Airworthiness Directives; The Boeing Company Airplanes, 27001-27005 [2013-10005]
Download as PDF
<![CDATA[
27001
Rules and Regulations
Federal Register
Vol. 78, No. 90
Thursday, May 9, 2013
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF AGRICULTURE
Animal and Plant Health Inspection
Service
9 CFR Part 11
[Docket No. APHIS–2011–0030]
RIN 0579–AD43
Horse Protection Act; Requiring Horse
Industry Organizations To Assess and
Enforce Minimum Penalties for
Violations; Correction
Animal and Plant Health
Inspection Service, USDA.
ACTION: Correcting amendment.
AGENCY:
In a final rule that was
published in the Federal Register on
June 7, 2012, and effective on July 9,
2012, we amended the horse protection
regulations to require horse industry
organizations or associations that
license Designated Qualified Persons to
assess and enforce minimum penalties
for violations of the Horse Protection
Act. This document corrects an error in
that final rule.
DATES: Effective May 9, 2013.
FOR FURTHER INFORMATION CONTACT: Dr.
Rachel Cezar, Horse Protection National
Coordinator, Animal Care, APHIS, 4700
River Road, Unit 84, Riverdale, MD
20737; (301) 851–3746.
SUPPLEMENTARY INFORMATION:
SUMMARY:
the minimum penalties in a new
§ 11.25.
As part of this change, we amended
paragraph (d) of § 11.21 to indicate that
horse industry organizations or
associations are required to assess and
enforce penalties for violations in
accordance with § 11.25. Before the
publication of the June 2012 final rule,
this paragraph also indicated that horse
industry organizations or associations
had to report all violations in
accordance with § 11.20(b)(3). However,
in revising § 11.21(d) to reflect the new
minimum penalty requirements, we
erroneously changed the paragraph
reference in the existing reporting
requirement to § 11.20(b)(4), which does
not exist. This document corrects that
error.
List of Subjects in 9 CFR Part 11
Animal welfare, Horses, Reporting
and recordkeeping requirements.
Accordingly, 9 CFR part 11 is
corrected by making the following
correcting amendment:
PART 11—HORSE PROTECTION
REGULATIONS
1. The authority citation for part 11
continues to read as follows:
■
Authority: 15 U.S.C. 1823–1825 and 1828;
7 CFR 2.22, 2.80, and 371.7.
§ 11.21
[Amended]
2. In § 11.21, paragraph (d), the
citation ‘‘§ 11.20(b)(4)’’ is removed and
the citation ‘‘§ 11.20(b)(3)’’ is added in
its place.
■
Done in Washington, DC, this 3rd day of
May 2013.
Kevin Shea,
Acting Administrator, Animal and Plant
Health Inspection Service.
tkelley on DSK3SPTVN1PROD with RULES
Background
[FR Doc. 2013–11028 Filed 5–8–13; 8:45 am]
In a final rule that was published in
the Federal Register on June 7, 2012 (77
FR 33607–33619, Docket No. APHIS–
2011–0030), and effective on July 9,
2012, we amended the horse protection
regulations in 9 CFR part 11 to require
horse industry organizations or
associations that license Designated
Qualified Persons to assess and enforce
minimum penalties for violations of the
Horse Protection Act. We established
BILLING CODE 3410–34–P
VerDate Mar<15>2010
15:51 May 08, 2013
Jkt 229001
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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 lowfrequency 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
SUMMARY:
E:\FR\FM\09MYR1.SGM
09MYR1
27002
Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations
& 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 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:
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:
wayne.lockett@faa.gov.
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.
tkelley on DSK3SPTVN1PROD with RULES
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.
VerDate Mar<15>2010
15:51 May 08, 2013
Jkt 229001
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 (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/2A10F5D4090A5346
86257A79006F0F97?
OpenDocument&Highligh
t=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 (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/2A10F5D4090A5346
86257A79006F0F97?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
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
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 (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/2C6E3DBDDD36F91C8
62576A4005D64E2?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 (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/
rgstc.nsf/0/2C6E3DBDDD36F
91C862576A4005D64E2?
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
E:\FR\FM\09MYR1.SGM
09MYR1
27003
Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations
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
Action
Labor cost
Internal inspection .........
External inspection ........
Up to 303 work-hours × $85 per hour = $25,755
Up to 10 work-hours × $85 per hour = $850 ......
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this AD.
tkelley on DSK3SPTVN1PROD with RULES
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
VerDate Mar<15>2010
15:51 May 08, 2013
Jkt 229001
Cost per
product
Parts cost
$0
0
Number of
airplanes
$25,755
850
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.
§ 39.13
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
307
307
Cost on
U.S. operators
$7,906,785
260,950
(c) Applicability
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
[Amended]
2. The FAA amends § 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).
(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 (https://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
E:\FR\FM\09MYR1.SGM
09MYR1
27004
Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations
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.
tkelley on DSK3SPTVN1PROD with RULES
(h) Optional Internal Inspections for Midbay 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
VerDate Mar<15>2010
15:51 May 08, 2013
Jkt 229001
(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,
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
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: 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 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 (https://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: wayne.lockett@faa.gov.
(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
E:\FR\FM\09MYR1.SGM
09MYR1
Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations
(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: https://
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0845; Directorate
Identifier 2012–CE–013–AD; Amendment
39–17431; AD 2013–08–14]
RIN 2120–AA64
Airworthiness Directives; Revo,
Incorporated Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
tkelley on DSK3SPTVN1PROD with RULES
AGENCY:
Examining the AD Docket
We are superseding an
existing airworthiness directive (AD) for
certain Revo, Incorporated Models
COLONIAL C–1, COLONIAL C–2, LAKE
LA–4, LAKE LA–4A, LAKE LA–4P, and
SUMMARY:
VerDate Mar<15>2010
15:51 May 08, 2013
LAKE LA–4–200 airplanes. That AD
currently requires a one-time, dyepenetrant inspection of the horizontal
stabilizer attachment fitting and
repetitive visual inspections of the
fitting for any evidence of fretting,
cracking, or corrosion (with necessary
replacement and modification);
replacement of the fitting upon reaching
the 850-hours time-in-service (TIS) safe
life; and reporting to the FAA the results
of the initial inspection and any cracks
found on repetitive inspections. This
new AD requires the same actions of AD
2005–12–02 except using revised
service documents and procedures, adds
Model COLONIAL C–1 airplanes to the
Applicability, and adds an optional
terminating action for the requirements.
This AD was prompted by a report from
Revo, Incorporated that, while the
drawing numbers are different, the
attachment fittings on the Model
COLONIAL C–1 airplanes are identical
in every other respect to those installed
on the airplanes referenced in AD 2005–
12–02. We are issuing this AD to correct
the unsafe condition on these products.
DATES: This AD is effective June 13,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications 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
the AD as of July 8, 2005 (70 FR 33820,
June 10, 2005).
ADDRESSES: For service information
identified in this AD, contact Revo,
Incorporated, 1396 Grandview
Boulevard, Kissimmee, FL 34744;
telephone: (407) 847–8080; email:
support@teamlake.com; Lake Central
Air Services, Muskoka Airport, R. R. #1,
Gravenhurst, Ontario, Canada P1P 1R1;
telephone: (705) 687–4343; email:
akecent@muskoka.com; Internet:
www.lakecentral.com; and Robert L.
Copeland (XLS Co., LLC), 418B Bartow
Municipal Airport, Bartow, FL 33830;
FAA Aerospace Engineer (Hal
Horsburgh), telephone: (404) 474–5553.
You may review copies of the
referenced service information at the
FAA, Small Airplane Directorate, 901
Locust St., Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148.
Jkt 229001
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
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
27005
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: Hal
Horsburgh, Aerospace Engineer, Atlanta
Aircraft Certification Office, FAA, 1701
Columbia Avenue, College Park, Georgia
30337; phone: (404) 474–5553; fax: (404)
474–5606; email:
hal.horsburgh@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2005–12–02,
amendment 39–14118 (70 FR 33820,
June 10, 2005). That AD applies to the
specified products. The NPRM
published in the Federal Register on
August 16, 2012 (77 FR 49389). That
NPRM proposed to require the same
actions of AD 2005–12–02, add Model
COLONIAL C–1 airplanes to the
Applicability, and add an optional
terminating action for the requirements.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (77
FR 49389, August 16, 2012) or on the
determination of the cost to the public.
We did notice that the date for XLS
Company’s instructions for continued
airworthiness was incorrect. We also
identified the need to clarify giving
credit for work done following previous
service documents and procedures so
the actions would not be unnecessarily
duplicated.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting the AD
as proposed except for a typographical
error in the date for XLS Company’s
instructions for continued
airworthiness, clarification of credit
allowed for work done following
previous service documents and
procedures, and minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM (August 16,
2012, 77 FR 49389) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
E:\FR\FM\09MYR1.SGM
09MYR1
]]>Agencies
[Federal Register Volume 78, Number 90 (Thursday, May 9, 2013)]
[Rules and Regulations]
[Pages 27001-27005]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-10005]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 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: 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: wayne.lockett@faa.gov.
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 (https://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
(https://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 (https://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 (https://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
--------------------------------------------------------------------------------------------------------------------------------------------------------
Cost per Number of Cost on U.S.
Action Labor cost Parts cost product airplanes operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
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.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 (https://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: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved 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 (https://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:
wayne.lockett@faa.gov.
(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: https://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
