Airworthiness Directives; Boeing Model 747-400 Series Airplanes, 69587-69589 [E7-23850]
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Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations
Alternative Methods of Compliance
(AMOCs)
(g)(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) 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.
[Docket No. FAA–2007–0302; Directorate
Identifier 2007–NM–161–AD; Amendment
39–15301; AD 2007–25–19]
and applicable corrective actions. This
AD also requires an inspection to
identify the part number, shop code,
and build date of the forward and rear
heat exchanger shells of the air
distribution system of the crew rest area,
and applicable corrective actions, which
end the repetitive inspections. This AD
results from a report of an
uncommanded up and down pitch
movement of an airplane in flight and
resistance in the elevator controls on the
ground during taxi. We are issuing this
AD to prevent cracking and buckling of
the forward or rear heat exchanger shell
of the air distribution system of the crew
rest area, which could result in jamming
of the rudder and/or elevator control
cables and consequent reduced
controllability of the airplane.
DATES: This AD becomes effective
December 26, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of December 26, 2007.
We must receive comments on this
AD by February 8, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
RIN 2120–AA64
Examining the AD Docket
Material Incorporated by Reference
(h) You must use Boeing Special Attention
Service Bulletin 747–53–2498, dated
December 19, 2006, 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 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/federalregister/cfr/ibr-locations.html.
Issued in Renton, Washington, on
November 30, 2007.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–23851 Filed 12–7–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; Boeing
Model 747–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
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AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 747–400 series airplanes.
This AD requires repetitive inspections
to detect discrepancies of the forward
and rear heat exchanger shells of the air
distribution system of the crew rest area,
VerDate Aug<31>2005
16:20 Dec 07, 2007
Jkt 214001
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 street address for
the Docket Office (telephone 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Barbara Mudrovich, Aerospace
Engineer, Cabin Safety and
PO 00000
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69587
Environmental Systems Branch, ANM–
150S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6477; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Background
We previously issued AD 2001–18–
04, amendment 39–12430 (66 FR 46512,
September 6, 2001), applicable to
certain Boeing Model 747–400 series
airplanes. That AD requires repetitive
inspections to detect damage or
deflection of the crew rest heat
exchanger (forward heat exchanger
only), and follow-on actions if
necessary. That AD also requires a onetime inspection to determine the part
number and shop code of the shell of
the crew rest area heat exchanger
(forward heat exchanger only), and
follow-on actions if necessary, which
terminate the repetitive inspections.
Discussion
Since issuance of AD 2001–18–04, we
have received a report of uncommanded
up and down pitch movement of an
airplane in flight and resistance in the
elevator controls on the ground during
taxi on a Boeing Model 747–400 series
airplane. An inspection revealed that
the rear heat exchanger shell of the air
distribution system of the crew rest area
had expanded and deformed inboard
and downwards, contacting the elevator
control cables, which restricted their
movements. Another inspection
revealed that the thickness of certain
forward heat exchanger shells of the air
distribution system of the crew rest area,
including forward heater exchanger
shell subject to the requirements of AD
2001–18–04, was incorrect. The
incorrect shells were manufactured from
two-ply laminate instead of three-ply
laminate.
Cracking and buckling of the forward
or rear heat exchanger shell of the air
distribution system of the crew rest area,
if not corrected, could result in jamming
of the rudder and/or elevator control
cables and consequent reduced
controllability of the airplane.
Relevant Service Information
Boeing has issued Service Bulletin
747–21A2439, Revision 2, dated May
24, 2007. The service bulletin describes
the following procedures:
• Repetitive general visual
inspections of the forward and rear heat
exchanger shells of the air distribution
system of the crew rest area for
discrepancies (i.e., cracks, creases,
deformation, deflection, and
interference with the rudder and/or
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Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations
elevator cables), and applicable
corrective actions (Work Package 1).
• An inspection to identify the part
number, shop code, and build date of
the forward and rear heat exchanger
shells of the air distribution system of
the crew rest area, and applicable
corrective actions (Work Package 2).
Accomplishing these actions eliminates
the need for the repetitive inspections.
The corrective actions include
replacing any discrepant forward or rear
heat exchanger shell of the air
distribution system of the crew rest area
with a certain new heat exchanger shell,
measuring the shell material thickness,
repairing holes, re-marking the part
number of the forward heat exchanger
shell, and making sure the ten common
fasteners are fully installed; as
applicable.
The compliance time specified in the
service bulletin for accomplishing Work
Package 1 is 1,200 flight hours or 90
days, whichever occurs first, and
thereafter at intervals not to exceed
2,500 flight hours. The compliance time
specified in the service bulletin for
accomplishing Work Package 2 is 24
months.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design that may be registered in the U.S.
at some time in the future. Therefore,
we are issuing this AD to prevent
cracking and buckling of the forward or
rear heat exchanger shell of the air
distribution system of the crew rest area,
which could result in jamming of the
rudder and/or elevator control cables
and consequent reduced controllability
of the airplane. This AD requires
accomplishing the actions specified in
the service information described
previously.
Differences Between This AD and
Service Information
For Work Package 1, Table 1 of
paragraph 1.E. of Boeing Service
Bulletin 747–21A2439, Revision 2,
specifies a compliance time of 1,200
flight hours or 90 days for
accomplishing both the general visual
inspections and replacement of the heat
exchanger shells if necessary. We have
determined that, because of the safety
implications and consequences
associated with cracking, any cracked
heat exchanger shell must be replaced
before further flight. Therefore, for Work
Package 1, this AD requires that the
applicable corrective actions for that
work package, which include
replacement of any discrepant forward
or rear heat exchanger shell, be done
before further flight. This difference has
been coordinated with Boeing.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
The following table provides the
estimated costs for U.S. operators to
comply with this AD for any affected
airplane that might be imported and
placed on the U.S. Register in the future.
ESTIMATED COSTS
Average
labor rate
per hour
Action
Work hours
Inspection (Work Package 1) ...................
Inspection (Work Package 2) ...................
Between 1 and 3 1 ..
Between 1 and 3 1 ..
1 Depending
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
Comments Invited
mstockstill on PROD1PC66 with RULES
Between $80 and $240, per inspection cycle.
Between $80 and $240.
on the airplane configuration.
FAA’s Determination of the Effective
Date
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2007–0302; Directorate Identifier 2007–
NM–161–AD’’ at the beginning of your
comments. We specifically invite
VerDate Aug<31>2005
$80
80
Cost per airplane
16:20 Dec 07, 2007
Jkt 214001
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
‘‘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.
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,
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 the regulation:
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Regulatory Findings
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Federal Register / Vol. 72, No. 236 / Monday, December 10, 2007 / Rules and Regulations
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2007–25–19 Boeing: Amendment 39–15301.
Docket No. FAA–2007–0302; Directorate
Identifier 2007–NM–161–AD.
Effective Date
(a) This AD becomes effective December
26, 2007.
Affected ADs
(b) None.
mstockstill on PROD1PC66 with RULES
Applicability
(c) This AD applies to Boeing Model 747–
400 series airplanes, certificated in any
category; as identified in Boeing Service
Bulletin 747–21A2439, Revision 2, dated
May 24, 2007.
Unsafe Condition
(d) This AD results from a report of an
uncommanded up and down pitch
movement of an airplane in flight and
resistance in the elevator controls on the
ground during taxi. We are issuing this AD
to prevent cracking and buckling of the
forward or rear heat exchanger shell of the air
distribution system of the crew rest area,
which could result in jamming of the rudder
and/or elevator control cables and
consequent reduced controllability of the
airplane.
VerDate Aug<31>2005
16:20 Dec 07, 2007
Jkt 214001
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.
Inspections and Corrective Actions
(f) At the applicable times specified in the
Table 1 of paragraph 1.E. of Boeing Service
Bulletin 747–21A2439, Revision 2, dated
May 24, 2007, except as provided by
paragraph (g) of this AD, do the actions
specified in paragraphs (f)(1) and (f)(2) of this
AD by accomplishing all the actions
specified in the Accomplishment
Instructions of the service bulletin.
(1) Do repetitive general visual inspections
to detect discrepancies (i.e., cracks, creases,
deformation, deflection, and interference
with the rudder and/or elevator cables) of the
forward and rear heat exchanger shells of the
air distribution system of the crew rest area,
and do the applicable corrective actions,
until the actions required by paragraph (f)(2)
of this AD are done. The applicable
corrective actions must be done before
further flight.
(2) Do an inspection to identify the part
number, shop code, and build date of the
forward and rear heat exchanger shells of the
air distribution system of the crew rest area,
and before further flight, do the applicable
corrective actions. Accomplishing these
actions ends the repetitive inspections
required by paragraph (f)(1) of this AD.
(g) Where Boeing Service Bulletin 747–
21A2439, Revision 2, dated May 24, 2007,
specifies a compliance time ‘‘after the release
date of the service bulletin’’ or ‘‘after the date
of Revision 02 of the service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
Actions According to Previous Issues of
Service Bulletin or Previously Accomplished
Inspections
(h) Actions done before the effective date
of this AD in accordance with Boeing Alert
Service Bulletin 747–21A2439, dated
November 3, 2005; or Boeing Service Bulletin
74721A2439, Revision 1, dated July 24, 2006;
are acceptable for compliance with the
corresponding actions specified in this AD.
(i) If a forward heat exchanger shell, part
number 65B41601–52, is found installed
during the replacement required by
paragraph (c) of AD 2001–18–04, amendment
39–12430, or was installed during the
inspection required by paragraph (d)(2) of
that AD (AD 2001–18–04 refers to Boeing
Alert Service Bulletin 747–21A2412, dated
January 20, 2000; or Revision 2, dated
November 30, 2000; as the appropriate
sources of service information for
accomplishing the required actions): Actions
required by paragraphs (f)(1) and (f)(2) of this
AD are not required for that forward heat
exchanger shell only.
Parts Installation
(j) As of the effective date of this AD, no
person may install a heat exchanger shell
having a part number identified in the
‘‘Existing Part Number’’ column of the table
specified in paragraph 2.C. of Boeing Service
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69589
Bulletin 747–21A2439, Revision 2, dated
May 24, 2007, on any airplane.
Special Flight Permits
(k) Special flight permits may be issued in
accordance with sections 21.197 and 21.199
of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the airplane to
a location where the requirements of this AD
can be done, except as provided by
paragraphs (k)(1) and (k)(2) of this AD.
(1) If any forward or rear heat exchanger
shell of the air distribution system of the
crew rest area is found deflecting or
interfering with the rudder and/or elevator
control cables (e.g., chafing, rubbing, or
contacting) during any inspection required
by paragraph (f)(1) of this AD, special flight
permits are not allowed.
(2) If any crack or crease is found on the
forward or rear heat exchanger shell of the air
distribution system of the crew rest area
during any inspection required by paragraph
(f)(1) of this AD, the air distribution system
in the crew rest area must be inoperative
during flight.
Alternative Methods of Compliance
(AMOCs)
(l)(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) 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
(m) You must use Boeing Service Bulletin
747–21A2439, Revision 2, dated May 24,
2007, 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 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/federalregister/cfr/ibr-locations.html.
Issued in Renton, Washington, on
November 30, 2007.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–23850 Filed 12–7–07; 8:45 am]
BILLING CODE 4910–13–P
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Agencies
[Federal Register Volume 72, Number 236 (Monday, December 10, 2007)]
[Rules and Regulations]
[Pages 69587-69589]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23850]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0302; Directorate Identifier 2007-NM-161-AD;
Amendment 39-15301; AD 2007-25-19]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 747-400 series airplanes. This AD requires
repetitive inspections to detect discrepancies of the forward and rear
heat exchanger shells of the air distribution system of the crew rest
area, and applicable corrective actions. This AD also requires an
inspection to identify the part number, shop code, and build date of
the forward and rear heat exchanger shells of the air distribution
system of the crew rest area, and applicable corrective actions, which
end the repetitive inspections. This AD results from a report of an
uncommanded up and down pitch movement of an airplane in flight and
resistance in the elevator controls on the ground during taxi. We are
issuing this AD to prevent cracking and buckling of the forward or rear
heat exchanger shell of the air distribution system of the crew rest
area, which could result in jamming of the rudder and/or elevator
control cables and consequent reduced controllability of the airplane.
DATES: This AD becomes effective December 26, 2007.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 26,
2007.
We must receive comments on this AD by February 8, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
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 street address for
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Barbara Mudrovich, Aerospace Engineer,
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 917-6477; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Background
We previously issued AD 2001-18-04, amendment 39-12430 (66 FR
46512, September 6, 2001), applicable to certain Boeing Model 747-400
series airplanes. That AD requires repetitive inspections to detect
damage or deflection of the crew rest heat exchanger (forward heat
exchanger only), and follow-on actions if necessary. That AD also
requires a one-time inspection to determine the part number and shop
code of the shell of the crew rest area heat exchanger (forward heat
exchanger only), and follow-on actions if necessary, which terminate
the repetitive inspections.
Discussion
Since issuance of AD 2001-18-04, we have received a report of
uncommanded up and down pitch movement of an airplane in flight and
resistance in the elevator controls on the ground during taxi on a
Boeing Model 747-400 series airplane. An inspection revealed that the
rear heat exchanger shell of the air distribution system of the crew
rest area had expanded and deformed inboard and downwards, contacting
the elevator control cables, which restricted their movements. Another
inspection revealed that the thickness of certain forward heat
exchanger shells of the air distribution system of the crew rest area,
including forward heater exchanger shell subject to the requirements of
AD 2001-18-04, was incorrect. The incorrect shells were manufactured
from two-ply laminate instead of three-ply laminate.
Cracking and buckling of the forward or rear heat exchanger shell
of the air distribution system of the crew rest area, if not corrected,
could result in jamming of the rudder and/or elevator control cables
and consequent reduced controllability of the airplane.
Relevant Service Information
Boeing has issued Service Bulletin 747-21A2439, Revision 2, dated
May 24, 2007. The service bulletin describes the following procedures:
Repetitive general visual inspections of the forward and
rear heat exchanger shells of the air distribution system of the crew
rest area for discrepancies (i.e., cracks, creases, deformation,
deflection, and interference with the rudder and/or
[[Page 69588]]
elevator cables), and applicable corrective actions (Work Package 1).
An inspection to identify the part number, shop code, and
build date of the forward and rear heat exchanger shells of the air
distribution system of the crew rest area, and applicable corrective
actions (Work Package 2). Accomplishing these actions eliminates the
need for the repetitive inspections.
The corrective actions include replacing any discrepant forward or
rear heat exchanger shell of the air distribution system of the crew
rest area with a certain new heat exchanger shell, measuring the shell
material thickness, repairing holes, re-marking the part number of the
forward heat exchanger shell, and making sure the ten common fasteners
are fully installed; as applicable.
The compliance time specified in the service bulletin for
accomplishing Work Package 1 is 1,200 flight hours or 90 days,
whichever occurs first, and thereafter at intervals not to exceed 2,500
flight hours. The compliance time specified in the service bulletin for
accomplishing Work Package 2 is 24 months.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design that may be
registered in the U.S. at some time in the future. Therefore, we are
issuing this AD to prevent cracking and buckling of the forward or rear
heat exchanger shell of the air distribution system of the crew rest
area, which could result in jamming of the rudder and/or elevator
control cables and consequent reduced controllability of the airplane.
This AD requires accomplishing the actions specified in the service
information described previously.
Differences Between This AD and Service Information
For Work Package 1, Table 1 of paragraph 1.E. of Boeing Service
Bulletin 747-21A2439, Revision 2, specifies a compliance time of 1,200
flight hours or 90 days for accomplishing both the general visual
inspections and replacement of the heat exchanger shells if necessary.
We have determined that, because of the safety implications and
consequences associated with cracking, any cracked heat exchanger shell
must be replaced before further flight. Therefore, for Work Package 1,
this AD requires that the applicable corrective actions for that work
package, which include replacement of any discrepant forward or rear
heat exchanger shell, be done before further flight. This difference
has been coordinated with Boeing.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
The following table provides the estimated costs for U.S. operators
to comply with this AD for any affected airplane that might be imported
and placed on the U.S. Register in the future.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average
Action Work hours labor rate Cost per airplane
per hour
----------------------------------------------------------------------------------------------------------------
Inspection (Work Package 1).............. Between 1 and 3 \1\........ $80 Between $80 and $240, per
inspection cycle.
Inspection (Work Package 2).............. Between 1 and 3 \1\........ 80 Between $80 and $240.
----------------------------------------------------------------------------------------------------------------
\1\ Depending on the airplane configuration.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2007-0302; Directorate Identifier 2007-NM-161-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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 the regulation:
[[Page 69589]]
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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):
2007-25-19 Boeing: Amendment 39-15301. Docket No. FAA-2007-0302;
Directorate Identifier 2007-NM-161-AD.
Effective Date
(a) This AD becomes effective December 26, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747-400 series airplanes,
certificated in any category; as identified in Boeing Service
Bulletin 747-21A2439, Revision 2, dated May 24, 2007.
Unsafe Condition
(d) This AD results from a report of an uncommanded up and down
pitch movement of an airplane in flight and resistance in the
elevator controls on the ground during taxi. We are issuing this AD
to prevent cracking and buckling of the forward or rear heat
exchanger shell of the air distribution system of the crew rest
area, which could result in jamming of the rudder and/or elevator
control cables and consequent reduced controllability 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.
Inspections and Corrective Actions
(f) At the applicable times specified in the Table 1 of
paragraph 1.E. of Boeing Service Bulletin 747-21A2439, Revision 2,
dated May 24, 2007, except as provided by paragraph (g) of this AD,
do the actions specified in paragraphs (f)(1) and (f)(2) of this AD
by accomplishing all the actions specified in the Accomplishment
Instructions of the service bulletin.
(1) Do repetitive general visual inspections to detect
discrepancies (i.e., cracks, creases, deformation, deflection, and
interference with the rudder and/or elevator cables) of the forward
and rear heat exchanger shells of the air distribution system of the
crew rest area, and do the applicable corrective actions, until the
actions required by paragraph (f)(2) of this AD are done. The
applicable corrective actions must be done before further flight.
(2) Do an inspection to identify the part number, shop code, and
build date of the forward and rear heat exchanger shells of the air
distribution system of the crew rest area, and before further
flight, do the applicable corrective actions. Accomplishing these
actions ends the repetitive inspections required by paragraph (f)(1)
of this AD.
(g) Where Boeing Service Bulletin 747-21A2439, Revision 2, dated
May 24, 2007, specifies a compliance time ``after the release date
of the service bulletin'' or ``after the date of Revision 02 of the
service bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
Actions According to Previous Issues of Service Bulletin or Previously
Accomplished Inspections
(h) Actions done before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 747-21A2439, dated
November 3, 2005; or Boeing Service Bulletin 74721A2439, Revision 1,
dated July 24, 2006; are acceptable for compliance with the
corresponding actions specified in this AD.
(i) If a forward heat exchanger shell, part number 65B41601-52,
is found installed during the replacement required by paragraph (c)
of AD 2001-18-04, amendment 39-12430, or was installed during the
inspection required by paragraph (d)(2) of that AD (AD 2001-18-04
refers to Boeing Alert Service Bulletin 747-21A2412, dated January
20, 2000; or Revision 2, dated November 30, 2000; as the appropriate
sources of service information for accomplishing the required
actions): Actions required by paragraphs (f)(1) and (f)(2) of this
AD are not required for that forward heat exchanger shell only.
Parts Installation
(j) As of the effective date of this AD, no person may install a
heat exchanger shell having a part number identified in the
``Existing Part Number'' column of the table specified in paragraph
2.C. of Boeing Service Bulletin 747-21A2439, Revision 2, dated May
24, 2007, on any airplane.
Special Flight Permits
(k) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be done, except as provided by
paragraphs (k)(1) and (k)(2) of this AD.
(1) If any forward or rear heat exchanger shell of the air
distribution system of the crew rest area is found deflecting or
interfering with the rudder and/or elevator control cables (e.g.,
chafing, rubbing, or contacting) during any inspection required by
paragraph (f)(1) of this AD, special flight permits are not allowed.
(2) If any crack or crease is found on the forward or rear heat
exchanger shell of the air distribution system of the crew rest area
during any inspection required by paragraph (f)(1) of this AD, the
air distribution system in the crew rest area must be inoperative
during flight.
Alternative Methods of Compliance (AMOCs)
(l)(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) 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
(m) You must use Boeing Service Bulletin 747-21A2439, Revision
2, dated May 24, 2007, 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 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/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 30, 2007.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7-23850 Filed 12-7-07; 8:45 am]
BILLING CODE 4910-13-P