Airworthiness Directives; Boeing Model 757-200, -200PF, and -200CB Series Airplanes, 58485-58487 [E6-16197]
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58485
Rules and Regulations
Federal Register
Vol. 71, No. 192
Wednesday, October 4, 2006
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT:
Federal Aviation Administration
Dennis Stremick, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6450; fax (425) 917–6590.
14 CFR Part 39
SUPPLEMENTARY INFORMATION:
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2006–24697; Directorate
Identifier 2006–NM–045–AD; Amendment
39–14781; AD 2006–20–11]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757–200, –200PF, and –200CB
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 757–200, –200PF, and
–200CB series airplanes. This AD
requires doing initial and repetitive
detailed or high frequency eddy current
inspections for cracks around the rivets
at the upper fastener row of the skin lap
splice of the fuselage, and repairing any
crack found. This AD results from a
report indicating that certain rivets were
incorrectly installed in some areas of the
skin lap splices during production
because they were drilled with a
countersink that was too deep. We are
issuing this AD to detect and correct
premature fatigue cracking at certain
skin lap splice locations of the fuselage,
and consequent rapid decompression of
the airplane.
DATES: This AD becomes effective
November 8, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of November 8, 2006.
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
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SUMMARY:
VerDate Aug<31>2005
14:25 Oct 03, 2006
Jkt 211001
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 would
apply to certain Boeing Model 757–200,
–200PF, and –200CB series airplanes.
That NPRM was published in the
Federal Register on May 9, 2006 (71 FR
26875). That NPRM proposed to require
doing initial and repetitive detailed or
high frequency eddy current (HFEC)
inspections for cracks around the rivets
at the upper fastener row of the skin lap
splice of the fuselage, and repairing any
crack found.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Support for NPRM
American Airlines agrees with the
NPRM and has no further comment at
this time.
NPRM Not Applicable
Continental Airlines states that, based
on the effectivity, the NPRM is not
applicable to its 757 fleet.
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Request To Add Credit for Alternate
Inspections
Northwest Airlines (NWA) and Air
Transport Association (ATA), on behalf
of member airlines, ask that, to avoid
unnecessary processing of an alternative
method of compliance (AMOC), credit
be allowed in this AD for accomplishing
the lap splice inspections specified in
Boeing Special Attention Service
Bulletin 757–53–0090, dated June 2,
2005 (referenced in the NPRM as the
source of service information for
accomplishing the required actions).
NWA states that paragraph 1.F. of the
referenced service bulletin specifies that
the lap splice inspections are approved
as an AMOC to AD 2001–20–12,
amendment 39–12460 (66 FR 52492,
October 16, 2001) for the significant
structural item (SSI) inspections. NWA
adds that AD 2006–11–11, amendment
39–14615 (71 FR 30278, May 26, 2006)
supersedes AD 2001–20–12.
We agree with the commenters.
Accomplishing the requirements in
paragraph (f) of AD 2006–11–11
terminates the requirements in
paragraph (f) of this AD. We have added
a new paragraph (i)(4) to this AD to
specify that the inspections in the
referenced service bulletin were
approved as an AMOC to AD 2006–11–
11.
Request To Revise Service Information
US Airways and ATA, on behalf of
member airlines, recommend that, prior
to release of a final rule, published
repair information be provided in a
subsequent revision to the referenced
service bulletin or the Boeing 757–200
Structural Repair Manual (SRM). U.S.
Airways states that published FAAapproved repair data as a means of
compliance to the proposed rule will
reduce the administrative burden of
processing AMOCs between the
operator and the Boeing Commercial
Airplanes Delegation Option
Authorization Organization. U.S.
Airways adds that providing repair data
in advance of the release of the final
rule will result in expedited repairs and
return airplanes to revenue service in a
timely manner.
We partially agree with the
commenters. Having all repair
procedures in one place can be simpler
for operators, but there is no repair
method defined as yet, and we do not
know if or when Boeing will revise its
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Federal Register / Vol. 71, No. 192 / Wednesday, October 4, 2006 / Rules and Regulations
service bulletin or SRM. Waiting to
include a revised service bulletin or
SRM in this action would delay
addressing an unsafe condition.
Therefore, we have made no change to
the AD in this regard.
Clarify Description of Production Rivets
Boeing asks that we clarify the
description of the production rivets
installed in the skin lap splices by
deleting ‘‘modified’’ when describing
the rivets. Boeing states that the
production rivets are commonly referred
to as ‘‘Briles’’ rivets, and are
manufactured with a 120-degree,
modified shear head. Boeing notes that
the current wording implies that the
rivets were modified before installation
on the aircraft.
We acknowledge Boeing’s request for
clarification. We have changed the
description in the Summary section and
in paragraph (d) of this AD as follows:
‘‘This AD results from a report
indicating that certain rivets were
incorrectly installed in some areas of the
skin lap splices during production
because they were drilled with a
countersink that was too deep.’’ The
Discussion section of the NPRM
preamble does not reappear in the final
rule.
Conclusion
We have carefully reviewed the
available data, including the comments
Airplane group
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. These changes will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
There are about 294 airplanes of the
affected design in the worldwide fleet.
This AD affects about 160 airplanes of
U.S. registry. The following tables
provide the estimated costs for U.S.
operators to comply with either the
detailed or HFEC inspections in this
AD.
Average hourly
labor rate
Work hours
Cost per
airplane
Estimated Costs for Detailed Inspection, per Inspection Cycle
Group
Group
Group
Group
1
2
3
4
............................................................................................................................
............................................................................................................................
............................................................................................................................
............................................................................................................................
7
6
12
10
$80
80
80
80
$560
480
960
800
80
80
80
80
960
880
1,600
1,200
Estimated Costs for HFEC Inspection, per Inspection Cycle
Group
Group
Group
Group
1
2
3
4
............................................................................................................................
............................................................................................................................
............................................................................................................................
............................................................................................................................
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.
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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,
VerDate Aug<31>2005
14:25 Oct 03, 2006
Jkt 211001
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
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Fmt 4700
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12
11
20
15
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 adding the following new
airworthiness directive (AD):
I
2006–20–11 Boeing: Amendment 39–14781.
Docket No. FAA–2006–24697;
Directorate Identifier 2006–NM–045–AD.
Effective Date
(a) This AD becomes effective November 8,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757–
200, –200PF, and –200CB series airplanes,
certificated in any category; as identified in
Boeing Special Attention Service Bulletin
757–53–0090, dated June 2, 2005.
Unsafe Condition
(d) This AD results from a report indicating
that certain rivets were incorrectly installed
in some areas of the skin lap splices during
production because they were drilled with a
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Federal Register / Vol. 71, No. 192 / Wednesday, October 4, 2006 / Rules and Regulations
countersink that was too deep. We are
issuing this AD to detect and correct
premature fatigue cracking at certain skin lap
splice locations of the fuselage 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.
9. This AMOC applies only to the common
areas inspected in accordance with Boeing
Special Attention Service Bulletin 757–53–
0090, dated June 2, 2005. All provisions of
AD 2006–11–11 that are not specifically
referenced in the above statements remain
fully applicable and must be complied with
as required by this AD. Operators may revise
their FAA-approved maintenance or
inspection program with these alternative
inspections for common areas.
Repair
(g) If any crack is found during any
inspection required by this AD: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
Material Incorporated by Reference
(j) You must use Boeing Special Attention
Service Bulletin 757–53–0090, dated June 2,
2005, 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 this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
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.
No Reporting Required
(h) Although Boeing Special Attention
Service Bulletin 757–53–0090, dated June 2,
2005, recommends that inspection results be
reported to the manufacturer, this AD does
not include that requirement.
Issued in Renton, Washington, on
September 22, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–16197 Filed 10–3–06; 8:45 am]
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Initial and Repetitive Inspections
(f) Do initial and repetitive detailed or high
frequency eddy current inspections for
cracking around the rivets at the upper
fastener row of the skin lap splice of the
fuselage by doing all the actions in
accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 757–53–0090, dated June 2,
2005, except as provided by paragraphs (g)
and (h) of this AD. Do the inspections at the
applicable times specified in Paragraph 1.E.,
‘‘Compliance,’’ of the service bulletin; except
where the service bulletin specifies a
compliance time after the original release
date of the service bulletin, this AD requires
compliance after the effective date of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (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.
(4) The inspections specified in paragraph
(f) of this AD are approved as an AMOC to
paragraph (h) of AD 2006–11–11, amendment
39–14615 for the inspections of Significant
Structural Item (SSI) 53–30–07 and 53–60–07
(fuselage lap splices, left and right upper
fastener row) listed in the May 2003 or June
2005 revision of the Boeing 757 Maintenance
Planning Data (MPD) Document D622N001–
VerDate Aug<31>2005
14:25 Oct 03, 2006
Jkt 211001
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–23145; Directorate
Identifier 2000–NM–215–AD; Amendment
39–14777; AD 2006–20–08]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–145, –145ER,
–145MR, –145LR, –145XR, –145MP, and
–145EP 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 all EMBRAER Model
EMB–145, –145ER, –145MR, –145LR,
–145XR, –145MP, and –145EP
airplanes. That AD currently requires
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Fmt 4700
Sfmt 4700
58487
repetitive inspections to detect cracking
or failure of the rod ends of the aileron
power control actuator (PCA), and
corrective actions if necessary. This new
AD requires the same repetitive
inspections of additional parts at new
inspection intervals for certain
airplanes; provides new corrective
actions; and provides an optional
terminating action for the requirements
of this AD. This AD results from the
issuance of mandatory continuing
airworthiness information by the
Brazilian airworthiness authority. We
are issuing this AD to detect and correct
cracking or breaking of the rod ends and
connecting fittings of the aileron PCA,
which could result in reduced
controllability of the airplane.
DATES: This AD becomes effective
November 8, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of November 8, 2006.
The Director of the Federal Register
approved the incorporation by reference
of EMBRAER Alert Service Bulletin
145–27–A054, Change 01, dated
February 17, 1999, on March 29, 1999
(64 FR 13892, March 23, 1999).
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 Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1175; fax (425) 227–1149.
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
E:\FR\FM\04OCR1.SGM
04OCR1
]]>Agencies
[Federal Register Volume 71, Number 192 (Wednesday, October 4, 2006)]
[Rules and Regulations]
[Pages 58485-58487]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-16197]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 71, No. 192 / Wednesday, October 4, 2006 /
Rules and Regulations
[[Page 58485]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24697; Directorate Identifier 2006-NM-045-AD;
Amendment 39-14781; AD 2006-20-11]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757-200, -200PF, and -
200CB Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 757-200, -200PF, and -200CB series airplanes. This
AD requires doing initial and repetitive detailed or high frequency
eddy current inspections for cracks around the rivets at the upper
fastener row of the skin lap splice of the fuselage, and repairing any
crack found. This AD results from a report indicating that certain
rivets were incorrectly installed in some areas of the skin lap splices
during production because they were drilled with a countersink that was
too deep. We are issuing this AD to detect and correct premature
fatigue cracking at certain skin lap splice locations of the fuselage,
and consequent rapid decompression of the airplane.
DATES: This AD becomes effective November 8, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 8,
2006.
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,
Washington 98124-2207, for the service information identified in this
proposed AD.
FOR FURTHER INFORMATION CONTACT: Dennis Stremick, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6450; 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 would apply to certain Boeing Model
757-200, -200PF, and -200CB series airplanes. That NPRM was published
in the Federal Register on May 9, 2006 (71 FR 26875). That NPRM
proposed to require doing initial and repetitive detailed or high
frequency eddy current (HFEC) inspections for cracks around the rivets
at the upper fastener row of the skin lap splice of the fuselage, and
repairing any crack found.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Support for NPRM
American Airlines agrees with the NPRM and has no further comment
at this time.
NPRM Not Applicable
Continental Airlines states that, based on the effectivity, the
NPRM is not applicable to its 757 fleet.
Request To Add Credit for Alternate Inspections
Northwest Airlines (NWA) and Air Transport Association (ATA), on
behalf of member airlines, ask that, to avoid unnecessary processing of
an alternative method of compliance (AMOC), credit be allowed in this
AD for accomplishing the lap splice inspections specified in Boeing
Special Attention Service Bulletin 757-53-0090, dated June 2, 2005
(referenced in the NPRM as the source of service information for
accomplishing the required actions). NWA states that paragraph 1.F. of
the referenced service bulletin specifies that the lap splice
inspections are approved as an AMOC to AD 2001-20-12, amendment 39-
12460 (66 FR 52492, October 16, 2001) for the significant structural
item (SSI) inspections. NWA adds that AD 2006-11-11, amendment 39-14615
(71 FR 30278, May 26, 2006) supersedes AD 2001-20-12.
We agree with the commenters. Accomplishing the requirements in
paragraph (f) of AD 2006-11-11 terminates the requirements in paragraph
(f) of this AD. We have added a new paragraph (i)(4) to this AD to
specify that the inspections in the referenced service bulletin were
approved as an AMOC to AD 2006-11-11.
Request To Revise Service Information
US Airways and ATA, on behalf of member airlines, recommend that,
prior to release of a final rule, published repair information be
provided in a subsequent revision to the referenced service bulletin or
the Boeing 757-200 Structural Repair Manual (SRM). U.S. Airways states
that published FAA-approved repair data as a means of compliance to the
proposed rule will reduce the administrative burden of processing AMOCs
between the operator and the Boeing Commercial Airplanes Delegation
Option Authorization Organization. U.S. Airways adds that providing
repair data in advance of the release of the final rule will result in
expedited repairs and return airplanes to revenue service in a timely
manner.
We partially agree with the commenters. Having all repair
procedures in one place can be simpler for operators, but there is no
repair method defined as yet, and we do not know if or when Boeing will
revise its
[[Page 58486]]
service bulletin or SRM. Waiting to include a revised service bulletin
or SRM in this action would delay addressing an unsafe condition.
Therefore, we have made no change to the AD in this regard.
Clarify Description of Production Rivets
Boeing asks that we clarify the description of the production
rivets installed in the skin lap splices by deleting ``modified'' when
describing the rivets. Boeing states that the production rivets are
commonly referred to as ``Briles'' rivets, and are manufactured with a
120-degree, modified shear head. Boeing notes that the current wording
implies that the rivets were modified before installation on the
aircraft.
We acknowledge Boeing's request for clarification. We have changed
the description in the Summary section and in paragraph (d) of this AD
as follows: ``This AD results from a report indicating that certain
rivets were incorrectly installed in some areas of the skin lap splices
during production because they were drilled with a countersink that was
too deep.'' The Discussion section of the NPRM preamble does not
reappear in the final rule.
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.
These changes will neither increase the economic burden on any operator
nor increase the scope of the AD.
Costs of Compliance
There are about 294 airplanes of the affected design in the
worldwide fleet. This AD affects about 160 airplanes of U.S. registry.
The following tables provide the estimated costs for U.S. operators to
comply with either the detailed or HFEC inspections in this AD.
----------------------------------------------------------------------------------------------------------------
Average hourly Cost per
Airplane group Work hours labor rate airplane
----------------------------------------------------------------------------------------------------------------
Estimated Costs for Detailed Inspection, per Inspection Cycle
----------------------------------------------------------------------------------------------------------------
Group 1................................................... 7 $80 $560
Group 2................................................... 6 80 480
Group 3................................................... 12 80 960
Group 4................................................... 10 80 800
----------------------------------------------------------------------------------------------------------------
Estimated Costs for HFEC Inspection, per Inspection Cycle
----------------------------------------------------------------------------------------------------------------
Group 1................................................... 12 80 960
Group 2................................................... 11 80 880
Group 3................................................... 20 80 1,600
Group 4................................................... 15 80 1,200
----------------------------------------------------------------------------------------------------------------
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
adding the following new airworthiness directive (AD):
2006-20-11 Boeing: Amendment 39-14781. Docket No. FAA-2006-24697;
Directorate Identifier 2006-NM-045-AD.
Effective Date
(a) This AD becomes effective November 8, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757-200, -200PF, and -200CB
series airplanes, certificated in any category; as identified in
Boeing Special Attention Service Bulletin 757-53-0090, dated June 2,
2005.
Unsafe Condition
(d) This AD results from a report indicating that certain rivets
were incorrectly installed in some areas of the skin lap splices
during production because they were drilled with a
[[Page 58487]]
countersink that was too deep. We are issuing this AD to detect and
correct premature fatigue cracking at certain skin lap splice
locations of the fuselage 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.
Initial and Repetitive Inspections
(f) Do initial and repetitive detailed or high frequency eddy
current inspections for cracking around the rivets at the upper
fastener row of the skin lap splice of the fuselage by doing all the
actions in accordance with the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 757-53-0090, dated June 2, 2005,
except as provided by paragraphs (g) and (h) of this AD. Do the
inspections at the applicable times specified in Paragraph 1.E.,
``Compliance,'' of the service bulletin; except where the service
bulletin specifies a compliance time after the original release date
of the service bulletin, this AD requires compliance after the
effective date of this AD.
Repair
(g) If any crack is found during any inspection required by this
AD: Before further flight, repair the crack using a method approved
in accordance with the procedures specified in paragraph (i) of this
AD.
No Reporting Required
(h) Although Boeing Special Attention Service Bulletin 757-53-
0090, dated June 2, 2005, recommends that inspection results be
reported to the manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (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.
(4) The inspections specified in paragraph (f) of this AD are
approved as an AMOC to paragraph (h) of AD 2006-11-11, amendment 39-
14615 for the inspections of Significant Structural Item (SSI) 53-
30-07 and 53-60-07 (fuselage lap splices, left and right upper
fastener row) listed in the May 2003 or June 2005 revision of the
Boeing 757 Maintenance Planning Data (MPD) Document D622N001-9. This
AMOC applies only to the common areas inspected in accordance with
Boeing Special Attention Service Bulletin 757-53-0090, dated June 2,
2005. All provisions of AD 2006-11-11 that are not specifically
referenced in the above statements remain fully applicable and must
be complied with as required by this AD. Operators may revise their
FAA-approved maintenance or inspection program with these
alternative inspections for common areas.
Material Incorporated by Reference
(j) You must use Boeing Special Attention Service Bulletin 757-
53-0090, dated June 2, 2005, 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
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
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 September 22, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-16197 Filed 10-3-06; 8:45 am]
BILLING CODE 4910-13-P
