[Federal Register Volume 78, Number 90 (Thursday, May 9, 2013)]
[Rules and Regulations]
[Pages 27020-27025]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-09113]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1316; Directorate Identifier 2012-NM-186-AD;
Amendment 39-17429; AD 2012-18-13 R1]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are revising an existing airworthiness directive (AD) for
all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series
[[Page 27021]]
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, various
inspections for discrepancies at the aft pressure bulkhead, and related
investigative and corrective actions if necessary. This new AD requires
clarifying certain actions specified in the existing AD. 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.
DATES: This AD is effective June 13, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 24,
2012 (77 FR 57990, September 19, 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 http://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: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to revise AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). That AD applies to all The Boeing Company Model
737-100, -200, -200C, -300, -400, and -500 series airplanes. (AD 2012-
18-13 superseded AD 99-08-23, Amendment 39-11132 (64 FR 19879, April
23, 1999)). The NPRM published in the Federal Register on January 9,
2013 (78 FR 1772). 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, various inspections for discrepancies at the aft pressure
bulkhead, and related investigative and corrective actions if
necessary. That NPRM also proposed to clarify certain actions specified
in the existing AD.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(78 FR 1772, January 9, 2013) and the FAA's response to each comment.
Supportive Comment
The Boeing Company stated that it supports the NPRM (78 FR 1772,
January 9, 2013).
Supplemental Type Certificate (STC) Comment
Aviation Partners Boeing stated that the installation of winglets
per STC ST01219SE (http://rgl.faa.gov/Regulatory--and--Guidance--
Library/rgstc.nsf/0/2c6e3dbddd36f91c862576a4005d64e2/$FILE/
ST01219SE.pdf) does not affect the accomplishment of the manufacturer's
service instructions.
We have added paragraph (c)(2) of this AD to state that
installation of STC ST01219SE (http://rgl.faa.gov/Regulatory--and--
Guidance--Library/rgstc.nsf/0/2c6e3dbddd36f91c862576a4005d64e2/$FILE/
ST01219SE.pdf) does not affect the ability to accomplish the actions
required by this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' AMOC approval request is not
necessary to comply with the requirements of 14 CFR 39.17.
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 change described previously-and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 1772, January 9, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 1772, January 9, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Costs of Compliance
We estimate that this AD affects 566 airplanes of U.S. registry.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Low frequency eddy current (LFEC) 8 work-hours x $85 per $0 $680................ $384,880.
inspection [retained action from hour = $680.
AD 99-08-23, Amendment 39-11132
(64 FR 19879, April 23, 1999)].
Detailed visual inspection 2 work-hours x $85 per 0 $170................ $96,220.
[retained action from AD hour = $170.
99[dash]08-23, Amendment 39-
11132 (64 FR 19879, April 23,
1999)].
[[Page 27022]]
Detailed, high frequency eddy Up to 60 work-hours x $85 0 Up to $5,100 per Up to $2,886,600
current (HFEC), and LFEC per hour = $5,100 per inspection cycle. per inspection
inspections of the web at the inspection cycle. 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
[retained actions from AD 2012-
18-13, Amendment 39-17190 (77 FR
57990, September 19, 2012)].
----------------------------------------------------------------------------------------------------------------
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-canning. 1 work-hour x $85 per hour = $85...... $0 $85
LFEC or HFEC inspection 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)
2012-18-13, Amendment 39-17190 (77 FR 57990, September 19, 2012), and
adding the following new AD:
2012-18-13 R1 The Boeing Company: Amendment 39-17429; Docket No.
FAA-2012-1316; Directorate Identifier 2012-NM-186-AD.
(a) Effective Date
This AD is effective June 13, 2013.
(b) Affected ADs
This AD revises AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012).
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (http://rgl.faa.gov/Regulatory--and--Guidance--Library/
rgstc.nsf/0/2c6e3dbddd36f91c862576a4005d64e2/$FILE/ST01219SE.pdf)
does not affect the ability to accomplish the actions required by
this AD. Therefore, for airplanes on which STC ST01219SE is
installed, a ``change in product'' alternative method of compliance
(AMOC) approval request is not necessary to comply with the
requirements of 14 CFR 39.17.
(d) Subject
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
[[Page 27023]]
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 (g) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). Perform either 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 (h) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). 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 (i) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). 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 (j) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). 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) Retained Inspections of the Web at the ``Y'' Chord Upper Bulkhead
From S-15L to S-15R
This paragraph restates the inspections of the web at the ``Y''
chord upper bulkhead from S-15L to S-15R required by paragraph (k)
of AD 2012-18-13, Amendment 39-17190 (77 FR 57990, September 19,
2012). 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 high frequency eddy current
(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) Retained Inspections of the Web at the ``Y'' Chord in the Lower
Bulkhead From S-15L to S-15R With Revised Inspection and Repair
Conditions
This paragraph restates the inspections of the web at the ``Y''
chord in the lower bulkhead from S-15L to S-15R required by
paragraph (l) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012), with revised inspection and repair conditions.
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 fastener holes, and elongated
fastener holes, 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
hole, elongated fastener hole, or corrosion 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 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) Retained One-Time Inspection Under the Tear Strap
This paragraph restates the one-time inspection under the tear
strap required by paragraph (m) of AD 2012-18-13, Amendment 39-17190
(77 FR 57990, September 19, 2012). 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) Retained Inspection for Oil-Canning
This paragraph restates the inspection for oil-canning required
by paragraph (n) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012). 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
[[Page 27024]]
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.
(o) Retained Inspection of the Dome Cap at the Center of the Bulkhead
This paragraph restates the inspection of the dome cap at the
center of the bulkhead required by paragraph (o) of AD 2012-18-13,
Amendment 39-17190 (77 FR 57990, September 19, 2012). 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) Retained Inspection of the Forward Flange of the ``Z'' Stiffeners
at the Dome Cap
This paragraph restates the inspection of the forward flange of
the ``Z'' stiffeners at the dome cap required by paragraph (p) of AD
2012-18-13, Amendment 39-17190 (77 FR 57990, September 19, 2012).
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) Retained Inspection for Existing Repairs on the Bulkhead
This paragraph restates the inspection for existing repairs on
the bulkhead required by paragraph (q) of AD 2012-18-13, Amendment
39-17190 (77 FR 57990, September 19, 2012). 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 an HFEC inspection or an 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
(ACO), 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) Retained Exceptions to the Service Information
This paragraph restates the exceptions to the service
information required by paragraph (r) of AD 2012-18-13, Amendment
39-17190 (77 FR 57990, September 19, 2012).
(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 October 24, 2012 (the effective date of AD 2012-18-13,
Amendment 39-17190 (77 FR 57990, September 19, 2012)).
(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 October 24, 2012 (the effective date of AD
2012-18-13, Amendment 39-17190 (77 FR 57990, September 19, 2012)).
(s) Retained Terminating Action With Revised Paragraph Reference
This paragraph restates the terminating action specified in
paragraph (s) of AD 2012-18-13, Amendment 39-17190 (77 FR 57990,
September 19, 2012), with a revised paragraph reference.
Accomplishment of the requirements in paragraph (k) of this AD
terminates the requirements of paragraphs (g) through (j) of this
AD.
[[Page 27025]]
(t) Credit for Previous Actions
This paragraph restates the credit for previous actions
specified by paragraph (t) of AD 2012-18-13, Amendment 39-17190 (77
FR 57990, September 19, 2012). 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.
(5) AMOCs approved previously in accordance with AD 2012-18-13,
Amendment 39-17190 (77 FR 57990, September 19, 2012), are approved
as AMOCs for the corresponding provisions of this AD.
(v) Related Information
(1) 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:
[email protected].
(2) 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.
(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 (77 FR 57990, September 19, 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 Boeing 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on April 5, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-09113 Filed 5-8-13; 8:45 am]
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