Airworthiness Directives; Boeing Model 737-200C Series Airplanes, 33992-33994 [06-5287]
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33992
Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations
Information and Regulatory Affairs of
OMB.
List of Subjects in 10 CFR Part 73
Criminal penalties, Export, Hazardous
materials transportation, Import,
Nuclear materials, Nuclear power plants
and reactors, Reporting and
recordkeeping requirements, Security
measures.
I For the reasons set out in the
preamble, and under the authority of the
Atomic Energy Act of 1954, as amended;
the Energy Reorganization Act of 1974,
as amended; the Energy Policy Act of
2005, and 5 U.S.C. 552 and 553; the
NRC is adopting the following
amendments to 10 CFR part 73.
PART 73—PHYSICAL PROTECTION OF
PLANTS AND MATERIALS
1. The authority citation for part 73 is
revised to read as follows:
I
Authority: Secs. 53, 161, 149, 68 Stat. 930,
948, as amended, sec. 147, 94 Stat. 780 (42
U.S.C. 2073, 2167, 2169, 2201); sec. 201, as
amended, 204, 88 Stat. 1242, as amended,
1245, sec. 1701, 106 Stat. 2951, 2952, 2953
(42 U.S.C. 5841, 5844, 2297f); sec. 1704, 112
Stat. 2750 (44 U.S.C. 3504 note); Energy
Policy Act of 2005, Public Law No. 109–58,
119 Stat. 594 (2005).
Section 73.1 also issued under secs. 135,
141, Public Law 97–425, 96 Stat. 2232, 2241
(42 U.S.C. 10155, 10161). Section 73.37(f)
also issued under sec. 301, Public Law 96–
295, 94 Stat. 789 (42 U.S.C. 5841 note).
Section 73.57 is issued under sec. 606, Public
Law 99–399, 100 Stat. 876 (42 U.S.C. 2169).
I 2. A new § 73.59 is added to read as
follows:
mstockstill on PROD1PC61 with RULES
§ 73.59 Relief from fingerprinting and
criminal history records check for
designated categories of individuals.
(a) For purposes of this section, the
phrase ‘‘Safeguards Information’’ means
information not otherwise classified as
National Security Information or
Restricted Data, which specifically
identifies a licensee’s or applicant’s
detailed—
(1) Control and accounting procedures
or security measures (including security
plans, procedures, and equipment) for
the physical protection of special
nuclear material, by whomever
possessed, whether in transit or at fixed
sites, in quantities determined by the
Commission to be significant to the
public health and safety or the common
defense and security;
(2) Security measures (including
security plans, procedures, and
equipment) for the physical protection
of source material or byproduct
material, by whomever possessed,
whether in transit or at fixed sites, in
quantities determined by the
VerDate Aug<31>2005
14:46 Jun 12, 2006
Jkt 208001
Commission to be significant to the
public health and safety or the common
defense and security;
(3) Security measures (including
security plans, procedures, and
equipment) for the physical protection
of and the location of certain plant
equipment vital to the safety of
production or utilization facilities
involving nuclear materials covered by
paragraphs (a)(1) and (a)(2) of this
section; or
(4) Any other information within the
scope of Section 147 of the Atomic
Energy Act of 1954, as amended, the
unauthorized disclosure of which, as
determined by the Commission through
order or regulation, could reasonably be
expected to have a significant adverse
effect on the health and safety of the
public or the common defense and
security by significantly increasing the
likelihood of radiological sabotage or
theft or diversion of source, byproduct,
or special nuclear material.
(b) Notwithstanding any other
provision of the Commission’s
regulations, fingerprinting and the
identification and criminal history
records checks required by section 149
of the Atomic Energy Act of 1954, as
amended, are not required for the
following individuals prior to granting
access to Safeguards Information:
(1) An employee of the Commission
or of the Executive Branch of the United
States government who has undergone
fingerprinting for a prior U.S.
government criminal history check;
(2) A member of Congress;
(3) An employee of a member of
Congress or Congressional committee
who has undergone fingerprinting for a
prior U.S. government criminal history
check;
(4) The Governor of a State or his or
her designated State employee
representative;
(5) A representative of a foreign
government organization that is
involved in planning for, or responding
to, nuclear or radiological emergencies
or security incidents who the
Commission approves for access to
Safeguards Information;
(6) Federal, State, or local law
enforcement personnel;
(7) State Radiation Control Program
Directors and State Homeland Security
Advisors or their designated State
employee representatives;
(8) Agreement State employees
conducting security inspections on
behalf of the NRC pursuant to an
agreement executed under section 274.i.
of the Atomic Energy Act;
(9) Representatives of the
International Atomic Energy Agency
(IAEA) engaged in activities associated
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Fmt 4700
Sfmt 4700
with the U.S./IAEA Safeguards
Agreement who have been certified by
the NRC.
Dated at Rockville, Maryland, this 7th day
of June, 2006.
For the Nuclear Regulatory Commission.
Annette L. Vietti-Cook,
Secretary of the Commission.
[FR Doc. E6–9178 Filed 6–12–06; 8:45 am]
BILLING CODE 7590–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24245; Directorate
Identifier 2005–NM–166–AD; Amendment
39–14643; AD 2006–12–17]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–200C Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
which applies to all Boeing Model 737–
200C series airplanes. That AD currently
requires a one-time external detailed
inspection for cracking of the fuselage
skin in the lower lobe cargo
compartment; repetitive internal
detailed inspections for cracking of the
frames in the lower lobe cargo
compartment; repair of cracked parts;
and terminating action for the repetitive
internal detailed inspections. This new
AD restates the requirements of the
existing AD and adds a requirement to
perform repetitive detailed inspections
of the body station (BS) 360 and BS 500
fuselage frames, after accomplishing the
terminating action, and repair if
necessary. This AD results from
multiple reports that the existing AD is
not fully effective in preventing cracks
in the BS 360 and BS 500 fuselage
frames. We are issuing this AD to detect
and correct cracking of the fuselage
frames from BS 360 to BS 500B, which
could lead to loss of the cargo door
during flight and consequent rapid
decompression of the airplane.
DATES: This AD becomes effective July
18, 2006.
On August 9, 1993 (58 FR 36863, July
9, 1993), the Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the AD.
ADDRESSES: You may examine the AD
docket on the Internet at https://
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Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Howard Hall, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6430; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
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Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 99–12–08, amendment
39–11192 (64 FR 31488, June 11, 1999).
The existing AD applies to all Boeing
Model 737–200C series airplanes. That
NPRM was published in the Federal
Register on March 30, 2006 (71 FR
16063). That NPRM proposed to require
a one-time external detailed inspection
for cracking of the fuselage skin in the
lower lobe cargo compartment;
repetitive internal detailed inspections
for cracking of the frames in the lower
lobe cargo compartment; repair of
cracked parts; and terminating action for
the repetitive internal detailed
inspections. That NPRM also proposed
to add a requirement to perform
repetitive detailed inspections of the
body station (BS) 360 and BS 500
fuselage frames, after accomplishing the
terminating action, and repair if
necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the one comment received.
The commenter, Boeing, supports the
NPRM.
Conclusion
We have carefully reviewed the
available data, including the comment
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14:46 Jun 12, 2006
Jkt 208001
received, and determined that air safety
and the public interest require adopting
the AD as proposed.
Costs of Compliance
There are about 90 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 18 airplanes
of U.S. registry.
The modification required by AD 99–
12–08, and retained in this AD, takes
approximately 160 work hours per
airplane to accomplish, at an average
labor rate of $80 per work hour.
Required parts cost about $5,500 per
airplane. Based on these figures, the
estimated cost of the currently required
modification for U.S. operators is
$329,400, or $18,300 per airplane.
The new inspections will take about
3 work hours per airplane, at an average
labor rate of $80 per work hour. Based
on these figures, the estimated cost of
the new inspections specified in this AD
for U.S. operators is $4,320, or $240 per
airplane, per inspection cycle.
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); and
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Fmt 4700
Sfmt 4700
33993
(3) 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–11192 (64
FR 31488, June 11, 1999) and by adding
the following new airworthiness
directive (AD):
I
2006–12–17 Boeing: Amendment 39–14643.
Docket No. FAA–2006–24245;
Directorate Identifier 2005–NM–166–AD.
Effective Date
(a) This AD becomes effective July 18,
2006.
Affected ADs
(b) This AD supersedes AD 99–12–08.
Applicability
(c) This AD applies to all Boeing Model
737–200C series airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from multiple reports
that the modification required by AD 99–12–
08 is not fully effective in preventing cracks
in the body station (BS) 360 and BS 500
fuselage frames. We are issuing this AD to
detect and correct cracking of the fuselage
frames from BS 360 to BS 500B, which could
lead to loss of the cargo door during flight
and consequent rapid decompression of the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
E:\FR\FM\13JNR1.SGM
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33994
Federal Register / Vol. 71, No. 113 / Tuesday, June 13, 2006 / Rules and Regulations
Restatement of Requirements of AD 99–12–
08
One-Time External Detailed Inspection
(f) Prior to the accumulation of 29,000 total
flight cycles or within 250 flight cycles after
August 9, 1993 (the effective date AD 93–13–
02, amendment 39–8615, which was
superseded by AD 99–12–08), whichever
occurs later, accomplish an external detailed
inspection to detect cracks of the fuselage
skin between stringers 19 left and 25 left and
at BS 360 to BS 540, in accordance with
Boeing Alert Service Bulletin 737–53A1160,
dated October 24, 1991; or Boeing Service
Bulletin 737–53A1160, Revision 1, dated
April 29, 1993. If any crack is found, prior
to further flight, accomplish the requirements
of paragraphs (f)(1) and (f)(2) of this AD.
(1) Perform an internal detailed inspection
to detect cracks of the frames between
stringers 19 left and 25 left and at BS 360 to
BS 500B, in accordance with either service
bulletin.
(2) Repair all cracks in accordance with a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), Transport
Airplane Directorate, FAA.
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Internal Detailed Inspections
(g) Within 3,000 flight cycles after
completing the requirements of paragraph (f)
of this AD, unless accomplished within the
last 6,000 flight cycles prior to August 9,
1993, perform an internal detailed inspection
to detect cracks of the frames between
stringers 19 left and 25 left and at body
stations 360 to 500B, in accordance with
Boeing Alert Service Bulletin 737–53A1160,
dated October 24, 1991; or Boeing Service
Bulletin 737–53A1160, Revision 1, dated
April 29, 1993. Thereafter, repeat the internal
detailed inspection at intervals not to exceed
9,000 flight cycles. If any crack is found
during any inspection required by this
paragraph, before further flight, repair as
specified in paragraph (g)(1) or (g)(2) of this
AD, as applicable.
(1) If any crack is found that does not
exceed the limits specified in the Boeing 737
Structural Repair Manual (SRM), repair the
crack in accordance with a method approved
by the Manager, Seattle ACO; or in
accordance with the procedures specified in
paragraph (k)(4) of this AD. The SRM is one
approved source of information for
accomplishing the requirements of this
paragraph. Repeat the internal detailed
inspection thereafter at intervals not to
exceed 9,000 flight cycles.
(2) If any crack is found that exceeds the
limits specified in the SRM, repair the crack
in accordance with a method approved by
the Manager, Seattle ACO; or in accordance
with the procedures specified in paragraph
(k)(4) of this AD. Repeat the internal detailed
visual inspection thereafter at intervals not to
exceed 9,000 flight cycles.
Install Doublers
(h) Prior to the accumulation of 75,000
total flight cycles, or within 3,000 flight
cycles after July 16, 1999 (the effective date
of AD 99–12–08), whichever occurs later,
install doublers on the specified frames
located between stringers 19 left and 25 left
from BS 360 to BS 500B, in accordance with
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14:46 Jun 12, 2006
Jkt 208001
Boeing Service Bulletin 737–53A1160,
Revision 1, dated April 29, 1993. Installing
these doublers on the specified fuselage
frames ends the repetitive inspections
required by paragraphs (f) and (g) of this AD.
New Requirements of This AD
Repetitive Inspection of Certain Frames
(i) Within 9,000 flight cycles after
accomplishing the modification required by
paragraph (h) of this AD, or within 4,500
flight cycles after the effective date of this
AD, whichever occurs later, perform an
internal detailed inspection to detect
cracking in the fuselage frame at BS 360 and
the fuselage frame at BS 500, between
stringers 19 left and 25 left, in accordance
with Boeing Alert Service Bulletin 737–
53A1160, dated October 24, 1991; or Boeing
Service Bulletin 737–53A1160, Revision 1,
dated April 29, 1993. Thereafter, repeat the
internal detailed inspection of the BS 360
and BS 500 frames at intervals not to exceed
9,000 flight cycles.
(j) If any crack is found during any
inspection required by paragraph (i) of this
AD, before further flight, repair the crack
using a method approved in accordance with
the procedures specified in paragraph (k) of
this AD.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with 14 CFR 39.19 on any
airplane to which the AMOC applies, notify
the appropriate principal inspector in the
FAA Flight Standards Certificate Holding
District Office.
(3) AMOCs approved previously in
accordance with AD 99–12–08, including
AMOCs approved previously in accordance
with AD 93–13–02, are approved as AMOCs
for the corresponding provisions specified in
paragraphs (f), (g), and (h) of this AD.
(4) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who 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.
Material Incorporated by Reference
(l) You must use Boeing Alert Service
Bulletin 737–53A1160, dated October 24,
1991; or Boeing Service Bulletin 737–
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Frm 00006
Fmt 4700
Sfmt 4700
53A1160, Revision 1, dated April 29, 1993,
as applicable, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of these documents on August 9,
1993 (58 FR 36863, July 9, 1993). Contact
Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124–2207, for a
copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the 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 June 5,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5287 Filed 6–12–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19002; Directorate
Identifier 2003–NM–27–AD; Amendment 39–
14639; AD 2006–12–13]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2 and A300 B4 Series Airplanes;
A300 B4–600, B4–600R, and F4–600R
Series Airplanes; and Model C4–605R
Variant F Airplanes (Collectively Called
A300–600 Series Airplanes)
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Airbus Model
A300 and A300–600 series airplanes.
That AD currently requires repetitive
inspections to detect cracks in Gear Rib
5 of the main landing gear (MLG)
attachment fittings at the lower flange,
and repair, if necessary. That AD also
requires modification of Gear Rib 5 of
the MLG attachment fittings, which
constitutes terminating action for the
repetitive inspections. This new AD
requires new repetitive inspections at
reduced compliance times. This new
AD also requires new repetitive
inspections of certain areas of the
E:\FR\FM\13JNR1.SGM
13JNR1
]]>Agencies
[Federal Register Volume 71, Number 113 (Tuesday, June 13, 2006)]
[Rules and Regulations]
[Pages 33992-33994]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5287]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24245; Directorate Identifier 2005-NM-166-AD;
Amendment 39-14643; AD 2006-12-17]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-200C Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) which applies to all Boeing Model 737-200C series airplanes. That
AD currently requires a one-time external detailed inspection for
cracking of the fuselage skin in the lower lobe cargo compartment;
repetitive internal detailed inspections for cracking of the frames in
the lower lobe cargo compartment; repair of cracked parts; and
terminating action for the repetitive internal detailed inspections.
This new AD restates the requirements of the existing AD and adds a
requirement to perform repetitive detailed inspections of the body
station (BS) 360 and BS 500 fuselage frames, after accomplishing the
terminating action, and repair if necessary. This AD results from
multiple reports that the existing AD is not fully effective in
preventing cracks in the BS 360 and BS 500 fuselage frames. We are
issuing this AD to detect and correct cracking of the fuselage frames
from BS 360 to BS 500B, which could lead to loss of the cargo door
during flight and consequent rapid decompression of the airplane.
DATES: This AD becomes effective July 18, 2006.
On August 9, 1993 (58 FR 36863, July 9, 1993), the Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the AD.
ADDRESSES: You may examine the AD docket on the Internet at https://
[[Page 33993]]
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Howard Hall, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6430; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 99-12-08, amendment 39-
11192 (64 FR 31488, June 11, 1999). The existing AD applies to all
Boeing Model 737-200C series airplanes. That NPRM was published in the
Federal Register on March 30, 2006 (71 FR 16063). That NPRM proposed to
require a one-time external detailed inspection for cracking of the
fuselage skin in the lower lobe cargo compartment; repetitive internal
detailed inspections for cracking of the frames in the lower lobe cargo
compartment; repair of cracked parts; and terminating action for the
repetitive internal detailed inspections. That NPRM also proposed to
add a requirement to perform repetitive detailed inspections of the
body station (BS) 360 and BS 500 fuselage frames, after accomplishing
the terminating action, and repair if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the one comment received.
The commenter, Boeing, supports the NPRM.
Conclusion
We have carefully reviewed the available data, including the
comment received, and determined that air safety and the public
interest require adopting the AD as proposed.
Costs of Compliance
There are about 90 airplanes of the affected design in the
worldwide fleet. This AD will affect about 18 airplanes of U.S.
registry.
The modification required by AD 99-12-08, and retained in this AD,
takes approximately 160 work hours per airplane to accomplish, at an
average labor rate of $80 per work hour. Required parts cost about
$5,500 per airplane. Based on these figures, the estimated cost of the
currently required modification for U.S. operators is $329,400, or
$18,300 per airplane.
The new inspections will take about 3 work hours per airplane, at
an average labor rate of $80 per work hour. Based on these figures, the
estimated cost of the new inspections specified in this AD for U.S.
operators is $4,320, or $240 per airplane, per inspection cycle.
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); and
(3) 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-11192 (64 FR 31488, June 11, 1999) and by adding
the following new airworthiness directive (AD):
2006-12-17 Boeing: Amendment 39-14643. Docket No. FAA-2006-24245;
Directorate Identifier 2005-NM-166-AD.
Effective Date
(a) This AD becomes effective July 18, 2006.
Affected ADs
(b) This AD supersedes AD 99-12-08.
Applicability
(c) This AD applies to all Boeing Model 737-200C series
airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from multiple reports that the modification
required by AD 99-12-08 is not fully effective in preventing cracks
in the body station (BS) 360 and BS 500 fuselage frames. We are
issuing this AD to detect and correct cracking of the fuselage
frames from BS 360 to BS 500B, which could lead to loss of the cargo
door during flight and consequent rapid decompression of the
airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
[[Page 33994]]
Restatement of Requirements of AD 99-12-08
One-Time External Detailed Inspection
(f) Prior to the accumulation of 29,000 total flight cycles or
within 250 flight cycles after August 9, 1993 (the effective date AD
93-13-02, amendment 39-8615, which was superseded by AD 99-12-08),
whichever occurs later, accomplish an external detailed inspection
to detect cracks of the fuselage skin between stringers 19 left and
25 left and at BS 360 to BS 540, in accordance with Boeing Alert
Service Bulletin 737-53A1160, dated October 24, 1991; or Boeing
Service Bulletin 737-53A1160, Revision 1, dated April 29, 1993. If
any crack is found, prior to further flight, accomplish the
requirements of paragraphs (f)(1) and (f)(2) of this AD.
(1) Perform an internal detailed inspection to detect cracks of
the frames between stringers 19 left and 25 left and at BS 360 to BS
500B, in accordance with either service bulletin.
(2) Repair all cracks in accordance with a method approved by
the Manager, Seattle Aircraft Certification Office (ACO), Transport
Airplane Directorate, FAA.
Internal Detailed Inspections
(g) Within 3,000 flight cycles after completing the requirements
of paragraph (f) of this AD, unless accomplished within the last
6,000 flight cycles prior to August 9, 1993, perform an internal
detailed inspection to detect cracks of the frames between stringers
19 left and 25 left and at body stations 360 to 500B, in accordance
with Boeing Alert Service Bulletin 737-53A1160, dated October 24,
1991; or Boeing Service Bulletin 737-53A1160, Revision 1, dated
April 29, 1993. Thereafter, repeat the internal detailed inspection
at intervals not to exceed 9,000 flight cycles. If any crack is
found during any inspection required by this paragraph, before
further flight, repair as specified in paragraph (g)(1) or (g)(2) of
this AD, as applicable.
(1) If any crack is found that does not exceed the limits
specified in the Boeing 737 Structural Repair Manual (SRM), repair
the crack in accordance with a method approved by the Manager,
Seattle ACO; or in accordance with the procedures specified in
paragraph (k)(4) of this AD. The SRM is one approved source of
information for accomplishing the requirements of this paragraph.
Repeat the internal detailed inspection thereafter at intervals not
to exceed 9,000 flight cycles.
(2) If any crack is found that exceeds the limits specified in
the SRM, repair the crack in accordance with a method approved by
the Manager, Seattle ACO; or in accordance with the procedures
specified in paragraph (k)(4) of this AD. Repeat the internal
detailed visual inspection thereafter at intervals not to exceed
9,000 flight cycles.
Install Doublers
(h) Prior to the accumulation of 75,000 total flight cycles, or
within 3,000 flight cycles after July 16, 1999 (the effective date
of AD 99-12-08), whichever occurs later, install doublers on the
specified frames located between stringers 19 left and 25 left from
BS 360 to BS 500B, in accordance with Boeing Service Bulletin 737-
53A1160, Revision 1, dated April 29, 1993. Installing these doublers
on the specified fuselage frames ends the repetitive inspections
required by paragraphs (f) and (g) of this AD.
New Requirements of This AD
Repetitive Inspection of Certain Frames
(i) Within 9,000 flight cycles after accomplishing the
modification required by paragraph (h) of this AD, or within 4,500
flight cycles after the effective date of this AD, whichever occurs
later, perform an internal detailed inspection to detect cracking in
the fuselage frame at BS 360 and the fuselage frame at BS 500,
between stringers 19 left and 25 left, in accordance with Boeing
Alert Service Bulletin 737-53A1160, dated October 24, 1991; or
Boeing Service Bulletin 737-53A1160, Revision 1, dated April 29,
1993. Thereafter, repeat the internal detailed inspection of the BS
360 and BS 500 frames at intervals not to exceed 9,000 flight
cycles.
(j) If any crack is found during any inspection required by
paragraph (i) of this AD, before further flight, repair the crack
using a method approved in accordance with the procedures specified
in paragraph (k) of this AD.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with 14 CFR
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 99-12-08,
including AMOCs approved previously in accordance with AD 93-13-02,
are approved as AMOCs for the corresponding provisions specified in
paragraphs (f), (g), and (h) of this AD.
(4) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who 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.
Material Incorporated by Reference
(l) You must use Boeing Alert Service Bulletin 737-53A1160,
dated October 24, 1991; or Boeing Service Bulletin 737-53A1160,
Revision 1, dated April 29, 1993, as applicable, to perform the
actions that are required by this AD, unless the AD specifies
otherwise. The Director of the Federal Register approved the
incorporation by reference of these documents on August 9, 1993 (58
FR 36863, July 9, 1993). Contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124-2207, for a copy of this service
information. You may review copies at the Docket Management
Facility, U.S. Department of Transportation, 400 Seventh Street SW.,
Room PL-401, Nassif Building, Washington, DC; on the Internet at
https://dms.dot.gov; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at the 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 June 5, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5287 Filed 6-12-06; 8:45 am]
BILLING CODE 4910-13-P
