin 737-53A1214, Revision 2, dated
May 24, 2001.
(4) Boeing Alert Service Bulletin 737-53A1214, Revision 3, dated
January 19, 2011.
(u) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the manager of the
ACO, send it to the attention of the person identified in the
Related Information section of this AD. Information may be emailed
to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes ODA that has been authorized by the
Manager, Seattle ACO to make those findings. For a repair method to
be approved, the repair must meet the certification basis of the
airplane, and the approval must specifically refer to this AD.
(4) AMOCs approved previously in accordance with AD 99-08-23,
Amendment 39-11132 (64 FR 19879, April 23, 1999), are approved as
AMOCs for the corresponding provisions of this AD.
(v) Related Information
For more information about this AD, contact Alan Pohl, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: (425) 917-6440; fax: (425) 917-6590; email:
alan.pohl@faa.gov.
[[Page 57994]]
(w) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
October 24, 2012.
(i) Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated
December 16, 2011.
(ii) Reserved.
(4) The following service information was approved for IBR on
May 10, 1999 (64 FR 19879, April 23, 1999).
(i) Boeing 737 Nondestructive Test Manual D6-37239, Part 6,
Section 53-10-54, dated December 5, 1998.
(ii) Boeing 737 Nondestructive Test Manual D6-37239, Part 6,
Section 51-00-00, Figure 23, dated November 5, 1995.
(5) For The Boeing Company 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.
(6) 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.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August 31, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-22334 Filed 9-18-12; 8:45 am]
BILLING CODE 4910-13-P
