Airworthiness Directives; Boeing Model 767-200 and -300 Series Airplanes, 73935-73937 [05-23957]
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Federal Register / Vol. 70, No. 239 / Wednesday, December 14, 2005 / Rules and Regulations
73935
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Service bulletin
Revision level
EMBRAER Service Bulletin 14LEG–49–0006 .....................................................
EMBRAER Service Bulletin 145–49–0029 ..........................................................
EMBRAER Service Bulletin 145–49–0023 ..........................................................
Original ..................................................
02 ..........................................................
01 ..........................................................
Issued in Renton, Washington, on
December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–23899 Filed 12–13–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21715; Directorate
Identifier 2004–NM–277–AD; Amendment
39–14416; AD 2005–25–23]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–200 and –300 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
Examining the Docket
The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 767–200 and –300 series
airplanes. This AD requires measuring
the turnbuckle gap of the inflation
cylinder of the off-wing emergency
escape slide; corrective action if
necessary; and installing a safety device
on the inflation cylinder of the off-wing
emergency escape slide. This AD results
from a report indicating that the
inflation trigger cable may inadvertently
disconnect from the inflation turnbuckle
of the inflation cylinder of the off-wing
emergency escape slide, due to incorrect
spacing of the cable insertion gap; and
additional reports indicating that the
pull force increase mechanism on the
off-wing charged cylinder assemblies of
the escape slide may be inadvertently
disengaged. We are issuing this AD to
prevent failed deployment of the
emergency escape slide during an
emergency, which could impede an
evacuation and result in injury to
passengers or airplane crewmembers, or
inadvertent inflation and loss of an
emergency escape slide during flight,
which could result in possible structural
damage to the airplane.
DATES: This AD becomes effective
January 18, 2006.
SUMMARY:
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15:23 Dec 13, 2005
Jkt 208001
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of January 18, 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 service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Sue
Rosanske, Aerospace Engineer, Cabin
Safety and Environmental Systems
Branch, ANM–150S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6448;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
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 767–200
and –300 series airplanes. That NPRM
was published in the Federal Register
on July 6, 2005 (70 FR 38821). That
NPRM proposed to require measuring
the turnbuckle gap of the inflation
cylinder of the off-wing emergency
escape slide; corrective action if
necessary; and installing a safety device
on the inflation cylinder of the off-wing
emergency escape slide.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
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Fmt 4700
Sfmt 4700
Date
April 20, 2005.
October 14, 2005.
April 25, 2005.
Supportive Comment
One commenter concurs with the
content of the NPRM.
Requests To Extend Compliance Time
Several commenters ask that the
compliance time for the actions
specified in paragraph (f) of the NPRM
be extended to 36 months. The
commenters make their requests to
extend the compliance time for several
reasons, including:
• To align the proposed actions with
existing maintenance schedules for
corresponding levels of maintenance on
escape slide systems and increased
efficiency and management of spare
parts stocks of escape slides.
• To correspond with the compliance
time specified in the Goodrich service
information (referenced in the NPRM) of
accomplishing the actions at the next
scheduled maintenance visit.
• To be consistent with slide
restoration intervals that allow the
modifications of the inflation cylinder
to be accomplished in a controlled shop
environment. In addition,
accomplishing the actions within 18
months would require operators to
significantly increase spare parts stock
for escape slides, which would cause an
undue burden and substantial cost
increase.
• To be consistent with the removal
of the off-wing escape slide cylinders
from the airplane for cylinder
hydrostatic testing and overhaul, which
eliminates the need for multiple
removals. Additional removals would
increase the potential for injuries to
maintenance personnel and damage to
parts.
We agree that the compliance time
may be extended. We have reconsidered
the urgency of the unsafe condition and
the amount of work related to the
required actions, in addition to the fact
that our intent was to require the actions
be accomplished during regular
maintenance visits. We find that
extending the compliance time from 18
to 36 months will not adversely affect
safety, and, for the majority of affected
operators, will allow the required
actions to be performed during regularly
scheduled maintenance at a base where
special equipment and trained
maintenance personnel will be available
if necessary. We have changed the
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73936
Federal Register / Vol. 70, No. 239 / Wednesday, December 14, 2005 / Rules and Regulations
compliance time for accomplishing the
actions required by paragraph (f) of this
AD accordingly.
Request To Revise Goodrich Service
Bulletin
Two commenters ask that Goodrich
Service Bulletin 130104–25–328,
Revision 1, dated July 23, 2003,
referenced in the NPRM as an additional
source of service information for
accomplishing the actions, be revised to
include a change to the part numbers for
modified off-wing cylinder assemblies.
One commenter states that this should
be done in order to track compliance
with the AD.
We disagree with the commenters’
request. Revision 1 of the service
bulletin already specifies a change to
the part numbers for the off-wing
cylinder assemblies and the regulator
valve to account for the modification.
The parts are identified in Table 6 of the
Accomplishment Instructions of the
service bulletin. We have made no
change to the AD in this regard.
Request To Increase Work Hours
One commenter asks that we increase
the amount of time needed to complete
the proposed actions to 6 work hours
per airplane.
We do not agree that it is necessary
to revise the work hour estimates of the
NPRM, which reflect only the actual
time needed for accomplishing the
actions based on the best data available
from the manufacturer. The work hours
do not include the time for planning,
access and close, and associated
administrative actions. The compliance
times in this AD should allow ample
time for operators to do the required
actions at the same time as scheduled
major airplane inspection and
maintenance activities, which would
reduce the additional time associated
with special scheduling. We have made
no change to the AD in this regard.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have changed this AD to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
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.
VerDate Aug<31>2005
15:23 Dec 13, 2005
Jkt 208001
Costs of Compliance
There are about 696 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 297 airplanes
of U.S. registry.
The inspection takes about 1 work
hour per airplane, at an average labor
rate of $65 per work hour. Based on
these figures, the estimated cost of the
inspection for U.S. operators is $19,305,
or $65 per airplane.
The safety device installation takes
about 3 work hours per airplane, at an
average labor rate of $65 per work hour.
Required parts cost is minimal. Based
on these figures, the estimated cost of
the installation for U.S. operators is
$57,915, or $195 per airplane.
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
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Frm 00032
Fmt 4700
Sfmt 4700
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 adding the following new
airworthiness directive (AD):
I
2005–25–23 Boeing: Amendment 39–14416.
Docket No. FAA–2005–21715;
Directorate Identifier 2004–NM–277–AD.
Effective Date
(a) This AD becomes effective January 18,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767–
200 and –300 series airplanes; certificated in
any category; equipped with off-wing
emergency escape slides; as identified in
Boeing Special Attention Service Bulletin
767–25–0358, dated September 18, 2003; and
Boeing Special Attention Service Bulletin
767–25–0317, dated June 27, 2002.
Unsafe Condition
(d) This AD was prompted by a report
indicating that the inflation trigger cable may
inadvertently disconnect from the inflation
turnbuckle of the inflation cylinder of the offwing emergency escape slide, due to
incorrect spacing of the cable insertion gap;
and additional reports indicating that the
pull force increase mechanism (PFIM) on the
off-wing charged cylinder assemblies of the
escape slide may be inadvertently
disengaged. We are issuing this AD to
prevent failed deployment of the emergency
escape slide during an emergency, which
could impede an evacuation and result in
injury to passengers or airplane
crewmembers, or inadvertent inflation and
loss of an emergency escape slide during
flight, which could result in possible
structural damage to 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.
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Federal Register / Vol. 70, No. 239 / Wednesday, December 14, 2005 / Rules and Regulations
Measurement/Corrective Action
(f) Within 36 months after the effective
date of this AD: Accomplish the actions
specified in paragraphs (f)(1) and (f)(2) of this
AD.
(1) Measure the turnbuckle gap of the
inflation cylinder of the off-wing emergency
escape slides to ensure it meets the
maximum allowable spacing limit and do
applicable corrective actions by doing all the
actions specified in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 767–25–0358, dated
September 18, 2003. Accomplish any
corrective action before further flight in
accordance with the service bulletin.
(2) Install a safety device on the PFIM of
the inflation cylinder of the off-wing
emergency escape slides, and part-mark the
inflation cylinder as applicable, by doing all
the actions specified in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 767–25–0317, dated June 27,
2002.
Note 1: Goodrich Service Bulletins
130104–25–342, dated July 23, 2003; and
130104–25–328, Revision 1, dated July 23,
2003; may be used as additional sources of
service information for accomplishing the
actions.
Parts Installation
(g) As of the effective date of this AD, no
person may install an inflation cylinder of
the off-wing emergency escape slides on any
airplane, unless it has been modified
according to paragraph (f) of this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle Aircraft
Certification Office, 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 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.
Material Incorporated by Reference
(i) You must use Boeing Special Attention
Service Bulletin 767–25–0358, dated
September 18, 2003; and Boeing Special
Attention Service Bulletin 767–25–0317,
dated June 27, 2002; 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 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/
VerDate Aug<31>2005
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Jkt 208001
73937
federal_register/code_of_federal_regulations/
ibr_locations.html.
Regulatory Information
Issued in Renton, Washington, on
December 6, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–23957 Filed 12–13–05; 8:45 am]
Under 5 U.S.C. 553(d)(3), the Coast
Guard finds that good cause exists for
making this rule effective less than 30
days after publication in the Federal
Register. Preliminary analysis indicates
that most vessel operators will not be
inconvenienced by the special
operations. Large oceangoing vessels do
not normally travel this far upstream on
the Willamette and the majority of
recreational vessels can pass the
drawbridge without an opening. Tugs
and tows are the most common vessels
that would have to proceed with extra
caution. There is a single frequent user
of the drawspan, who agreed to the plan
prior to publication of the NPRM. The
Burnside Bridge is part of a heavily
traveled commuter arterial that serves
downtown Portland.
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 117
[CGD13–05–023]
RIN 1625–AA09
Drawbridge Operation Regulations;
Willamette River, Portland, OR
Coast Guard, DHS.
ACTION: Final rule.
AGENCY:
SUMMARY: The Coast Guard is revising
the drawbridge operation regulations for
bridges on the Willamette River,
Oregon. The modification will
reorganize the text into a more
understandable format with minor
editing of the regulations and change
the operating regulations for the draw of
the Burnside Bridge across the
Willamette River, mile 12.4, at Portland,
Oregon. The change will enable the
bridge owner to provide single-leaf
operation of the Burnside Bridge, except
during the Rose Festival, to facilitate
major structural and mechanical
rehabilitation of the bridge.
DATES: This rule is effective January 2,
2006.
ADDRESSES: Comments and materials
received from the public, as well as
documents indicated in this preamble as
being available in the docket, are part of
docket [CG13–05–023] and are available
for inspection or copying at the
Waterways Management Branch
between 7:30 a.m. and 4 p.m., Monday
through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT:
Austin Pratt, Chief, Bridge Section,
(206) 220–7282.
SUPPLEMENTARY INFORMATION:
Regulatory History
On August 22, 2005, we published a
notice of proposed rulemaking (NPRM)
entitled ‘‘Drawbridge Operation
Regulations; Willamette River, Portland,
Oregon’’ in the Federal Register (70 FR
48929). We received no letters
commenting on the proposed rule. No
public meeting was requested, and none
was held.
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Background and Purpose
The operating regulations currently in
effect for the drawbridges on the
Willamette River are at 33 CFR 117.897.
The regulations as they are currently
written are confusing as to which
exceptions apply to which bridge. The
reorganization of the text will enhance
and facilitate comprehension of the
regulations’ meaning.
The rule will enable Multnomah
County, the owner of the Burnside
Bridge, to rehabilitate the structure. The
work includes repairing the drawbridge
mechanism, replacing the concrete deck
and repairing corroded steel. One side
will be disabled throughout the period.
The operable side will be indicated via
Local Notice to Mariners.
The Burnside Bridge in the closed
position provides 65.5 feet of vertical
clearance above 0.0 datum Corps of
Engineers at the center of the bascule
and 205 feet of horizontal clearance.
Drawbridge openings are provided on
average 40 times monthly for
recreational vessels, tugs and tows, and
floating construction equipment. This
averages less than twice a day for
opening frequency.
The current regulation provides that
the spans need not open for the passage
of vessels from 7 a.m. to 9 a.m. and from
4 p.m. to 6 p.m. Monday through
Friday, except New Years Day,
Memorial Day, Fourth of July, Labor
Day, Thanksgiving Day, and Christmas
Day. From 8 a.m. to 5 p.m., Monday
through Friday, one hour’s notice is
required for all openings and two hours
notice at all other times. The draw
operates on signal during Rose Festival
Week and whenever the river level
reaches and remains above +12 feet.
E:\FR\FM\14DER1.SGM
14DER1
]]>Agencies
[Federal Register Volume 70, Number 239 (Wednesday, December 14, 2005)]
[Rules and Regulations]
[Pages 73935-73937]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23957]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21715; Directorate Identifier 2004-NM-277-AD;
Amendment 39-14416; AD 2005-25-23]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-200 and -300 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 767-200 and -300 series airplanes. This AD
requires measuring the turnbuckle gap of the inflation cylinder of the
off-wing emergency escape slide; corrective action if necessary; and
installing a safety device on the inflation cylinder of the off-wing
emergency escape slide. This AD results from a report indicating that
the inflation trigger cable may inadvertently disconnect from the
inflation turnbuckle of the inflation cylinder of the off-wing
emergency escape slide, due to incorrect spacing of the cable insertion
gap; and additional reports indicating that the pull force increase
mechanism on the off-wing charged cylinder assemblies of the escape
slide may be inadvertently disengaged. We are issuing this AD to
prevent failed deployment of the emergency escape slide during an
emergency, which could impede an evacuation and result in injury to
passengers or airplane crewmembers, or inadvertent inflation and loss
of an emergency escape slide during flight, which could result in
possible structural damage to the airplane.
DATES: This AD becomes effective January 18, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of January 18,
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 service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Sue Rosanske, Aerospace Engineer,
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 917-6448; 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
767-200 and -300 series airplanes. That NPRM was published in the
Federal Register on July 6, 2005 (70 FR 38821). That NPRM proposed to
require measuring the turnbuckle gap of the inflation cylinder of the
off-wing emergency escape slide; corrective action if necessary; and
installing a safety device on the inflation cylinder of the off-wing
emergency escape slide.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Supportive Comment
One commenter concurs with the content of the NPRM.
Requests To Extend Compliance Time
Several commenters ask that the compliance time for the actions
specified in paragraph (f) of the NPRM be extended to 36 months. The
commenters make their requests to extend the compliance time for
several reasons, including:
To align the proposed actions with existing maintenance
schedules for corresponding levels of maintenance on escape slide
systems and increased efficiency and management of spare parts stocks
of escape slides.
To correspond with the compliance time specified in the
Goodrich service information (referenced in the NPRM) of accomplishing
the actions at the next scheduled maintenance visit.
To be consistent with slide restoration intervals that
allow the modifications of the inflation cylinder to be accomplished in
a controlled shop environment. In addition, accomplishing the actions
within 18 months would require operators to significantly increase
spare parts stock for escape slides, which would cause an undue burden
and substantial cost increase.
To be consistent with the removal of the off-wing escape
slide cylinders from the airplane for cylinder hydrostatic testing and
overhaul, which eliminates the need for multiple removals. Additional
removals would increase the potential for injuries to maintenance
personnel and damage to parts.
We agree that the compliance time may be extended. We have
reconsidered the urgency of the unsafe condition and the amount of work
related to the required actions, in addition to the fact that our
intent was to require the actions be accomplished during regular
maintenance visits. We find that extending the compliance time from 18
to 36 months will not adversely affect safety, and, for the majority of
affected operators, will allow the required actions to be performed
during regularly scheduled maintenance at a base where special
equipment and trained maintenance personnel will be available if
necessary. We have changed the
[[Page 73936]]
compliance time for accomplishing the actions required by paragraph (f)
of this AD accordingly.
Request To Revise Goodrich Service Bulletin
Two commenters ask that Goodrich Service Bulletin 130104-25-328,
Revision 1, dated July 23, 2003, referenced in the NPRM as an
additional source of service information for accomplishing the actions,
be revised to include a change to the part numbers for modified off-
wing cylinder assemblies. One commenter states that this should be done
in order to track compliance with the AD.
We disagree with the commenters' request. Revision 1 of the service
bulletin already specifies a change to the part numbers for the off-
wing cylinder assemblies and the regulator valve to account for the
modification. The parts are identified in Table 6 of the Accomplishment
Instructions of the service bulletin. We have made no change to the AD
in this regard.
Request To Increase Work Hours
One commenter asks that we increase the amount of time needed to
complete the proposed actions to 6 work hours per airplane.
We do not agree that it is necessary to revise the work hour
estimates of the NPRM, which reflect only the actual time needed for
accomplishing the actions based on the best data available from the
manufacturer. The work hours do not include the time for planning,
access and close, and associated administrative actions. The compliance
times in this AD should allow ample time for operators to do the
required actions at the same time as scheduled major airplane
inspection and maintenance activities, which would reduce the
additional time associated with special scheduling. We have made no
change to the AD in this regard.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have changed this AD to clarify the appropriate procedure for
notifying the principal inspector before using any approved AMOC on any
airplane to which the AMOC applies.
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 696 airplanes of the affected design in the
worldwide fleet. This AD will affect about 297 airplanes of U.S.
registry.
The inspection takes about 1 work hour per airplane, at an average
labor rate of $65 per work hour. Based on these figures, the estimated
cost of the inspection for U.S. operators is $19,305, or $65 per
airplane.
The safety device installation takes about 3 work hours per
airplane, at an average labor rate of $65 per work hour. Required parts
cost is minimal. Based on these figures, the estimated cost of the
installation for U.S. operators is $57,915, or $195 per airplane.
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):
2005-25-23 Boeing: Amendment 39-14416. Docket No. FAA-2005-21715;
Directorate Identifier 2004-NM-277-AD.
Effective Date
(a) This AD becomes effective January 18, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767-200 and -300 series
airplanes; certificated in any category; equipped with off-wing
emergency escape slides; as identified in Boeing Special Attention
Service Bulletin 767-25-0358, dated September 18, 2003; and Boeing
Special Attention Service Bulletin 767-25-0317, dated June 27, 2002.
Unsafe Condition
(d) This AD was prompted by a report indicating that the
inflation trigger cable may inadvertently disconnect from the
inflation turnbuckle of the inflation cylinder of the off-wing
emergency escape slide, due to incorrect spacing of the cable
insertion gap; and additional reports indicating that the pull force
increase mechanism (PFIM) on the off-wing charged cylinder
assemblies of the escape slide may be inadvertently disengaged. We
are issuing this AD to prevent failed deployment of the emergency
escape slide during an emergency, which could impede an evacuation
and result in injury to passengers or airplane crewmembers, or
inadvertent inflation and loss of an emergency escape slide during
flight, which could result in possible structural damage to 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 73937]]
Measurement/Corrective Action
(f) Within 36 months after the effective date of this AD:
Accomplish the actions specified in paragraphs (f)(1) and (f)(2) of
this AD.
(1) Measure the turnbuckle gap of the inflation cylinder of the
off-wing emergency escape slides to ensure it meets the maximum
allowable spacing limit and do applicable corrective actions by
doing all the actions specified in the Accomplishment Instructions
of Boeing Special Attention Service Bulletin 767-25-0358, dated
September 18, 2003. Accomplish any corrective action before further
flight in accordance with the service bulletin.
(2) Install a safety device on the PFIM of the inflation
cylinder of the off-wing emergency escape slides, and part-mark the
inflation cylinder as applicable, by doing all the actions specified
in the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 767-25-0317, dated June 27, 2002.
Note 1: Goodrich Service Bulletins 130104-25-342, dated July 23,
2003; and 130104-25-328, Revision 1, dated July 23, 2003; may be
used as additional sources of service information for accomplishing
the actions.
Parts Installation
(g) As of the effective date of this AD, no person may install
an inflation cylinder of the off-wing emergency escape slides on any
airplane, unless it has been modified according to paragraph (f) of
this AD.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Seattle Aircraft Certification Office, 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 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.
Material Incorporated by Reference
(i) You must use Boeing Special Attention Service Bulletin 767-
25-0358, dated September 18, 2003; and Boeing Special Attention
Service Bulletin 767-25-0317, dated June 27, 2002; 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 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 December 6, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-23957 Filed 12-13-05; 8:45 am]
BILLING CODE 4910-13-P
