Airworthiness Directives; The Boeing Company Model 737-200, -200C, -300, -400, and -500 Series Airplanes, 74667-74670 [2011-30608]
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Federal Register / Vol. 76, No. 231 / Thursday, December 1, 2011 / Rules and Regulations
Mississauga, Ontario, Canada L5S 1V7;
telephone (905) 405–1371; fax (905) 405–
1373; email inquiry@deca-aviation.com;
Internet https://www.deca-aviation.com.
(3) You may review copies of the 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.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 10, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–30232 Filed 11–30–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0914; Directorate
Identifier 2010–NM–166–AD; Amendment
39–16876; AD 2011–24–12]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–200, –200C, –300,
–400, and –500 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding an
existing airworthiness directive (AD) for
certain Model 737–300, –400, and –500
series airplanes. That AD currently
requires repetitive external nondestructive inspections to detect cracks
in the fuselage skin along the chem-mill
step at stringers S–1 and S–2 right,
between station (STA) 827 and STA
847, and repair if necessary. This new
AD adds inspections for cracking in
additional fuselage crown skin
locations, and repair if necessary. This
new AD also reduces the inspection
thresholds for certain airplanes, extends
emcdonald on DSK5VPTVN1PROD with RULES
SUMMARY:
certain repetitive inspection intervals,
and adds airplanes to the applicability
of the existing AD. This AD was
prompted by reports of additional crack
findings of the fuselage crown skin at
the chem-milled steps. We are issuing
this AD to detect and correct fatigue
cracking of the fuselage skin panels at
the chem-milled steps, which could
result in sudden fracture and failure of
the fuselage skin panels, and
consequent rapid decompression of the
airplane.
DATES: This AD is effective January 5,
2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of January 5, 2012.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of February 16, 2010 (75 FR
1527, January 12, 2010).
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; Email
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call (425) 227–
1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between
9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: (800) 647–5527)
is Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Wayne Lockett, Aerospace Engineer,
74667
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 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 2010–01–09,
Amendment 39–16167 (75 FR 1527,
January 12, 2010). That AD applies to
the specified products. The NPRM
published in the Federal Register on
September 1, 2011 (76 FR 54399). That
NPRM proposed to continue to require
repetitive external non-destructive
inspections to detect cracks in the
fuselage skin along the chem-mill step
at stringers S–1 and S–2 right, between
station (STA) 827 and STA 847, and
repair if necessary. That NPRM also
proposed to add inspections for
cracking in additional fuselage crown
skin locations, and repair if necessary.
That NPRM also proposed to reduce the
inspection thresholds for certain
airplanes, extend certain repetitive
inspection intervals, and add airplanes
to the applicability of the existing AD.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comments received.
Boeing and the National Transportation
Safety Board support the NPRM.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Interim Action
We consider this proposed AD
interim action. If final action is later
identified, we might consider further
rulemaking then.
Costs of Compliance
We estimate that this AD affects 654
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Average labor
rate per hour
Action
Work hours
Inspection in AD 2010–01–09 (75 FR
1527, January 12, 2010).
2 ..............................
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$85
Sfmt 4700
Cost per product
Number of
U.S.-registered
airplanes
$170 per inspection
cycle.
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01DER1
Fleet cost
$22,950 per inspection cycle.
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Federal Register / Vol. 76, No. 231 / Thursday, December 1, 2011 / Rules and Regulations
ESTIMATED COSTS—Continued
Average labor
rate per hour
Action
Work hours
New inspection in this AD .........................
85
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Authority for This Rulemaking
Adoption of the Amendment
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.
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Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2010–01–09, Amendment 39–16167 (75
FR 1527, January 12, 2010), and adding
the following new AD:
■
2011–24–12 The Boeing Company:
Amendment 39–16876; Docket No.
FAA–2011–0914; Directorate Identifier
2010–NM–166–AD.
(a) Effective Date
This airworthiness directive (AD) is
effective January 5, 2012.
(b) Affected ADs
This AD supersedes AD 2010–01–09,
Amendment 39–16167 (75 FR 1527, January
12, 2010).
(c) Applicability
This AD applies to all The Boeing
Company Model 737–200, –200C, –300,
–400, and –500 series airplanes, certificated
in any category.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
additional crack findings of the fuselage
crown skin at the chem-milled steps. We are
issuing this AD to detect and correct fatigue
cracking of the fuselage skin panels at the
chem-milled steps, which could result in
sudden fracture and failure of the fuselage
skin panels, and consequent rapid
decompression of the airplane.
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Frm 00044
Number of
U.S.-registered
airplanes
Between $170 and
$2,550 per inspection cycle.
Between 2 and 30 ..
We have received no definitive data
that would enable us to provide a cost
estimate for the on-condition actions
specified in this AD.
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Cost per product
Fmt 4700
Sfmt 4700
654
Fleet cost
Between $111,180
and $1,667,700
per inspection
cycle.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
Restatement of Requirements of AD 2010–
01–09, Amendment 39–16167 (75 FR 1527,
January 12, 2010)
(g) Initial and Repetitive Inspections
For airplanes identified in Boeing Alert
Service Bulletin 737–53A1301, dated
September 3, 2009: Before the accumulation
of 35,000 total flight cycles, or within 500
flight cycles after February 16, 2010 (the
effective date of AD 2010–01–09), whichever
occurs later, except as provided by paragraph
(i) of this AD, do an external non-destructive
inspection (NDI) to detect cracks in the
fuselage skin along the chem-mill steps at
stringers S–1 and S–2 right, between station
(STA) 827 and STA 847, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1301, dated
September 3, 2009; or Boeing Alert Service
Bulletin 737–53A1301, Revision 2, dated
April 25, 2011. If no cracking is found, repeat
the inspection thereafter at intervals not to
exceed 500 flight cycles; except as provided
by paragraphs (i) and (n) of this AD.
Accomplishing the inspections required by
paragraph (j) of this AD terminates the
inspections required by this paragraph.
(h) Repair
If any crack is found during any inspection
required by paragraph (g) of this AD, and
Boeing Alert Service Bulletin 737–53A1301,
dated September 3, 2009; or Boeing Alert
Service Bulletin 737–53A1301, Revision 2,
dated April 25, 2011; specifies to contact
Boeing for repair instructions: Before further
flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (q) of this AD.
(i) Optional Terminating Action for
Repetitive Inspections in Paragraph (g) of
This AD
Installing an external repair doubler along
the chem-milled steps at stringers S–1 and S–
2 right, between STA 827 and STA 847,
constitutes terminating action for the
repetitive inspections required by paragraph
(g) of this AD for the repaired area only,
provided all of the conditions specified in
paragraphs (i)(1), (i)(2), and (i)(3) of this AD
are met.
(1) The repair is installed after September
3, 2009;
(2) The repair was approved by the FAA
or by a Boeing Company Authorized
Representative or the Boeing Commercial
Airplanes Organization Designation
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Federal Register / Vol. 76, No. 231 / Thursday, December 1, 2011 / Rules and Regulations
Authorization (ODA) that has been
authorized by the Manager, Seattle Aircraft
Certification Office (ACO), FAA, to make
such findings; and
(3) The repair extends a minimum of three
rows of fasteners on each side of the chemmill line in the circumferential direction.
New Inspections Including Additional
Locations and Reduced Inspection Intervals
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(j) Groups 1 Through 25: Initial and
Repetitive Inspections
For Groups 1 through 25 airplanes
identified in Boeing Alert Service Bulletin
737–53A1301, Revision 2, dated April 25,
2011: Except as provided by paragraph (k) of
this AD, at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1301,
Revision 2, dated April 25, 2011, do the
applicable inspections required by
paragraphs (j)(1) and (j)(2) of this AD, in
accordance with paragraphs 3.B.1 through
3.B.25 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1301,
Revision 2, dated April 25, 2011. If no
cracking is found, repeat the applicable
inspections thereafter at the applicable
intervals specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1301, Revision 2, dated
April 25, 2011; except as provided by
paragraphs (m) and (n) of this AD. Doing the
inspections required by this paragraph
terminates the inspections required by
paragraph (g) of this AD.
(1) For Groups 2, 8, 10, 13 through 18, and
21 through 25 airplanes: Do a detailed
inspection and an external non-destructive
inspection (NDI) (medium frequency eddy
current inspection, magneto optical imaging
inspection, c-scan inspection, or ultrasonic
phased array inspection) for cracking in the
fuselage skin at the chem-mill steps at
stringers S–1 and S–2R between STA 827 and
STA 847, as identified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1301, Revision 2,
dated April 25, 2011.
(2) For Groups 1 through 25 airplanes: Do
a detailed inspection and an external NDI
(medium frequency eddy current inspection;
magneto optical imaging inspection, c-scan
inspection, or ultrasonic phased array
inspection) for cracking in the fuselage skin
at the chem-mill steps at the specified
locations other than at S–1 and S–2R
between STA 827 and STA 847, as identified
in the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1301,
Revision 2, dated April 25, 2011.
Note 1: Option 1 of Boeing Alert Service
Bulletin 737–53A1301, Revision 2, dated
April 25, 2011, specifies a detailed
inspection, and one additional inspection
(external NDI, medium frequency eddy
current inspection, magneto optical imaging
inspection, or c-scan inspection). Option 2 of
Boeing Alert Service Bulletin 737–53A1301,
Revision 2, dated April 25, 2011, specifies a
detailed inspection and an external
ultrasonic phased array inspection. These
options have different compliance times after
the initial inspection.
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17:21 Nov 30, 2011
Jkt 226001
(k) Exception
Where Boeing Alert Service Bulletin 737–
53A1301, Revision 2, dated April 25, 2011,
specifies a compliance time after ‘‘the date of
Revision 1,’’ or ‘‘the date of Revision 2’’ of
that service bulletin, this AD requires
compliance within the specified time after
the effective date of this AD.
(l) Repair
If any crack is found during any inspection
required by paragraph (j) of this AD: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (q) of this AD. Doing
the repair ends the repetitive inspections
required by paragraph (j) for the repaired area
only.
(m) Optional Terminating Action for
Repetitive Inspections
Installing an external repair doubler along
the chem-milled steps at any location
identified in Boeing Alert Service Bulletin
737–53A1301, Revision 2, dated April 25,
2011, constitutes terminating action for the
repetitive inspections required by paragraph
(j) of this AD for the repaired area only,
provided all of the conditions specified in
paragraphs (m)(1), (m)(2), and (m)(3) of this
AD are met.
(1) The repair is installed after the
applicable date specified in paragraph
(m)(1)(i) and (m)(1)(ii) of this AD.
(i) For repairs at S–1 and S–2R between
STA 827 and STA 847: Installed after
September 3, 2009.
(ii) For repairs at locations other than at S–
1 and S–2R between STA 827 and STA 847:
Installed after June 7, 2010.
(2) The repair was approved by the FAA
or by a Boeing Company Authorized
Representative or the Boeing Commercial
Airplanes Organization Designation
Authorization (ODA) that has been
authorized by the Manager, Seattle Aircraft
Certification Office (ACO) to make such
findings; and
(3) The repair extends a minimum of three
rows of fasteners on each side of the chemmill line in the circumferential direction.
(n) Modification
Accomplishing a modification of the chemmilled steps at any location identified in
Boeing Alert Service Bulletin 737–53A1301,
Revision 2, dated April 25, 2011, using a
method approved in accordance with the
procedures specified in paragraph (q)(1) of
this AD, terminates the repetitive inspections
required by paragraphs (g) and (j) of this AD
for the modified area only.
(o) Group 26 Airplanes
For Group 26 airplanes identified in
Boeing Alert Service Bulletin 737–53A1301,
Revision 2, dated April 25, 2011: Within
1,800 flight cycles after the effective date of
this AD, accomplish applicable inspections
and corrective action, as identified in the
service bulletin, using a method approved in
accordance with the procedures specified in
paragraph (q)(1) of this AD.
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74669
(p) Credit for Actions Accomplished in
Accordance With Previous Service
Information
Actions done before the effective date of
this AD in accordance with Boeing Alert
Service Bulletin 737–53A1301, Revision 1,
dated June 7, 2010, are acceptable for
compliance with the corresponding
requirements of this AD.
(q) 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.
(r) Related Information
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, Washington 98057–
3356; phone: (425) 917–6447; fax: (425) 917–
6590; email: wayne.lockett@faa.gov.
(s) Material Incorporated by Reference
You must use the following service
information to do the actions required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference (IBR) under 5
U.S.C. 552(a) and 1 CFR part 51 of the
following service information on the date
specified:
(1) Boeing Alert Service Bulletin 737–
53A1301, Revision 2, dated April 25, 2011,
approved for IBR January 5, 2012.
(2) Boeing Alert Service Bulletin 737–
53A1301, dated September 3, 2009, approved
for IBR February 16, 2010 (75 FR 1527,
January 12, 2010).
(3) 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; email me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
(4) You may review copies of the 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.
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(5) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at an NARA facility, call (202) 741–
6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
November 17, 2011.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2011–30608 Filed 11–30–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
National Oceanic and Atmospheric
Administration
15 CFR Part 902
50 CFR Parts 679 and 680
[Docket No. 100107012–1689–03]
RIN 0648–AY53
Fisheries of the Exclusive Economic
Zone Off Alaska; Pacific Cod
Allocations in the Gulf of Alaska;
Amendment 83
National Marine Fisheries
Service (NMFS), National Oceanic and
Atmospheric Administration (NOAA),
Commerce.
ACTION: Final rule.
AGENCY:
NMFS publishes regulations
to implement Amendment 83 to the
Fishery Management Plan for
Groundfish of the Gulf of Alaska (GOA).
Amendment 83 allocates Western and
Central GOA Pacific cod total allowable
catch (TAC) limits among various gear
and operational sectors. Sector
allocations limit the amount of Western
and Central GOA Pacific cod that each
sector is authorized to harvest. This
action reduces competition among
sectors and supports stability in the
Pacific cod fishery. This rule limits
access to the Federal Pacific cod TAC
fisheries prosecuted in State of Alaska
waters, commonly known as the parallel
fishery, adjacent to the Western and
Central GOA. This action is intended to
promote community participation and
provide incentives for new entrants in
the jig sector. It also promotes the goals
and objectives of the Magnuson-Stevens
Fishery Conservation and Management
Act, the Fishery Management Plan, and
other applicable laws.
DATES: Effective January 1, 2012.
ADDRESSES: Electronic copies of this
rule, the Environmental Assessment
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SUMMARY:
VerDate Mar<15>2010
17:21 Nov 30, 2011
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(EA), and Regulatory Impact Review
(RIR) may be obtained from the NMFS
Alaska Region Web site at https://
alaskafisheries.noaa.gov.
Written comments regarding the
burden-hour estimates or other aspects
of the collection-of-information
requirements contained in this final rule
may be submitted by mail to NMFS,
Alaska Region, P.O. Box 21668, Juneau,
AK 99802–1668, Attn: Ellen Sebastian,
Records Officer; in person at NMFS,
Alaska Region, 709 West 9th Street,
Room 420A, Juneau, Alaska; and by
email to
OIRA_Submission@omb.eop.gov, or by
fax to (202) 395–7285.
FOR FURTHER INFORMATION CONTACT:
Seanbob Kelly, (907) 586–7228.
SUPPLEMENTARY INFORMATION: NMFS
manages the groundfish fisheries in the
U.S. exclusive economic zone (EEZ) of
the GOA under the Fishery Management
Plan for Groundfish of the GOA (FMP).
The North Pacific Fishery Management
Council (Council) prepared, and NMFS
approved, the FMP under the authority
of the Magnuson-Stevens Fishery
Conservation and Management Act
(MSA), 16 U.S.C. 1801 et seq.
Regulations governing U.S. fisheries and
implementing the FMP appear at 50
CFR parts 600 and 679.
The Notice of Availability for
Amendment 83 was published in the
Federal Register on June 28, 2011 (76
FR 37763), with a 60-day comment
period that ended August 29, 2011. The
Secretary of Commerce (Secretary)
approved Amendment 83 on September
22, 2011. The Council submitted the
proposed rule to NMFS, and it was
published in the Federal Register on
July 26, 2011 (76 FR 44700). The 45-day
comment period on the proposed rule
ended September 9, 2011. NMFS
received a total of 6 letters, from five
unique persons, on Amendment 83 and
the proposed rule implementing the
amendment. The letters contained 29
individual comments. A summary of
these comments and the responses by
NMFS are provided under Response to
Comments below.
Elements of the Final Rule
A detailed review of the provisions of
Amendment 83 and its implementing
rule is provided in the preamble to the
proposed rule (76 FR 44700, July 26,
2011), and is not repeated here. The
proposed rule is available from the
NMFS Alaska Region web site (see
ADDRESSES). The following provides a
list and brief review of the regulatory
changes made by this final rule to the
management of the GOA Pacific cod
fishery. NMFS’ responses to public
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Frm 00046
Fmt 4700
Sfmt 4700
comments on Amendment 83 and the
proposed rule to implement
Amendment 83 are also presented
below.
Amendment 83 was adopted by the
Council in December 2009 to supersede
the current inshore/offshore processing
allocation of Western and Central GOA
Pacific cod among various harvesting
sectors. Pacific Cod is second only to
walleye pollock as the predominant
GOA fishery. As one of the most
valuable fish species in the GOA, Pacific
cod is the primary species targeted by
vessels using pot and hook-and-line gear
and is an important species for vessels
using the trawl gear. Smaller amounts of
Pacific cod are taken by vessels using jig
gear. Currently, Pacific cod in the GOA
is apportioned on the basis of processor
component (inshore and offshore) and
season, as implemented under
Amendment 23 to the GOA FMP (57 FR
23321, June 3, 1992). Under inshore/
offshore management, 90 percent of the
Western, Central, and Eastern GOA TAC
is allocated to vessels catching Pacific
cod for processing by the inshore
component, and 10 percent to vessels
catching Pacific cod for processing by
the offshore component. The Council
recognized that competition among
participants in the Western and Central
GOA Pacific cod fisheries has
intensified in recent years. Because the
TACs are divided by inshore/offshore
processing components of the fishery
and not divided among gear or
operation types, there is a derby-style
race for fish and competition among the
various gear types for shares of the
TACs.
Amendment 83 establishes sector
allocations for each gear and operation
type in the Western and Central GOA
Pacific cod fisheries. In both regulatory
areas, the sectors are jig, hook-and-line
catcher/processor (C/P), pot catcher
vessel (CV) and C/P combined, trawl
C/P, trawl CV, and hook-and-line CV;
however, in the Central GOA, the hookand-line CV sector are further divided
by vessel length. In the Central GOA,
hook-and-line CVs less than 50 ft (15.2
m) LOA (< 50 ft (15.2 m) LOA) are in
one sector and hook-and-line CVs
greater than or equal to 50 ft (15.2 m)
(≥ 50 ft (15.2 m)) are in another sector.
Historically, the majority of catch by
hook-and-line CVs has been harvested
by vessels < 50 ft (15.2 m) LOA, but in
recent years, there has been a
substantial increase in catch by hookand-line CVs that are between 50 ft (15.2
m) and 60 ft (18.3 m) LOA. Dividing this
sector at 50 ft (15.2 m) LOA protects
smaller boats from an influx of effort by
vessels ≥ 50 ft (15.2 m) LOA. The
Council recognized that in the Central
E:\FR\FM\01DER1.SGM
01DER1
]]>Agencies
[Federal Register Volume 76, Number 231 (Thursday, December 1, 2011)]
[Rules and Regulations]
[Pages 74667-74670]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-30608]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0914; Directorate Identifier 2010-NM-166-AD;
Amendment 39-16876; AD 2011-24-12]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 737-200, -
200C, -300, -400, and -500 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain Model 737-300, -400, and -500 series airplanes. That AD
currently requires repetitive external non-destructive inspections to
detect cracks in the fuselage skin along the chem-mill step at
stringers S-1 and S-2 right, between station (STA) 827 and STA 847, and
repair if necessary. This new AD adds inspections for cracking in
additional fuselage crown skin locations, and repair if necessary. This
new AD also reduces the inspection thresholds for certain airplanes,
extends certain repetitive inspection intervals, and adds airplanes to
the applicability of the existing AD. This AD was prompted by reports
of additional crack findings of the fuselage crown skin at the chem-
milled steps. We are issuing this AD to detect and correct fatigue
cracking of the fuselage skin panels at the chem-milled steps, which
could result in sudden fracture and failure of the fuselage skin
panels, and consequent rapid decompression of the airplane.
DATES: This AD is effective January 5, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of January 5,
2012.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
February 16, 2010 (75 FR 1527, January 12, 2010).
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; Email
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may
review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington. For information on the availability of this material at the
FAA, call (425) 227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (phone: (800) 647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 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 2010-01-09, Amendment 39-16167 (75 FR 1527,
January 12, 2010). That AD applies to the specified products. The NPRM
published in the Federal Register on September 1, 2011 (76 FR 54399).
That NPRM proposed to continue to require repetitive external non-
destructive inspections to detect cracks in the fuselage skin along the
chem-mill step at stringers S-1 and S-2 right, between station (STA)
827 and STA 847, and repair if necessary. That NPRM also proposed to
add inspections for cracking in additional fuselage crown skin
locations, and repair if necessary. That NPRM also proposed to reduce
the inspection thresholds for certain airplanes, extend certain
repetitive inspection intervals, and add airplanes to the applicability
of the existing AD.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comments received. Boeing and the
National Transportation Safety Board support the NPRM.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Interim Action
We consider this proposed AD interim action. If final action is
later identified, we might consider further rulemaking then.
Costs of Compliance
We estimate that this AD affects 654 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Cost per registered Fleet cost
rate per hour product airplanes
----------------------------------------------------------------------------------------------------------------
Inspection in AD 2010-01-09 2.............. $85 $170 per 135 $22,950 per
(75 FR 1527, January 12, inspection inspection
2010). cycle. cycle.
[[Page 74668]]
New inspection in this AD.... Between 2 and 85 Between $170 654 Between
30. and $2,550 per $111,180 and
inspection $1,667,700 per
cycle. inspection
cycle.
----------------------------------------------------------------------------------------------------------------
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)
2010-01-09, Amendment 39-16167 (75 FR 1527, January 12, 2010), and
adding the following new AD:
2011-24-12 The Boeing Company: Amendment 39-16876; Docket No. FAA-
2011-0914; Directorate Identifier 2010-NM-166-AD.
(a) Effective Date
This airworthiness directive (AD) is effective January 5, 2012.
(b) Affected ADs
This AD supersedes AD 2010-01-09, Amendment 39-16167 (75 FR
1527, January 12, 2010).
(c) Applicability
This AD applies to all The Boeing Company Model 737-200, -200C,
-300, -400, and -500 series airplanes, certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of additional crack findings of
the fuselage crown skin at the chem-milled steps. We are issuing
this AD to detect and correct fatigue cracking of the fuselage skin
panels at the chem-milled steps, which could result in sudden
fracture and failure of the fuselage skin panels, and consequent
rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
Restatement of Requirements of AD 2010-01-09, Amendment 39-16167 (75 FR
1527, January 12, 2010)
(g) Initial and Repetitive Inspections
For airplanes identified in Boeing Alert Service Bulletin 737-
53A1301, dated September 3, 2009: Before the accumulation of 35,000
total flight cycles, or within 500 flight cycles after February 16,
2010 (the effective date of AD 2010-01-09), whichever occurs later,
except as provided by paragraph (i) of this AD, do an external non-
destructive inspection (NDI) to detect cracks in the fuselage skin
along the chem-mill steps at stringers S-1 and S-2 right, between
station (STA) 827 and STA 847, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1301, dated
September 3, 2009; or Boeing Alert Service Bulletin 737-53A1301,
Revision 2, dated April 25, 2011. If no cracking is found, repeat
the inspection thereafter at intervals not to exceed 500 flight
cycles; except as provided by paragraphs (i) and (n) of this AD.
Accomplishing the inspections required by paragraph (j) of this AD
terminates the inspections required by this paragraph.
(h) Repair
If any crack is found during any inspection required by
paragraph (g) of this AD, and Boeing Alert Service Bulletin 737-
53A1301, dated September 3, 2009; or Boeing Alert Service Bulletin
737-53A1301, Revision 2, dated April 25, 2011; specifies to contact
Boeing for repair instructions: Before further flight, repair the
crack using a method approved in accordance with the procedures
specified in paragraph (q) of this AD.
(i) Optional Terminating Action for Repetitive Inspections in Paragraph
(g) of This AD
Installing an external repair doubler along the chem-milled
steps at stringers S-1 and S-2 right, between STA 827 and STA 847,
constitutes terminating action for the repetitive inspections
required by paragraph (g) of this AD for the repaired area only,
provided all of the conditions specified in paragraphs (i)(1),
(i)(2), and (i)(3) of this AD are met.
(1) The repair is installed after September 3, 2009;
(2) The repair was approved by the FAA or by a Boeing Company
Authorized Representative or the Boeing Commercial Airplanes
Organization Designation
[[Page 74669]]
Authorization (ODA) that has been authorized by the Manager, Seattle
Aircraft Certification Office (ACO), FAA, to make such findings; and
(3) The repair extends a minimum of three rows of fasteners on
each side of the chem-mill line in the circumferential direction.
New Inspections Including Additional Locations and Reduced Inspection
Intervals
(j) Groups 1 Through 25: Initial and Repetitive Inspections
For Groups 1 through 25 airplanes identified in Boeing Alert
Service Bulletin 737-53A1301, Revision 2, dated April 25, 2011:
Except as provided by paragraph (k) of this AD, at the applicable
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1301, Revision 2, dated April 25, 2011, do
the applicable inspections required by paragraphs (j)(1) and (j)(2)
of this AD, in accordance with paragraphs 3.B.1 through 3.B.25 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1301, Revision 2, dated April 25, 2011. If no cracking is
found, repeat the applicable inspections thereafter at the
applicable intervals specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-53A1301, Revision 2, dated April
25, 2011; except as provided by paragraphs (m) and (n) of this AD.
Doing the inspections required by this paragraph terminates the
inspections required by paragraph (g) of this AD.
(1) For Groups 2, 8, 10, 13 through 18, and 21 through 25
airplanes: Do a detailed inspection and an external non-destructive
inspection (NDI) (medium frequency eddy current inspection, magneto
optical imaging inspection, c-scan inspection, or ultrasonic phased
array inspection) for cracking in the fuselage skin at the chem-mill
steps at stringers S-1 and S-2R between STA 827 and STA 847, as
identified in the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1301, Revision 2, dated April 25, 2011.
(2) For Groups 1 through 25 airplanes: Do a detailed inspection
and an external NDI (medium frequency eddy current inspection;
magneto optical imaging inspection, c-scan inspection, or ultrasonic
phased array inspection) for cracking in the fuselage skin at the
chem-mill steps at the specified locations other than at S-1 and S-
2R between STA 827 and STA 847, as identified in the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1301, Revision
2, dated April 25, 2011.
Note 1: Option 1 of Boeing Alert Service Bulletin 737-53A1301,
Revision 2, dated April 25, 2011, specifies a detailed inspection,
and one additional inspection (external NDI, medium frequency eddy
current inspection, magneto optical imaging inspection, or c-scan
inspection). Option 2 of Boeing Alert Service Bulletin 737-53A1301,
Revision 2, dated April 25, 2011, specifies a detailed inspection
and an external ultrasonic phased array inspection. These options
have different compliance times after the initial inspection.
(k) Exception
Where Boeing Alert Service Bulletin 737-53A1301, Revision 2,
dated April 25, 2011, specifies a compliance time after ``the date
of Revision 1,'' or ``the date of Revision 2'' of that service
bulletin, this AD requires compliance within the specified time
after the effective date of this AD.
(l) Repair
If any crack is found during any inspection required by
paragraph (j) of this AD: Before further flight, repair the crack
using a method approved in accordance with the procedures specified
in paragraph (q) of this AD. Doing the repair ends the repetitive
inspections required by paragraph (j) for the repaired area only.
(m) Optional Terminating Action for Repetitive Inspections
Installing an external repair doubler along the chem-milled
steps at any location identified in Boeing Alert Service Bulletin
737-53A1301, Revision 2, dated April 25, 2011, constitutes
terminating action for the repetitive inspections required by
paragraph (j) of this AD for the repaired area only, provided all of
the conditions specified in paragraphs (m)(1), (m)(2), and (m)(3) of
this AD are met.
(1) The repair is installed after the applicable date specified
in paragraph (m)(1)(i) and (m)(1)(ii) of this AD.
(i) For repairs at S-1 and S-2R between STA 827 and STA 847:
Installed after September 3, 2009.
(ii) For repairs at locations other than at S-1 and S-2R between
STA 827 and STA 847: Installed after June 7, 2010.
(2) The repair was approved by the FAA or by a Boeing Company
Authorized Representative or the Boeing Commercial Airplanes
Organization Designation Authorization (ODA) that has been
authorized by the Manager, Seattle Aircraft Certification Office
(ACO) to make such findings; and
(3) The repair extends a minimum of three rows of fasteners on
each side of the chem-mill line in the circumferential direction.
(n) Modification
Accomplishing a modification of the chem-milled steps at any
location identified in Boeing Alert Service Bulletin 737-53A1301,
Revision 2, dated April 25, 2011, using a method approved in
accordance with the procedures specified in paragraph (q)(1) of this
AD, terminates the repetitive inspections required by paragraphs (g)
and (j) of this AD for the modified area only.
(o) Group 26 Airplanes
For Group 26 airplanes identified in Boeing Alert Service
Bulletin 737-53A1301, Revision 2, dated April 25, 2011: Within 1,800
flight cycles after the effective date of this AD, accomplish
applicable inspections and corrective action, as identified in the
service bulletin, using a method approved in accordance with the
procedures specified in paragraph (q)(1) of this AD.
(p) Credit for Actions Accomplished in Accordance With Previous Service
Information
Actions done before the effective date of this AD in accordance
with Boeing Alert Service Bulletin 737-53A1301, Revision 1, dated
June 7, 2010, are acceptable for compliance with the corresponding
requirements of this AD.
(q) 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.
(r) Related Information
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, Washington
98057-3356; phone: (425) 917-6447; fax: (425) 917-6590; email:
wayne.lockett@faa.gov.
(s) Material Incorporated by Reference
You must use the following service information to do the actions
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register approved the incorporation by reference
(IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following
service information on the date specified:
(1) Boeing Alert Service Bulletin 737-53A1301, Revision 2, dated
April 25, 2011, approved for IBR January 5, 2012.
(2) Boeing Alert Service Bulletin 737-53A1301, dated September
3, 2009, approved for IBR February 16, 2010 (75 FR 1527, January 12,
2010).
(3) 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; email
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(4) You may review copies of the 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.
[[Page 74670]]
(5) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at an NARA facility, call (202) 741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on November 17, 2011.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-30608 Filed 11-30-11; 8:45 am]
BILLING CODE 4910-13-P
