[Federal Register Volume 78, Number 90 (Thursday, May 9, 2013)]
[Rules and Regulations]
[Pages 27001-27005]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-10005]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1161; Directorate Identifier 2011-NM-277-AD;
Amendment 39-17442; AD 2013-09-01]
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 superseding an existing airworthiness directive (AD)
for certain The Boeing Company Model 737-200, -200C, -300, -400, and -
500 series airplanes. That AD currently requires a one-time mid-
frequency eddy current (MFEC) inspection, a low-frequency eddy current
(LFEC) inspection, and a detailed inspection for damage or cracking of
stringer S-4L and S-4R lap joints and stringer clips between body
station (BS) 540 and BS 727, and follow-on inspections and repair if
necessary. This new AD instead requires repetitive external eddy
current inspections for cracking of certain fuselage crown lap joints,
and corrective actions if necessary; internal eddy current and detailed
inspections for cracking of certain fuselage crown lap joints, and
repair if necessary; and detailed inspections of certain stringer
clips, and replacement with new stringer clips if necessary. This AD
also adds airplanes to the applicability. This AD was prompted by
reports of cracking of the lap joint lower row. We are issuing this AD
to detect and correct cracking of the fuselage lap joints, which could
result in sudden decompression of the airplane.
DATES: This AD is effective June 13, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publication listed in the AD as of June 13, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of May
17, 2002 (67 FR 17917, April 12, 2002).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data
[[Page 27002]]
& Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 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, WA. 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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; 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 supersede AD 2003-08-15, Amendment 39-13128 (68 FR 20341,
April 25, 2003). That AD applies to the specified products. The NPRM
published in the Federal Register on November 7, 2012 (77 FR 66757).
That NPRM proposed to require repetitive external eddy current
inspections for cracking of certain fuselage crown lap joints and
corrective actions; internal eddy current and detailed inspections for
cracking of certain fuselage crown lap joints, and repair if necessary;
and detailed inspections of certain stringer clips, and replacement
with new stringer clips if necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 66757, November 7, 2012) and the FAA's response to each comment.
Support of NPRM (77 FR 66757, November 7, 2012)
Ann Harrison stated that she supports the NPRM (77 FR 66757,
November 7, 2012).
Request for Clarification of Inspection Requirements
Boeing and Lufthansa requested clarification that the repetitive
inspections referred to in paragraph (i)(3) of the NPRM (77 FR 66757,
November 7, 2012) are external inspections. The commenters noted that
the internal inspection specified in Boeing Alert Service Bulletin 737-
53A1255, Revision 2, dated August 7, 2012, is a one-time inspection.
Lufthansa suggested we delete paragraph (i)(3) from the NPRM. Boeing
suggested we revise paragraph (i)(3) of the NPRM to state that the
repetitive inspection is external.
We agree that clarification is needed. The internal inspection is
required only once prior to the accomplishment of the lap splice
modification. Since the external inspection specified in paragraph (g)
of this AD is repetitive, we have deleted paragraph (i)(3) of this AD.
Request To Use Previous Alternative Methods of Compliance (AMOCs)
Alaska Airlines requested that we change the NPRM (77 FR 66757,
November 7, 2012) to state that ``AMOCs approved previously in
accordance with AD 2003-08-15 [(68 FR 20341, April 25, 2003)] and AD
2004-18-06 [(69 FR 54206, September 8, 2004)] are approved as AMOCs for
the corresponding provisions of this AD.'' Alaska Airlines stated that
there is a global AMOC for the PEMCO main deck cargo door installation
in accordance with supplemental type certificate (STC) SA2969SO (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2A10F5D4090A534686257A79006F0F97?OpenDocument&Highlight=stcsa2969so).
The commenter stated that since the STC is not a repair, this global
AMOC should be specified in paragraph (n) of the NPRM.
We agree with the request to include in the AD previously approved
AMOCs for the corresponding requirements of this AD. Installation of
the PEMCO main deck cargo door done in accordance with STC SA2969SO
(http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2A10F5D4090A534686257A79006F0F97?OpenDocument&Highlight=stcsa2969so)
involves installation of an external doubler onto the existing skin and
lap splices from stringer S-3R to S-23L between body station (BS) 312
and BS 500B. We have added new paragraph (n)(6) to this AD to state
that installation of STC SA2969SO is approved as an AMOC to the
corresponding requirements of paragraphs (g) and (i) of this AD from
stringer S-3R to S-23L between BS 312 and BS 500B only.
Boeing requested that we revise paragraph (n)(4) of the NPRM (77 FR
66757, November 7, 2012) to add references to paragraphs (g) and (h) of
AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002), in
order to provide approval for lap joint modifications that have been
approved as AMOCs to paragraphs (g) and (h) of AD 2002-07-08.
We agree with the request. Lap joints modified prior to the
effective date of this AD that have been approved as an AMOC for
paragraphs (g) and (h) of AD 2002-07-08, Amendment 39-12702 (67 FR
17917, April 12, 2002), should not be subject to the lap joint
inspections required by this AD. We have added references to paragraphs
(g) and (h) of AD 2002-07-08 to paragraph (n)(4) of this AD.
STC Winglet 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?OpenDocument&Highlight=st01219se) does
not affect the accomplishment of the manufacturer's service
instructions.
We have added paragraph (c)(2) to this AD to state that
installation of STC ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) 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. For all other AMOC requests, the
operator must request approval for an AMOC in accordance with the
procedures specified in paragraph (n) of this AD.
Request To Clarify Locations of Optional Internal Inspections
Boeing requested that we include further clarification in paragraph
(h) of the NPRM (77 FR 66757, November 7, 2012) indicating that the
optional internal inspections are for cracks between tear straps only.
Boeing stated that paragraph (g) of the NPRM inspects for cracking at
tear strap locations and
[[Page 27003]]
between tear straps. Boeing also stated that paragraph (h) of the NPRM
provides an optional inspection for the inspections required by
paragraph (g), but only for cracking between tear straps. Boeing added
that it is important to clarify that the inspections required by
paragraph (h) of the NPRM are only applicable at locations between tear
straps.
We agree that the requested wording will further clarify the
location for the optional internal inspections specified in paragraph
(h) of this AD. We have added the phrase ``between tear straps'' to the
beginning of the first sentence of paragraph (h) of this AD.
Boeing also requested that we clarify paragraph (j) of the NPRM (77
FR 66757, November 7, 2012) to indicate that the optional internal
inspections are for cracks at tear strap locations. Boeing added that
the wording in the NPRM only allows this confirmation when
accomplishing the internal inspections specified in paragraph (i) of
the NPRM. Boeing stated that Boeing Alert Service Bulletin 737-53A1255,
Revision 2, dated August 7, 2012, specifies that this optional
inspection at tear strap locations is for cracks found during either
the external inspection specified in paragraph (g) of the NPRM, or the
internal inspections specified in paragraph (i) of the NPRM.
We agree that adding a reference to the tear strap location near
the beginning of the first sentence of paragraph (j) of this AD will
clarify the requirement. We have revised paragraph (j) of this AD
accordingly. We have also added a reference to paragraph (g) of this
AD, as requested by the commenter.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 66757, November 7, 2012) for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 66757, November 7, 2012).
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 307 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
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Cost per Number of Cost on U.S.
Action Labor cost Parts cost product airplanes operators
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Internal inspection............................ Up to 303 work-hours x $85 per hour = $0 $25,755 307 $7,906,785
$25,755.
External inspection............................ Up to 10 work-hours x $85 per hour = 0 850 307 260,950
$850.
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We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
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)
2003-08-15, Amendment 39-13128 (68 FR 20341, April 25, 2003), and
adding the following new AD:
2013-09-01 The Boeing Company: Amendment 39-17442; Docket No. FAA-
2012-1161; Directorate Identifier 2011-NM-277-AD.
(a) Effective Date
This AD is effective June 13, 2013.
(b) Affected ADs
This AD supersedes AD 2003-08-15, Amendment 39-13128 (68 FR
20341, April 25, 2003).
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-200, -200C,
-300, -400, and -500 series airplanes; certificated in any category;
as specified in Boeing Alert Service Bulletin 737-53A1255, Revision
2, dated August 7, 2012.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se)
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
[[Page 27004]]
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 reports of cracking of the lap joint
lower row. We are issuing this AD to detect and correct cracking of
the fuselage lap joints, which could result in sudden decompression
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) External Crown Lap Joint Inspection and Repair
For airplanes on which the lap splice modification specified in
AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002), has
not been accomplished, except as required by paragraphs (l)(1) and
(l)(2) of this AD: At the applicable times specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1255,
Revision 2, dated August 7, 2012, do an external eddy current
inspection for cracking in the crown lap joints, except as provided
by paragraphs (h) and (j) of this AD, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1255, Revision 2, dated August 7, 2012. At the intervals
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1255, Revision 2, dated August 7, 2012, repeat the
inspections, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated August
7, 2012. If any cracking is found in a lap joint, before further
flight, repair, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated
August 7, 2012.
(h) Optional Internal Inspections for Mid-bay Fastener Locations
As an option to confirm cracks found between tear straps during
the inspections required by paragraph (g) of this AD, do an internal
mid-frequency eddy current (MFEC) inspection for cracking in the lap
joint fastener row between tear straps of the crown lap and do a
detailed inspection of the lap joint lower fastener row for
cracking, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated August
7, 2012.
(i) Internal Crown Lap Joint Inspection and Repair
For airplanes on which the lap splice modification specified in
AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002), has
not been accomplished: At the times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1255,
Revision 2, dated August 7, 2012, except as required by paragraphs
(l)(1) and (l)(2) of this AD, do an internal MFEC, low frequency
eddy current (LFEC), and detailed inspection for cracking in the
crown lap joints and stringer clips, except as provided by paragraph
(j) of this AD, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated
August 7, 2012.
(1) If any cracking is found in any lap joint, before further
flight, repair, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated
August 7, 2012.
(2) If any cracking is found in any stringer clip, before
further flight, replace the stringer clip with a new stringer clip,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1255, Revision 2, dated August 7, 2012.
(j) Optional Inspections for Tear Strap Locations Only
As an option to confirm cracks found at tear strap locations
while doing the inspections required by paragraph (g) or (i) of this
AD, do an open-hole inspection for cracking at the tear strap
locations, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated August
7, 2012.
(k) Terminating Action
(1) Accomplishing a repair of a crown lap joint in accordance
with Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated
August 7, 2012, terminates the inspections required by paragraphs
(g) and (i) of this AD for the repaired area only.
(2) Accomplishing the modification of the crown lap joints in
accordance with any of the service bulletins specified in paragraphs
(k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD terminates the
inspections required by paragraphs (g) and (i) of this AD for the
modified area only.
(i) Boeing Service Bulletin 737-53A1177, Revision 4, dated
September 2, 1999.
(ii) Boeing Service Bulletin 737-53A1177, Revision 5, dated
February 15, 2001.
(iii) Boeing Service Bulletin 737-53A1177, Revision 6, dated May
31, 2001.
(l) Exceptions to Service Information
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1255, Revision 2, dated August 7, 2012,
specifies a compliance time ``from the Revision 1 date of this
service bulletin,'' this AD requires a compliance time ``after the
effective date of this AD.''
(2) Where the ``Condition'' column, in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1255,
Revision 2, dated August 7, 2012, specifies airplanes with certain
flight cycles ``at the Revision 1 date of this service bulletin,''
for this AD the condition is for airplanes with corresponding flight
cycles ``as of the effective date of this AD.''
(m) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g), (h), (i), and (j) of this AD, if those actions were
performed before the effective date of this AD using Boeing Alert
Service Bulletin 737-53A1255, Revision 1, dated November 7, 2011,
which is not incorporated by reference in this AD.
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved for paragraphs (a), (b), (c), (d), (e), (g),
and (h) of AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12,
2002), before the effective date of this AD, are approved for the
corresponding requirements of paragraphs (g), (i), and (k) of this
AD.
(5) As of the effective date of this AD, any AMOCs approved for
paragraphs (g) and (i) of this AD are approved as AMOCs for the
corresponding requirements of paragraphs (a), (b), (c), (d), and (e)
of AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002).
(6) As of the effective date of this AD, installation of STC
SA2969SO (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/2A10F5D4090A534686257A79006F0F97?OpenDocument&Highlight=stc
sa2969so) is approved as an AMOC for the corresponding requirements
of paragraphs (g) and (i) of this AD from stringer S-3R to S-23L
between body station (BS) 312 and BS 500B only.
(o) Related Information
(1) For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6447; 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, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference
[[Page 27005]]
(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
June 13, 2013.
(i) Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated
August 7, 2012.
(ii) Reserved.
(4) The following service information was approved for IBR on
May 17, 2002 (67 FR 17917, April 12, 2002).
(i) Boeing Service Bulletin 737-53A1177, Revision 4, dated
September 2, 1999.
(ii) Boeing Service Bulletin 737-53A1177, Revision 5, dated
February 15, 2001.
(iii) Boeing Service Bulletin 737-53A1177, Revision 6, dated May
31, 2001.
(5) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet 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, WA. For information on the availability of this material at
the FAA, call 425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on April 18, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-10005 Filed 5-8-13; 8:45 am]
BILLING CODE 4910-13-P