Airworthiness Directives; Boeing Model 727 Airplanes, 66743-66745 [E8-25686]
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Federal Register / Vol. 73, No. 219 / Wednesday, November 12, 2008 / Rules and Regulations
Safety and Environmental Systems Branch,
ANM–150S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6476; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Material Incorporated by Reference
(i) You must use Boeing Special Attention
Service Bulletin 757–30–0024, Revision 1,
dated October 25, 2007, 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 Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207; telephone 206–
544–9990; fax 206–766–5682; e-mail
DDCS@boeing.com; Internet https://
www.myboeingfleet.com.
(3) You may review copies of the service
information incorporated by reference at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., 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/code_
of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on October
10, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–25636 Filed 11–10–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0151; Directorate
Identifier 2007–NM–347–AD; Amendment
39–15708; AD 2008–22–12]
RIN 2120–AA64
mstockstill on PROD1PC66 with RULES
Airworthiness Directives; Boeing
Model 727 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
VerDate Aug<31>2005
18:26 Nov 10, 2008
Jkt 217001
Boeing Model 727 airplanes. This AD
requires repetitive inspections for any
crack in the area of the elevator side
fitting/hinge fitting joint and for any
crack or elongation inside and outside
of the holes in the clevis and in the lug,
corrective actions if necessary, and
other specified actions. This AD results
from reports of elongated holes and
cracks found in the lugs of the
attachment fittings of the elevator
quadrant upper support assembly at the
tip of the vertical fin. We are issuing
this AD to detect and correct damage to
the aft attachment lugs of the elevator
quadrant support assembly that could
lead to failure of the lugs. This
condition could accelerate wear
elsewhere in the elevator control
system, which could reduce the crew’s
ability to maintain safe flight.
DATES: This AD is effective December
17, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 17, 2008.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207;
telephone 206–544–9990; fax 206–766–
5682; e-mail DDCS@boeing.com;
Internet https://
www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 917–6577; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to all
Boeing Model 727 airplanes. That
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
66743
NPRM was published in the Federal
Register on February 8, 2008 (73 FR
7489). That NPRM proposed to require
repetitive inspections for any crack in
the area of the elevator side fitting/hinge
fitting joint and for any crack or
elongation inside and outside of the
holes in the clevis and in the lug,
corrective actions if necessary, and
other specified actions.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received from
the two commenters.
Support for the NPRM
Boeing concurs with the NPRM.
Request To Extend Compliance Time
FedEx requests that we extend the
compliance time from 18 months to 30
months for doing the initial inspections
of the side and hinge fittings of the
elevator control quadrant upper support
assembly. FedEx states that, prior to
issuance of the AD, it will take
immediate action to accomplish the
inspections within the required
timetable, but that the 18-month
compliance time will likely cause FedEx
to do the inspections outside of
scheduled heavy maintenance. FedEx,
therefore, requests an extension of the
compliance time, so that it may
accomplish the initial inspections for its
entire fleet during its next scheduled Ccheck. FedEx states that it prefers to do
the inspections at a maintenance facility
during a scheduled heavy maintenance
check because of the difficulty
associated in providing safe and
adequate access to the inspection areas,
the availability of the requisite tooling,
and the presence of skilled mechanics.
FedEx also requests that we extend
the calendar time from 24 months to 30
months for doing the repetitive
inspections. (The NPRM proposed
accomplishing those inspections within
24 months, 4,000 flight hours, or 3,000
flight cycles, whichever occurs first.)
FedEx states that an increase in calendar
time should provide an equivalent level
of safety because it operates its airplanes
at a low, daily-utilization rate, thereby,
keeping the flight cycle and flight hour
count significantly below the proposed
requirement, even after 30 months of
calendar time has elapsed. FedEx also
states that increasing the calendar time
for the repetitive inspections in this way
will allow FedEx to accomplish the
inspections within its heavy
maintenance schedule.
We disagree with the FedEx’s request
to extend the compliance times for the
initial inspection and repetitive interval.
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Federal Register / Vol. 73, No. 219 / Wednesday, November 12, 2008 / Rules and Regulations
In developing appropriate compliance
times for these actions, we considered
the urgency associated with the subject
unsafe condition, the average utilization
rate of the affected fleet, and the
practical aspect of accomplishing the
required actions within a period of time
that corresponds to the normal
scheduled maintenance for most
affected operators. Although FedEx did
not submit any technical data to support
its request, its airplane utilization rate
might possibly support an extension in
the compliance time. However, FedEx’s
airplane utilization rate might not be
typical for most operators, and we
believe that the required compliance
times specified in the referenced service
bulletins coincides with most operators’
utilization rates. If FedEx’s airplane
utilization rate and maintenance
program for the inspection area prove
that the new compliance time would
provide an acceptable level of safety,
FedEx may apply for an AMOC
according to the provisions in paragraph
(i) of this AD. We have not changed the
AD in this regard.
products identified in this rulemaking
action.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting the AD
as proposed.
List of Subjects in 14 CFR Part 39
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Costs of Compliance
We estimate that this AD affects 401
airplanes of U.S. registry. We also
estimate that it takes about 2 work-hours
per product to comply with this AD.
The average labor rate is $80 per workhour. Based on these figures, we
estimate the cost of this AD to the U.S.
operators to be $64,160, or $160 per
product, 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
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18:26 Nov 10, 2008
Jkt 217001
Regulatory Findings
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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2008–22–12 Boeing: Amendment 39–
15708. Docket No. FAA–2008–0151;
Directorate Identifier 2007–NM–347–AD.
Effective Date
(a) This airworthiness directive (AD) is
effective December 17, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model
727, 727C, 727–100, 727–100C, 727–200, and
727–200F series airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from reports of
elongated holes and cracks found in the lugs
of the attachment fittings of the elevator
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
quadrant upper support assembly at the tip
of the vertical fin. We are issuing this AD to
detect and correct damage to the aft
attachment lugs of the elevator quadrant
support assembly that could lead to failure of
the lugs. This condition could accelerate
wear elsewhere in the elevator control
system, which could reduce the crew’s
ability to maintain safe flight.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Repetitive Inspections and Corrective/Other
Specified Actions
(f) At the applicable compliance times
specified in paragraph 1.E. of Boeing Special
Attention Service Bulletin 727–55–0092,
dated June 4, 2007, except as provided by
paragraph (g) of this AD: Do the detailed
inspection for any crack in the area of the
elevator side fitting/hinge fitting joint,
detailed inspections for elongation inside
and outside of the holes in the clevis and in
the lug, and high frequency eddy current
(HFEC) inspections for any crack inside and
outside of the holes in the clevis and in the
lug, and do all the applicable corrective
actions and other specified actions, by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of the service bulletin, except as
provided by paragraph (h) of this AD. Repeat
the inspections thereafter at the applicable
intervals specified in paragraph 1.E. of the
service bulletin. Accomplishing the repair or
modification specified in Part 3 of the service
bulletin terminates only the repetitive
inspections specified in Part 2 of the service
bulletin.
Exceptions to Compliance Times
(g) Where paragraph 1.E. of Boeing Special
Attention Service Bulletin 727–55–0092,
dated June 4, 2007, specifies counting the
compliance time from ‘‘. . . the date on this
service bulletin,’’ this AD requires counting
the compliance time from the effective date
of this AD. Where paragraph 1.E. of the
service bulletin specifies a compliance time
of ‘‘. . . 18 months . . . ’’ or ‘‘24
months . . .,’’ this AD requires a compliance
time of 30 months.
Exception to Corrective Actions
(h) If any damage beyond the repair limits
or any crack is found in the area of the
elevator side fitting/hinge fitting joint during
any inspection required by this AD, and
Boeing Special Attention Service Bulletin
727–55–0092, dated June 4, 2007, specifies to
contact Boeing for appropriate action: Before
further flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, ATTN:
Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
917–6577; fax (425) 917–6590; has the
E:\FR\FM\12NOR1.SGM
12NOR1
Federal Register / Vol. 73, No. 219 / Wednesday, November 12, 2008 / Rules and Regulations
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(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.
Material Incorporated by Reference
(j) You must use Boeing Special Attention
Service Bulletin 727–55–0092, dated June 4,
2007, 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 Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207; telephone 206–
544–9990; fax 206–766–5682; e-mail
DDCS@boeing.com; Internet https://
www.myboeingfleet.com.
(3) You may review copies of the service
information incorporated by reference at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., 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/code_of_
federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on October
9, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–25686 Filed 11–10–08; 8:45 am]
mstockstill on PROD1PC66 with RULES
BILLING CODE 4910–13–P
VerDate Aug<31>2005
18:26 Nov 10, 2008
Jkt 217001
66745
DEPARTMENT OF TRANSPORTATION
Discussion
Federal Aviation Administration
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on August 7, 2008 (73 FR
45891). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
14 CFR Part 39
[Docket No. FAA–2008–0849; Directorate
Identifier 2008–NM–080–AD; Amendment
39–15709; AD 2008–22–13]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A310 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Two operators of A300 aircraft fitted with
General Electric (GE) CF6–50 engine series
have reported cracks on the lower side of Rib
5 in the pylon box.
*
*
*
*
*
Investigations disclosed that these cracks
are due to the stresses resulting from the
pressure applied by the thrust reverser cowl
bumpers.
*
*
*
*
*
Cracking of the engine pylons could
result in reduced structural integrity of
the engine support structure. We are
issuing this AD to require actions to
correct the unsafe condition on these
products.
This AD becomes effective
December 17, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 17, 2008.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
DATES:
PO 00000
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Fmt 4700
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Two operators of A300 aircraft fitted with
General Electric (GE) CF6–50 engine series
have reported cracks on the lower side of Rib
5 in the pylon box.
The concerned area is similar on A310
aircraft fitted with GE CF6–80A or CF6–80C
series engines.
Investigations disclosed that these cracks
are due to the stresses resulting from the
pressure applied by the thrust reverser cowl
bumpers.
As a result of the A310 Extended Service
Goal (ESG) study, an inspection programme
of this area is required by this Airworthiness
Directive (AD).
A similar inspection programme is being
contemplated for A300 and A300–600 series
aircraft.
Cracking of the engine pylons could
result in reduced structural integrity of
the engine support structure. Corrective
actions include modifying the Rib 5 in
the pylon box. You may obtain further
information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a Note within the AD.
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]]>Agencies
[Federal Register Volume 73, Number 219 (Wednesday, November 12, 2008)]
[Rules and Regulations]
[Pages 66743-66745]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-25686]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0151; Directorate Identifier 2007-NM-347-AD;
Amendment 39-15708; AD 2008-22-12]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 727 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Boeing Model 727 airplanes. This AD requires repetitive inspections for
any crack in the area of the elevator side fitting/hinge fitting joint
and for any crack or elongation inside and outside of the holes in the
clevis and in the lug, corrective actions if necessary, and other
specified actions. This AD results from reports of elongated holes and
cracks found in the lugs of the attachment fittings of the elevator
quadrant upper support assembly at the tip of the vertical fin. We are
issuing this AD to detect and correct damage to the aft attachment lugs
of the elevator quadrant support assembly that could lead to failure of
the lugs. This condition could accelerate wear elsewhere in the
elevator control system, which could reduce the crew's ability to
maintain safe flight.
DATES: This AD is effective December 17, 2008.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 17,
2008.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207; telephone 206-544-9990; fax 206-766-5682; e-mail DDCS@boeing.com;
Internet https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
917-6577; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that would apply to
all Boeing Model 727 airplanes. That NPRM was published in the Federal
Register on February 8, 2008 (73 FR 7489). That NPRM proposed to
require repetitive inspections for any crack in the area of the
elevator side fitting/hinge fitting joint and for any crack or
elongation inside and outside of the holes in the clevis and in the
lug, corrective actions if necessary, and other specified actions.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received from the two commenters.
Support for the NPRM
Boeing concurs with the NPRM.
Request To Extend Compliance Time
FedEx requests that we extend the compliance time from 18 months to
30 months for doing the initial inspections of the side and hinge
fittings of the elevator control quadrant upper support assembly. FedEx
states that, prior to issuance of the AD, it will take immediate action
to accomplish the inspections within the required timetable, but that
the 18-month compliance time will likely cause FedEx to do the
inspections outside of scheduled heavy maintenance. FedEx, therefore,
requests an extension of the compliance time, so that it may accomplish
the initial inspections for its entire fleet during its next scheduled
C-check. FedEx states that it prefers to do the inspections at a
maintenance facility during a scheduled heavy maintenance check because
of the difficulty associated in providing safe and adequate access to
the inspection areas, the availability of the requisite tooling, and
the presence of skilled mechanics.
FedEx also requests that we extend the calendar time from 24 months
to 30 months for doing the repetitive inspections. (The NPRM proposed
accomplishing those inspections within 24 months, 4,000 flight hours,
or 3,000 flight cycles, whichever occurs first.) FedEx states that an
increase in calendar time should provide an equivalent level of safety
because it operates its airplanes at a low, daily-utilization rate,
thereby, keeping the flight cycle and flight hour count significantly
below the proposed requirement, even after 30 months of calendar time
has elapsed. FedEx also states that increasing the calendar time for
the repetitive inspections in this way will allow FedEx to accomplish
the inspections within its heavy maintenance schedule.
We disagree with the FedEx's request to extend the compliance times
for the initial inspection and repetitive interval.
[[Page 66744]]
In developing appropriate compliance times for these actions, we
considered the urgency associated with the subject unsafe condition,
the average utilization rate of the affected fleet, and the practical
aspect of accomplishing the required actions within a period of time
that corresponds to the normal scheduled maintenance for most affected
operators. Although FedEx did not submit any technical data to support
its request, its airplane utilization rate might possibly support an
extension in the compliance time. However, FedEx's airplane utilization
rate might not be typical for most operators, and we believe that the
required compliance times specified in the referenced service bulletins
coincides with most operators' utilization rates. If FedEx's airplane
utilization rate and maintenance program for the inspection area prove
that the new compliance time would provide an acceptable level of
safety, FedEx may apply for an AMOC according to the provisions in
paragraph (i) of this AD. We have not changed the AD in this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Costs of Compliance
We estimate that this AD affects 401 airplanes of U.S. registry. We
also estimate that it takes about 2 work-hours per product to comply
with this AD. The average labor rate is $80 per work-hour. Based on
these figures, we estimate the cost of this AD to the U.S. operators to
be $64,160, or $160 per product, 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
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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
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 FAA amends Sec. 39.13 by adding the following new AD:
2008-22-12 Boeing: Amendment 39-15708. Docket No. FAA-2008-0151;
Directorate Identifier 2007-NM-347-AD.
Effective Date
(a) This airworthiness directive (AD) is effective December 17,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F series airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from reports of elongated holes and cracks
found in the lugs of the attachment fittings of the elevator
quadrant upper support assembly at the tip of the vertical fin. We
are issuing this AD to detect and correct damage to the aft
attachment lugs of the elevator quadrant support assembly that could
lead to failure of the lugs. This condition could accelerate wear
elsewhere in the elevator control system, which could reduce the
crew's ability to maintain safe flight.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Repetitive Inspections and Corrective/Other Specified Actions
(f) At the applicable compliance times specified in paragraph
1.E. of Boeing Special Attention Service Bulletin 727-55-0092, dated
June 4, 2007, except as provided by paragraph (g) of this AD: Do the
detailed inspection for any crack in the area of the elevator side
fitting/hinge fitting joint, detailed inspections for elongation
inside and outside of the holes in the clevis and in the lug, and
high frequency eddy current (HFEC) inspections for any crack inside
and outside of the holes in the clevis and in the lug, and do all
the applicable corrective actions and other specified actions, by
accomplishing all of the applicable actions specified in the
Accomplishment Instructions of the service bulletin, except as
provided by paragraph (h) of this AD. Repeat the inspections
thereafter at the applicable intervals specified in paragraph 1.E.
of the service bulletin. Accomplishing the repair or modification
specified in Part 3 of the service bulletin terminates only the
repetitive inspections specified in Part 2 of the service bulletin.
Exceptions to Compliance Times
(g) Where paragraph 1.E. of Boeing Special Attention Service
Bulletin 727-55-0092, dated June 4, 2007, specifies counting the
compliance time from ``. . . the date on this service bulletin,''
this AD requires counting the compliance time from the effective
date of this AD. Where paragraph 1.E. of the service bulletin
specifies a compliance time of ``. . . 18 months . . . '' or ``24
months . . .,'' this AD requires a compliance time of 30 months.
Exception to Corrective Actions
(h) If any damage beyond the repair limits or any crack is found
in the area of the elevator side fitting/hinge fitting joint during
any inspection required by this AD, and Boeing Special Attention
Service Bulletin 727-55-0092, dated June 4, 2007, specifies to
contact Boeing for appropriate action: Before further flight, repair
the crack using a method approved in accordance with the procedures
specified in paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(i)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-
120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 917-6577; fax (425) 917-6590; has the
[[Page 66745]]
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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.
Material Incorporated by Reference
(j) You must use Boeing Special Attention Service Bulletin 727-
55-0092, dated June 4, 2007, 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
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207; telephone 206-544-9990; fax 206-766-5682; e-mail
DDCS@boeing.com; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information
incorporated by reference at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., 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/code_of_federal_
regulations/ibr_locations.html.
Issued in Renton, Washington, on October 9, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-25686 Filed 11-10-08; 8:45 am]
BILLING CODE 4910-13-P
