Airworthiness Directives; Boeing Model 737-600, -700, -700C, and -800 Series Airplanes, 12068-12070 [E7-4540]
Download as PDF
12068
Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations
Effective Date
(a) This AD becomes effective on April 19,
2007.
unfeathering accumulators installed, that are
certificated in any category.
Affected ADs
(b) None.
(d) This AD results from several reports on
the affected airplanes of chafing damage on
the left propeller accumulator oil tube
assembly. This includes an in-flight oil leak
from the left engine on a Raytheon Aircraft
Company Model G58 airplane. We are
issuing this AD to detect, correct, and
Applicability
(c) This AD applies to Models 58 and G58
airplanes, serial numbers TH–2097 through
TH–2150, with optional propeller
Unsafe Condition
prevent any chafing damage of the left
propeller accumulator oil tube assembly,
which could result in loss of engine oil. Loss
of engine oil may lead to fire or smoke in the
engine compartment, inability to unfeather
the propeller, engine damage, or loss of
engine power.
Compliance
(e) To address this problem, you must do
the following, unless already done:
Actions
Compliance
Procedures
(1) Inspect the left propeller accumulator oil
tube assembly for chafing.
For airplanes that have not had a 100-hour
time-in-service (TIS) inspection or the inspection
following
Raytheon
Safety
´
Communique No. 271, dated May 2006:
Within the next 25 hours TIS after April 19,
2007 (the effective date of this AD). For airplanes that have had a 100-hour TIS inspection or the inspection following
´
Raytheon Safety Communique No. 271,
dated May 2006: Within the next 50 hours
TIS after April 19, 2007 (the effective date
of this AD).
Before further flight after the inspection required by paragraph (e)(1) of this AD.
Follow Raytheon Aircraft Company Mandatory
Service Bulletin No. SB 61–3806, issued:
August 2006.
(2) If any chafing is found in the inspection required by paragraph (e)(1) of this AD, replace
the propeller accumulator oil tube assembly.
(3) Reposition and secure with clamps the left
manifold pressure hose and its metal identification tags to ensure clearance between it
and all tubes, hoses, electrical wires, parts,
components, and structure.
Material Incorporated by Reference
DEPARTMENT OF TRANSPORTATION
rmajette on PROD1PC67 with RULES
(f) You must use Raytheon Aircraft
Company Mandatory Service Bulletin No. SB
61–3806, issued: August 2006, to do the
actions required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Raytheon Aircraft Company,
9709 E. Central, Wichita, Kansas 67201–
0085; telephone: (800) 429–5372 or (316)
676–3140.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; or 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 Kansas City, Missouri, on March
7, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–4523 Filed 3–14–07; 8:45 am]
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14:08 Mar 14, 2007
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Before further flight after the inspection or replacement required in paragraphs (e)(1)
and (e)(2) of this AD.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24369; Directorate
Identifier 2006–NM–001–AD; Amendment
39–14990; AD 2007–06–09]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, and –800
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Boeing Model
737–600, –700, –700C, and –800 series
airplanes. That AD currently requires
replacing the point ‘‘D’’ splice fitting
between windows number 1 and 2 with
a new splice fitting; performing an eddy
current inspection for cracking of the
holes in the structure common to the
new splice fitting, including doing any
related investigative actions; and
performing corrective actions if
necessary. This new AD adds repetitive
inspections for cracking of the skin just
below each splice fitting, and related
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Fmt 4700
Sfmt 4700
Follow Raytheon Aircraft Company Mandatory
Service Bulletin No. SB 61–3806, issued:
August 2006.
Follow Raytheon Aircraft Company Mandatory
Service Bulletin No. SB 61–3806, issued:
August 2006.
corrective actions if necessary. This AD
results from full-scale fuselage fatigue
testing on the splice fitting that failed
prior to the design objective on Boeing
Model 737–800 series airplanes, and a
report of a cracked splice fitting on an
operational airplane. We are issuing this
AD to prevent cracking of the existing
fitting, which may result in cracking
through the skin and consequent
decompression of the flight deck.
This AD becomes effective April
19, 2007.
The incorporation by reference of
Boeing Alert Service Bulletin 737–
53A1222, Revision 3, dated January 3,
2007, as listed in the regulations, is
approved by the Director of the Federal
Register as of April 19, 2007.
On December 21, 2005 (70 FR 72595,
December 6, 2005), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 737–53A1222,
Revision 2, dated October 20, 2005.
DATES:
You may examine the AD
docket on the Internet at https://
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,
ADDRESSES:
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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations
corrective actions if necessary. That
NPRM also proposed to add repetitive
inspections for cracking of the skin just
below each splice fitting, and related
corrective actions if necessary.
Washington 98124–2207, for service
information identified in this AD.
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; telephone
(425) 917–6447; 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 2005–25–03, amendment
39–14396 (70 FR 72595, December 6,
2005). The existing AD applies to
certain Boeing Model 737–600, –700,
–700C, and –800 series airplanes. That
NPRM was published in the Federal
Register on April 11, 2006 (71 FR
18251). That NPRM proposed to
continue to require replacing the point
‘‘D’’ splice fitting between windows
number 1 and 2 with a new splice
fitting; performing an eddy current
inspection for cracking of the holes in
the structure common to the new splice
fitting, including doing any related
investigative actions; and performing
Explanation of Revision Service
Information
The NPRM referred to Boeing Alert
Service Bulletin 737–53A1222, Revision
2, as the appropriate source of service
information for the inspection of
paragraph (g). Boeing has since revised
the service bulletin. Revision 3, dated
January 3, 2007, corrects and clarifies
certain information and adds fastener
options, but adds no additional work for
airplanes with splice fittings replaced as
specified in a previous version of the
service bulletin. We have revised this
final rule to refer to Revision 3 of the
service bulletin for the inspection in
paragraph (g), and to provide credit for
work done in accordance with Revision
2.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Support for the NPRM
One commenter, Continental Airlines,
agrees with the NPRM.
Request To Provide an Alternate
Method of Compliance (AMOC)
KLM Engineering and Maintenance
requests that the FAA review the
inspection methods for the proposed
one-time inspection of certain fastener
locations during the point ‘‘D’’ splice
fitting replacement. The commenter
12069
advises that, for certain fastener
locations, an eddy current open fastener
hole is impractical and may not even be
possible due to structure build-up. The
commenter requests that an AMOC be
given specifying fluorescent penetrant
inspections instead of the eddy current
open fastener hole inspections. The
commenter notes that use of the
fluorescent penetrant inspections has
been coordinated with the
manufacturer.
Since we issued the NPRM, the
manufacturer issued Revision 3 of
Boeing Alert Service Bulletin (ASB)
737–53A1222. Revision 3, dated January
3, 2007, contains procedures for
performing fluorescent penetrant
inspections. This final rule incorporates
the revised service bulletin; therefore,
no AMOC will be necessary to do this
type of inspection. We have not changed
this AD regarding this issue.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
There are about 563 airplanes of the
affected design in the worldwide fleet.
We estimate that about 243 airplanes are
on the U.S. Register, and that the
average labor rate is $80 per hour. The
following table provides the estimated
costs for U.S. operators to comply with
this AD.
ESTIMATED COSTS
Action
Work hours
Parts
Cost per
airplane
Fleet cost
Replacing splice fittings with new fittings (required by AD 2005–25–03) .......
External detailed inspection (new action) ........................................................
36
1
$15,445
0
$18,325
80
$4,452,975
1 19,440
1 Per
inspection cycle.
rmajette on PROD1PC67 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
VerDate Aug<31>2005
14:08 Mar 14, 2007
Jkt 211001
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.
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Fmt 4700
Sfmt 4700
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:
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12070
Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations
(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
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]
2007–06–09 Boeing: Amendment 39–14990.
Docket No. FAA–2006–24369;
Directorate Identifier 2006–NM–001–AD.
Effective Date
(a) This AD becomes effective April 19,
2007.
Applicability
(c) This AD applies to Boeing Model 737–
600, –700, –700C, and –800 series airplanes,
certificated in any category; as identified in
Boeing Alert Service Bulletin (ASB) 737–
53A1222, Revision 3, dated January 3, 2007.
rmajette on PROD1PC67 with RULES
Restatement of Certain Requirements of AD
2005–25–03
(j)(1) The Manager, Seattle ACO, FAA, 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 § 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) 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.
(4) AMOCs approved previously in
accordance with AD 2005–25–03,
amendment 39–14396, are approved as
AMOCs for the corresponding provisions of
paragraphs (f) and (h) of this AD.
Replacing the Splice Fittings
(f) Replace the splice fittings with new
splice fittings in accordance with the
Accomplishment Instructions of Boeing ASB
737–53A1222, Revision 2, dated October 20,
2005, or Revision 3, dated January 3, 2007,
at the times specified in paragraph (f)(1) or
(f)(2) of this AD, as applicable. Before further
flight, do any related investigative actions by
accomplishing all the applicable actions
specified in the Accomplishment
Instructions.
(1) For airplanes that have accumulated
fewer than 13,500 total flight cycles as
December 21, 2005 (the effective date of AD
2005–25–03): Replace prior to the
accumulation of 13,500 total flight cycles, or
within 1,000 flight cycles after December 21,
2005, whichever occurs later.
(2) For airplanes that have accumulated
13,500 or more total flight cycles as of
December 21, 2005: Replace at the later of the
times specified in paragraphs (f)(2)(i) and
(f)(2)(ii) of this AD.
(i) Prior to the accumulation of 18,000 total
flight cycles, or within 1,000 flight cycles
after December 21, 2005, whichever occurs
first.
(ii) Within 90 days after December 21,
2005.
Unsafe Condition
(d) This AD results from full-scale fuselage
fatigue testing on a splice fitting that failed
prior to the design objective on Boeing Model
737–800 series airplanes, and a report of a
cracked splice fitting on an operational
airplane. We are issuing this AD to prevent
cracking of the existing fitting, which may
result in cracking through the skin and
consequent decompression of the flight deck.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
Jkt 211001
Repetitive Inspections
(g) Within 24,000 flight cycles after
accomplishing the actions specified in
paragraph (f) of this AD, perform an external
detailed inspection of the skin just below
each splice fitting, in accordance with the
Accomplishment Instructions of Boeing ASB
737–53A1222, Revision 3, dated January 3,
2007. Thereafter, repeat the external detailed
inspections at intervals not to exceed 24,000
flight cycles.
Corrective Actions
Affected ADs
(b) This AD supersedes AD 2005–25–03.
14:08 Mar 14, 2007
Alternative Methods of Compliance
(AMOCs)
New Requirements of This AD
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14396 (70
FR 72595, December 6, 2005) and by
adding the following new airworthiness
directive (AD):
I
VerDate Aug<31>2005
the compliance times specified, unless the
actions have already been done.
(h) If any cracking is found during any
inspection required by this AD, prior to
further flight, repair in accordance with a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA, or
with a method approved in accordance with
the procedures specified in paragraph (j) of
this AD.
Acceptable Method of Compliance
(i) Replacing the splice fitting and any
related investigative actions before December
21, 2005 (the effective date of AD 2005–25–
03), in accordance with Boeing Service
Bulletin 737–53–1222, dated June 6, 2002; or
Boeing ASB 737–53A1222, Revision 1, dated
January 30, 2003, is acceptable for
compliance with the requirements of
paragraph (f) of this AD. An inspection done
before the effective date of this AD in
accordance with Boeing ASB 737–53A1222,
Revision 2, dated October 20, 2005, is
acceptable for compliance with the
requirements of paragraph (g) of this AD.
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Frm 00040
Fmt 4700
Sfmt 4700
Material Incorporated by Reference
(k) You must use Boeing Alert Service
Bulletin 737–53A1222, Revision 2, dated
October 20, 2005; or Boeing Alert Service
Bulletin 737–53A1222, Revision 3, dated
January 3, 2007; to perform the actions that
are required by this AD, unless the AD
specifies otherwise.
(1) The incorporation by reference of
Boeing Alert Service Bulletin 737–53A1222,
Revision 3, dated January 3, 2007, is
approved by the Director of the Federal
Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51.
(2) On December 21, 2005 (70 FR 72595,
December 6, 2005), the Director of the
Federal Register approved the incorporation
by reference of Boeing Alert Service Bulletin
737–53A1222, Revision 2, dated October 20,
2005.
(3) 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 FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, S.W., Renton, Washington; or 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/ibrlocations.html.
Issued in Renton, Washington, on March 7,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–4540 Filed 3–14–07; 8:45 am]
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Agencies
[Federal Register Volume 72, Number 50 (Thursday, March 15, 2007)]
[Rules and Regulations]
[Pages 12068-12070]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-4540]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24369; Directorate Identifier 2006-NM-001-AD;
Amendment 39-14990; AD 2007-06-09]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 737-600, -700, -700C, and
-800 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 Boeing Model 737-600, -700, -700C, and -
800 series airplanes. That AD currently requires replacing the point
``D'' splice fitting between windows number 1 and 2 with a new splice
fitting; performing an eddy current inspection for cracking of the
holes in the structure common to the new splice fitting, including
doing any related investigative actions; and performing corrective
actions if necessary. This new AD adds repetitive inspections for
cracking of the skin just below each splice fitting, and related
corrective actions if necessary. This AD results from full-scale
fuselage fatigue testing on the splice fitting that failed prior to the
design objective on Boeing Model 737-800 series airplanes, and a report
of a cracked splice fitting on an operational airplane. We are issuing
this AD to prevent cracking of the existing fitting, which may result
in cracking through the skin and consequent decompression of the flight
deck.
DATES: This AD becomes effective April 19, 2007.
The incorporation by reference of Boeing Alert Service Bulletin
737-53A1222, Revision 3, dated January 3, 2007, as listed in the
regulations, is approved by the Director of the Federal Register as of
April 19, 2007.
On December 21, 2005 (70 FR 72595, December 6, 2005), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 737-53A1222, Revision 2, dated October
20, 2005.
ADDRESSES: You may examine the AD docket on the Internet at https://
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,
[[Page 12069]]
Washington 98124-2207, for service information identified in this AD.
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; telephone (425)
917-6447; 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 2005-25-03, amendment
39-14396 (70 FR 72595, December 6, 2005). The existing AD applies to
certain Boeing Model 737-600, -700, -700C, and -800 series airplanes.
That NPRM was published in the Federal Register on April 11, 2006 (71
FR 18251). That NPRM proposed to continue to require replacing the
point ``D'' splice fitting between windows number 1 and 2 with a new
splice fitting; performing an eddy current inspection for cracking of
the holes in the structure common to the new splice fitting, including
doing any related investigative actions; and performing corrective
actions if necessary. That NPRM also proposed to add repetitive
inspections for cracking of the skin just below each splice fitting,
and related corrective actions if necessary.
Explanation of Revision Service Information
The NPRM referred to Boeing Alert Service Bulletin 737-53A1222,
Revision 2, as the appropriate source of service information for the
inspection of paragraph (g). Boeing has since revised the service
bulletin. Revision 3, dated January 3, 2007, corrects and clarifies
certain information and adds fastener options, but adds no additional
work for airplanes with splice fittings replaced as specified in a
previous version of the service bulletin. We have revised this final
rule to refer to Revision 3 of the service bulletin for the inspection
in paragraph (g), and to provide credit for work done in accordance
with Revision 2.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Support for the NPRM
One commenter, Continental Airlines, agrees with the NPRM.
Request To Provide an Alternate Method of Compliance (AMOC)
KLM Engineering and Maintenance requests that the FAA review the
inspection methods for the proposed one-time inspection of certain
fastener locations during the point ``D'' splice fitting replacement.
The commenter advises that, for certain fastener locations, an eddy
current open fastener hole is impractical and may not even be possible
due to structure build-up. The commenter requests that an AMOC be given
specifying fluorescent penetrant inspections instead of the eddy
current open fastener hole inspections. The commenter notes that use of
the fluorescent penetrant inspections has been coordinated with the
manufacturer.
Since we issued the NPRM, the manufacturer issued Revision 3 of
Boeing Alert Service Bulletin (ASB) 737-53A1222. Revision 3, dated
January 3, 2007, contains procedures for performing fluorescent
penetrant inspections. This final rule incorporates the revised service
bulletin; therefore, no AMOC will be necessary to do this type of
inspection. We have not changed this AD regarding this issue.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 563 airplanes of the affected design in the
worldwide fleet. We estimate that about 243 airplanes are on the U.S.
Register, and that the average labor rate is $80 per hour. The
following table provides the estimated costs for U.S. operators to
comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Work hours Parts airplane Fleet cost
----------------------------------------------------------------------------------------------------------------
Replacing splice fittings with new fittings 36 $15,445 $18,325 $4,452,975
(required by AD 2005-25-03)................
External detailed inspection (new action)... 1 0 80 \1\ 19,440
----------------------------------------------------------------------------------------------------------------
\1\ 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:
[[Page 12070]]
(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
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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]
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2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14396 (70 FR 72595, December 6, 2005) and by
adding the following new airworthiness directive (AD):
2007-06-09 Boeing: Amendment 39-14990. Docket No. FAA-2006-24369;
Directorate Identifier 2006-NM-001-AD.
Effective Date
(a) This AD becomes effective April 19, 2007.
Affected ADs
(b) This AD supersedes AD 2005-25-03.
Applicability
(c) This AD applies to Boeing Model 737-600, -700, -700C, and -
800 series airplanes, certificated in any category; as identified in
Boeing Alert Service Bulletin (ASB) 737-53A1222, Revision 3, dated
January 3, 2007.
Unsafe Condition
(d) This AD results from full-scale fuselage fatigue testing on
a splice fitting that failed prior to the design objective on Boeing
Model 737-800 series airplanes, and a report of a cracked splice
fitting on an operational airplane. We are issuing this AD to
prevent cracking of the existing fitting, which may result in
cracking through the skin and consequent decompression of the flight
deck.
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.
Restatement of Certain Requirements of AD 2005-25-03
Replacing the Splice Fittings
(f) Replace the splice fittings with new splice fittings in
accordance with the Accomplishment Instructions of Boeing ASB 737-
53A1222, Revision 2, dated October 20, 2005, or Revision 3, dated
January 3, 2007, at the times specified in paragraph (f)(1) or
(f)(2) of this AD, as applicable. Before further flight, do any
related investigative actions by accomplishing all the applicable
actions specified in the Accomplishment Instructions.
(1) For airplanes that have accumulated fewer than 13,500 total
flight cycles as December 21, 2005 (the effective date of AD 2005-
25-03): Replace prior to the accumulation of 13,500 total flight
cycles, or within 1,000 flight cycles after December 21, 2005,
whichever occurs later.
(2) For airplanes that have accumulated 13,500 or more total
flight cycles as of December 21, 2005: Replace at the later of the
times specified in paragraphs (f)(2)(i) and (f)(2)(ii) of this AD.
(i) Prior to the accumulation of 18,000 total flight cycles, or
within 1,000 flight cycles after December 21, 2005, whichever occurs
first.
(ii) Within 90 days after December 21, 2005.
New Requirements of This AD
Repetitive Inspections
(g) Within 24,000 flight cycles after accomplishing the actions
specified in paragraph (f) of this AD, perform an external detailed
inspection of the skin just below each splice fitting, in accordance
with the Accomplishment Instructions of Boeing ASB 737-53A1222,
Revision 3, dated January 3, 2007. Thereafter, repeat the external
detailed inspections at intervals not to exceed 24,000 flight
cycles.
Corrective Actions
(h) If any cracking is found during any inspection required by
this AD, prior to further flight, repair in accordance with a method
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA, or with a method approved in accordance with the
procedures specified in paragraph (j) of this AD.
Acceptable Method of Compliance
(i) Replacing the splice fitting and any related investigative
actions before December 21, 2005 (the effective date of AD 2005-25-
03), in accordance with Boeing Service Bulletin 737-53-1222, dated
June 6, 2002; or Boeing ASB 737-53A1222, Revision 1, dated January
30, 2003, is acceptable for compliance with the requirements of
paragraph (f) of this AD. An inspection done before the effective
date of this AD in accordance with Boeing ASB 737-53A1222, Revision
2, dated October 20, 2005, is acceptable for compliance with the
requirements of paragraph (g) of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Seattle ACO, FAA, 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 Sec.
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) 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.
(4) AMOCs approved previously in accordance with AD 2005-25-03,
amendment 39-14396, are approved as AMOCs for the corresponding
provisions of paragraphs (f) and (h) of this AD.
Material Incorporated by Reference
(k) You must use Boeing Alert Service Bulletin 737-53A1222,
Revision 2, dated October 20, 2005; or Boeing Alert Service Bulletin
737-53A1222, Revision 3, dated January 3, 2007; to perform the
actions that are required by this AD, unless the AD specifies
otherwise.
(1) The incorporation by reference of Boeing Alert Service
Bulletin 737-53A1222, Revision 3, dated January 3, 2007, is approved
by the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) On December 21, 2005 (70 FR 72595, December 6, 2005), the
Director of the Federal Register approved the incorporation by
reference of Boeing Alert Service Bulletin 737-53A1222, Revision 2,
dated October 20, 2005.
(3) 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 FAA, Transport Airplane Directorate, 1601
Lind Avenue, S.W., Renton, Washington; or 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 March 7, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-4540 Filed 3-14-07; 8:45 am]
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