Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 67379-67383 [E8-25997]
Download as PDF
<![CDATA[
Federal Register / Vol. 73, No. 221 / Friday, November 14, 2008 / Rules and Regulations
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Sanjay Ralhan,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1405; fax (425) 227–1149. 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.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
sroberts on PROD1PC70 with RULES
Related Information
(h) Refer to MCAI Brazilian Airworthiness
Directive 2007–11–04R1, effective December
21, 2007; Embraer Service Bulletin 145–30–
0052, Revision 01, dated January 23, 2008;
and Embraer Service Bulletin 145LEG–30–
0019, Revision 01, dated January 25, 2008;
for related information.
Material Incorporated by Reference
(i) You must use Embraer Service Bulletin
145–30–0052, Revision 01, dated January 23,
2008; or Embraer Service Bulletin 145LEG–
30–0019, Revision 01, dated January 25,
2008; as applicable; 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 Empresa Brasileira de
Aeronautica S.A. (EMBRAER), Technical
Publications Section (PC 060), Av. Brigadeiro
˜
Faria Lima, 2170—Putim—12227–901 Sao
Jose dos Campos—SP—BRASIL; telephone:
+55 12 3927–5852 or +55 12 3309–0732; fax:
+55 12 3927–7546; e-mail:
distrib@embraer.com.br; Internet: https://
www.flyembraer.com.
(3) 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/ibrlocations.html.
VerDate Aug<31>2005
15:52 Nov 13, 2008
Jkt 217001
Issued in Renton, Washington, on October
20, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–25756 Filed 11–13–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27011; Directorate
Identifier 2006–NM–175–AD; Amendment
39–15722; AD 2008–23–01]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Airbus Model
A318, A319, A320, and A321 airplanes.
That AD currently requires inspecting to
determine the part number and serial
number of the fuel tank boost pumps
and, for airplanes with affected pumps,
revising the airplane flight manual
(AFM) and the FAA-approved
maintenance program. The existing AD
also provides for optional terminating
action for compliance with the revisions
to the AFM and the maintenance
program. This new AD requires
modifying or replacing the fuel tank
boost pumps, which would terminate
the AFM limitations and the
maintenance program revisions. This
AD results from a report that a fuel tank
boost pump failed in service, due to a
detached screw of the boost pump
housing that created a short circuit
between the stator and rotor of the boost
pump motor and tripped a circuit
breaker. We are issuing this AD to
prevent electrical arcing in the fuel tank
boost pump motor, which, in the
presence of a combustible air-fuel
mixture in the pump, could result in an
explosion and loss of the airplane.
DATES: This AD becomes effective
December 19, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 19, 2008.
On July 3, 2006 (71 FR 34814, June
16, 2006), the Director of the Federal
Register approved the incorporation by
reference of a certain other publication.
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
67379
For service information
identified in this AD, contact Airbus,
Airworthiness Office—EAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; fax +33 5 61 93 44 51;
e-mail: account.airwortheas@airbus.com; Internet https://
www.airbus.com.
ADDRESSES:
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: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2141; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental
notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an
AD that supersedes AD 2006–12–02,
amendment 39–14626 (71 FR 34814,
June 16, 2006). The existing AD applies
to all Airbus Model A318, A319, A320,
and A321 airplanes. That supplemental
NPRM was published in the Federal
Register on March 13, 2008 (73 FR
13507). That supplemental NPRM
proposed to supersede an existing AD
that currently requires inspecting to
determine the part number and serial
number of the fuel tank boost pumps
and, for airplanes with affected pumps,
revising the airplane flight manual
(AFM) and the FAA-approved
maintenance program. The existing AD
also provides for optional terminating
action for compliance with the revisions
to the AFM and the maintenance
program. That supplemental NPRM
proposed to require modifying or
replacing the fuel tank boost pumps,
which would terminate the AFM
limitations and the maintenance
program revisions. That supplemental
NPRM proposed to exclude certain
modified airplanes from the
applicability, require the AFM/
maintenance program revisions on
E:\FR\FM\14NOR1.SGM
14NOR1
67380
Federal Register / Vol. 73, No. 221 / Friday, November 14, 2008 / Rules and Regulations
additional airplanes, and require
modification or replacement of
additional fuel tank boost pumps.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received on
the supplemental NPRM.
Request To Remove Paragraph (k) of
the Supplemental NPRM
Airbus states a concern that we have
introduced Airbus Modification 36734/
Mandatory Service Bulletin A320–28–
1153, dated May 5, 2006, as terminating
action to the AD. Airbus recognizes that
this modification and associated service
bulletin were terminating action for AD
2006–12–02, however Airbus points out
that any modified pump installed
according to either Airbus Modification
36734 or Airbus Mandatory Service
Bulletin A320–28–1153 is two-way
interchangeable with an affected pump
having a part number ending in –005,
–002, or –001. Airbus points out that
Airbus Modification 37508 and Airbus
Mandatory Service Bulletin A320–28–
1159, dated January 8, 2007, are the
only means to ensure that no affected
pumps are on the airplanes. Further,
Airbus states that operators that do not
use Airbus Mandatory Service Bulletin
A320–28–1159 will not be allowed to
update their AFMs.
From these statements, we infer that
Airbus is requesting that we remove
paragraph (k) of the supplemental
NPRM, which provides credit for
actions done using Airbus Mandatory
Service Bulletin A320–28–1153, and
that we remove reference to Airbus
Modification 36734 from the
applicability statement of the
supplemental NPRM. We do not agree.
This AD requires accomplishment of
Airbus Mandatory Service Bulletin
A320–28–1159, which, as Airbus points
out, allows operators to remove the TR
from the AFM. We have determined that
any affected fuel pump modified in
accordance with the actions specified in
Airbus Mandatory Service Bulletin
A320–28–1153 (Modification 36734)
will be the same as any affected fuel
pump modified in accordance with
Airbus Mandatory Service Bulletin
A320–28–1159. Therefore, paragraph (k)
of this AD merely provides credit to
operators that have previously modified
an affected fuel pump before the
effective date of this AD using Airbus
Mandatory Service Bulletin A320–28–
1153 for that pump only. While we
understand Airbus’ concern that the
modified pumps may be interchanged
with unmodified pumps, we note that
paragraph (j) of this AD allows removal
of the AFM TR only if all pumps have
been replaced or modified. Therefore,
we have made no change to this AD in
this regard.
Request To Refer to Latest Temporary
Revision (TR)
Airbus notes that Airbus TR 4.03.00/
28, Issue 02, dated May 18, 2007, to the
Airbus A318/319/320/321 AFM has
replaced Airbus TR 4.03.00/28, dated
May 4, 2006. From this statement, we
infer that Airbus requests that we revise
this AD to refer to Airbus TR 4.03.00/
28, Issue 02. Because Airbus TR 4.03.00/
28, Issue 02, is already referred to in
paragraph (g)(2) of this AD, we do not
agree that any change to the AD is
necessary in this regard.
Request To Remove Certain Fuel Boost
Pumps
Air Transport Association (ATA), on
behalf of one of its members, Northwest
Airlines (NWA), states that the proposed
actions should not apply to fuel boost
pumps below serial number (S/N) 6137
and that no operating restrictions
should be placed on airplanes with
those pumps. NWA states that there
have been no definitive findings of
missing or loose fasteners on pumps
below S/N 6137. NWA further asserts
that the fuel boost pump vendor, Eaton,
has indicated the cause of the unsecured
nuts was errors made by a robotic tool
used during assembly, which was not
used prior to S/N 6137 and not used on
any older pump part numbers.
From these statements, we infer that
the commenters request that we remove
fuel boost pumps having S/N below S/
N 6137 from the requirements of this
AD. We do not agree. While it is true
that there have not been any confirmed
loose or missing fasteners found on the
–001, –002, or –005 Eaton fuel boost
pump with a serial number below S/N
6137, these pumps are vulnerable to the
same unsafe condition. We, along with
Airbus and the European Aviation
Safety Agency (EASA), have determined
that all of the subject fuel boost pumps
might have had inadequate torque
applied to the screws during assembly,
whether hand-driven (below S/N 6137)
or robotic-driven (above S/N 6137).
Therefore, the operational restriction
must be applied to all airplanes with the
affected Eaton fuel boost pumps
installed until the fuel boost pumps are
modified in accordance with the AD.
We have made no change to the AD in
this regard.
Conclusion
We have carefully reviewed the
available data, including the comments
received on the supplemental NPRM,
and determined that air safety and the
public interest require adopting the AD
as proposed in the supplemental NPRM.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Action
Identification of boost
pumps.
Revisions to AFM
and maintenance
program.
Modifications ............
sroberts on PROD1PC70 with RULES
Average labor
rate per hour
Work hours
Fleet cost
$80
None .........................
$80
670 ...........................
$53,600.
1
80
None .........................
80
Up to 670 .................
Up to $53,600.
3
80
Eaton states that
pumps will qualify
for free repair.
240
Up to 670 .................
Up to $160,800.
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
15:52 Nov 13, 2008
Number of U.S.registered airplanes
1
Authority for This Rulemaking
VerDate Aug<31>2005
Cost per
airplane
Parts
Jkt 217001
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
E:\FR\FM\14NOR1.SGM
14NOR1
Federal Register / Vol. 73, No. 221 / Friday, November 14, 2008 / Rules and Regulations
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
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
removing amendment 39–14626 (71 FR
34814, June 16, 2006) and by adding the
following new AD:
sroberts on PROD1PC70 with RULES
■
2008–23–01 Airbus: Amendment 39–15722.
Docket No. FAA–2007–27011;
Directorate Identifier 2006–NM–175–AD.
VerDate Aug<31>2005
17:21 Nov 13, 2008
Jkt 217001
Effective Date
(a) This AD becomes effective December
19, 2008.
Affected ADs
(b) This AD supersedes AD 2006–12–02.
Applicability
(c) This AD applies to Airbus Model A318,
A319, A320, and A321 airplanes, certificated
in any category, except those airplanes on
which Airbus Modification 36734 or 37508
has been incorporated in production.
Unsafe Condition
(d) This AD results from a report that a fuel
tank boost pump failed in service, due to a
detached screw of the boost pump housing
that created a short circuit between the stator
and rotor of the boost pump motor and
tripped a circuit breaker. We are issuing this
AD to prevent electrical arcing in the fuel
tank boost pump motor, which, in the
presence of a combustible air-fuel mixture in
the pump, could result in an explosion and
loss 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.
Restatement of Certain Requirements of AD
2006–12–02
Part and Serial Number Inspection
(f) Within 10 days after July 3, 2006 (the
effective date of AD 2006–12–02), inspect to
determine the part number (P/N) and serial
number (S/N) of each fuel tank boost pump
installed in the wing and center fuel tanks.
A review of maintenance records may be
performed instead of the required inspection
if the P/N and S/N of the fuel boost pump
can be conclusively determined from that
review. Airbus Mandatory Service Bulletin
A320–28–1152, dated May 5, 2006; or
Revision 01, dated July 17, 2006; is
acceptable for complying with the
requirements of this paragraph.
Revisions to Airplane Flight Manual (AFM)/
Maintenance Program
P/N 568–1–27202–005 With S/Ns 6137 and
Subsequent
(g) For airplanes equipped with one or
more Eaton Aerospace Limited (formerly FR–
HITEMP Limited) fuel boost pumps, having
P/N 568–1–27202–005 with S/N 6137 and
subsequent: Prior to further flight after
accomplishing the inspection required by
paragraph (f) of this AD, do the actions
specified in paragraphs (g)(1) and (g)(2), as
applicable of this AD, until the
modifications/replacements required by
paragraph (j) of this AD have been done.
(1) Revise the Limitations section of the
Airbus A318/319/320/321 AFM (‘‘the AFM’’)
and the FAA-approved maintenance program
by incorporating the following. This may be
accomplished by inserting copies of this AD
into the AFM and the maintenance program.
‘‘Apply the following procedure at each
fuel loading:
Refueling:
PO 00000
Frm 00023
Fmt 4700
Sfmt 4700
67381
Before refueling, all pumps must be turned
off, in order to prevent them from
automatically starting during the
refueling process.
Ground fuel transfer:
For all aircraft, do not start a fuel transfer
from any wing tank, if it contains less
than 700 kg (1,550 lb) of fuel.
For A318, A319, and A320 aircraft with a
center tank, do not start a fuel transfer
from the center tank, if it contains less
than 2,000 kg (4,500 lb) of fuel.
If a tank has less than the required
quantity, it is necessary to add fuel (via
a transfer from another tank or refueling)
to enable a transfer to take place.
Defueling:
For all aircraft, when defueling the wings,
do not start the fuel pumps if the fuel
quantity in the inner tank (wing tank for
A321) is below 700 kg (1,550 lb). If the
fuel on the aircraft is not sufficient to
achieve the required fuel distribution,
then transfer fuel or refuel the aircraft to
obtain the required fuel quantity in the
wing tank.
For A318, A319, and A320 aircraft with a
center tank, when performing a pressure
defuel of the center tank, make sure that
the center tank contains at least 2,000 kg
(4,500 lb) of fuel. If it has less than the
required quantity, then transfer fuel to
the center tank. Defuel the aircraft
normally, and turn OFF the center tank
pumps immediately after the FAULT
light on the corresponding pushbuttonswitch comes on.’’
(2) For all airplanes equipped with a center
tank (Modification 20024) excluding A321
models, revise the Limitations section of the
Airbus A318/319/320/321 AFM (‘‘the AFM’’)
to incorporate the changes specified in
Airbus Temporary Revision (TR) 4.03.00/28,
dated May 4, 2006; or 4.03.00/28, Issue 02,
dated May 18, 2007. This may be
accomplished by inserting a copy of the TR
into the AFM. When general revisions of the
AFM have been issued that incorporate the
revisions specified in the TR, the copy of the
TR may be removed from the AFM, provided
the relevant information in the general
revision is identical to that in TR 4.03.00/28,
dated May 4, 2006; or 4.03.00/28, Issue 02,
dated May 18, 2007.
New Requirements of This AD
Part and Serial Number Inspection
(h) For all airplanes: Within 10 days after
the effective date of this AD, inspect to
determine the type and part number of each
fuel tank boost pump installed in the wing
and center fuel tanks. A review of
maintenance records may be performed
instead of the required inspection if the part
number and serial number of the fuel boost
pump can be conclusively determined from
that review. Airbus Mandatory Service
Bulletin A320–28–1159, dated January 8,
2007, is acceptable for complying with the
requirements of this paragraph.
Revisions to AFM/Maintenance Program:
P/Ns 568–1–27202–001 and –002; and P/N
568–1–27202–005 With S/Ns Below 6137
(i) For airplanes equipped with one or
more Eaton Aerospace Limited (formerly FR–
E:\FR\FM\14NOR1.SGM
14NOR1
67382
Federal Register / Vol. 73, No. 221 / Friday, November 14, 2008 / Rules and Regulations
HITEMP Limited) fuel boost pumps, having
P/N 568–1–27202–001 or 568–1–27202–002;
or P/N 568–1–27202–005 with any serial
number below 6137: Before further flight
after accomplishing the inspection required
by paragraph (h) of this AD, do the actions
specified in paragraphs (g)(1) and (g)(2) of
this AD, as applicable, until the
modifications/replacements required by
paragraph (j) of this AD have been done.
Terminating Action
(j) For airplanes equipped with one or
more Eaton Aerospace Limited (formerly FR–
HITEMP Limited) fuel boost pumps, having
P/N 568–1–27202–001, –002, or –005: Within
5,000 flight hours or 18 months, whichever
occurs first after the effective date of this AD,
modify or replace affected fuel boost pumps
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–28–1159, dated January 8,
2007. Modification or replacement of all
affected fuel tank boost pumps on an airplane
terminates the requirements of this AD, and
the limitations required by paragraph (g) of
this AD may be removed from the Airbus
A318/319/320/321 AFM and the
maintenance program for that airplane.
Note 1: For additional sources of service
information for the fuel pump modification/
replacement, Airbus Mandatory Service
Bulletin A320–28–1159, dated January 8,
2007, refers to EATON Service Bulletin
8410–28–05, dated October 2, 2006.
Credit for Actions Done Using Alternative
Service Information
(k) Modification of a fuel pump before the
effective date of this AD in accordance with
Airbus Mandatory Service Bulletin A320–28–
1153, dated May 5, 2006, is acceptable for
compliance with the corresponding
requirements of paragraph (j) of this AD, for
that pump only.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, ATTN: Tim Dulin, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 227–2141; fax (425)
227–1149; 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.
(3) AMOCs approved previously in
accordance with AD 2006–12–02 are
approved as AMOCs for the corresponding
provisions of this AD.
Related Information
(m) European Aviation Safety Agency
airworthiness directive 2007–0218, dated
August 10, 2007, also addresses the subject
of this AD.
Material Incorporated by Reference
(n) You must use the service information
specified in Table 1 of this AD to perform the
actions that are required by this AD, as
applicable, unless the AD specifies
otherwise.
TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE
Service information
Revision/issue level
Airbus Mandatory Service Bulletin A320–28–1152, including Appendix 01 ..........................
Airbus Mandatory Service Bulletin A320–28–1152, including Appendix 01 ..........................
Airbus Mandatory Service Bulletin A320–28–1159 ................................................................
Airbus Temporary Revision 4.03.00/28 ..................................................................................
Airbus Temporary Revision 4.03.00/28 to the Airbus A318/319/320/321 Airplane Flight
Manual.
Original ...........................
Revision 01 ....................
Original ...........................
Original ...........................
Issue 02 .........................
(1) The Director of the Federal Register
approved the incorporation by reference of
the documents specified in Table 2 of this
Date
May 5, 2006.
July 17, 2006.
January 8, 2007.
May 4, 2006.
May 18, 2007.
AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
TABLE 2—NEW MATERIAL INCORPORATED BY REFERENCE
Revision/issue level
Airbus Mandatory Service Bulletin A320–28–1152, including Appendix 01 ..........................
Airbus Mandatory Service Bulletin A320–28–1152, including Appendix 01 ..........................
Airbus Mandatory Service Bulletin A320–28–1159 ................................................................
Airbus Temporary Revision 4.03.00/28 to the Airbus A318/319/320/321 Airplane Flight
Manual.
sroberts on PROD1PC70 with RULES
Service information
Original ...........................
Revision 01 ....................
Original ...........................
Issue 02 .........................
VerDate Aug<31>2005
15:52 Nov 13, 2008
Jkt 217001
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
E:\FR\FM\14NOR1.SGM
14NOR1
Date
May 5, 2006.
July 17, 2006.
January 8, 2007.
May 18, 2007.
Federal Register / Vol. 73, No. 221 / Friday, November 14, 2008 / Rules and Regulations
(2) On July 3, 2006 (71 FR 34814, June 16,
2006), the Director of the Federal Register
previously approved the incorporation by
reference of Airbus Temporary Revision
4.03.00/28, dated May 4, 2006.
(3) Contact Airbus, Airworthiness Office—
EAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; fax +33 5 61 93 44
51; e-mail: account.airworth-eas@airbus.com;
Internet https://www.airbus.com, 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/
code_of_federal_regulations/ibr_
locations.html.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
issuing this AD to detect and correct
fatigue cracking of the upper frame to
side frame splice of the fuselage, which
could result in reduced structural
integrity of the frame and adjacent lap
joint. This reduced structural integrity
can increase loading in the fuselage
skin, which will accelerate skin crack
growth and result in decompression of
the airplane.
DATES: Effective December 1, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 1, 2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD on August 12, 2008 (73 FR
38905, July 8, 2008).
We must receive comments on this
AD by January 13, 2009.
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; telephone
206–544–9990; fax 206–766–5682;
e-mail DDCS@boeing.com; Internet
https://www.myboeingfleet.com.
The FAA is revising an
existing airworthiness directive (AD)
that applies to certain Boeing Model
737–100, –200, –200C, –300, –400, and
–500 series airplanes. That AD currently
requires various repetitive inspections
for cracking of the upper frame to side
frame splice of the fuselage, and other
specified and corrective actions if
necessary. That AD also provides for an
optional preventive modification, which
terminates the repetitive inspections.
This new AD adds an optional
terminating action that was
inadvertently omitted from that AD.
This AD results from a report that the
upper frame of the fuselage was severed
between stringers S–13L and S–14L at
station 747, and the adjacent frame at
station 767 had a 1.3-inch-long crack at
the same stringer location. We are
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:
Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6447; fax (425) 917–6590.
Issued in Renton, Washington, on October
24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–25997 Filed 11–13–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1147; Directorate
Identifier 2008–NM–128–AD; Amendment
39–15719; AD 2008–13–12 R1]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
AGENCY:
sroberts on PROD1PC70 with RULES
SUMMARY:
VerDate Aug<31>2005
15:52 Nov 13, 2008
Jkt 217001
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
67383
SUPPLEMENTARY INFORMATION:
Discussion
On June 12, 2008, we issued AD
2008–13–12, amendment 39–15575 (73
FR 38905, July 8, 2008), for certain
Boeing Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
That AD requires various repetitive
inspections for cracking of the upper
frame to side frame splice of the
fuselage, and other specified and
corrective actions if necessary. That AD
also provides for an optional preventive
modification, which terminates the
repetitive inspections. That AD resulted
from a report that the upper frame of the
fuselage was severed between stringers
S–13L and S–14L at station 747, and the
adjacent frame at station 767 had a 1.3inch-long crack at the same stringer
location. We issued that AD to detect
and correct fatigue cracking of the upper
frame to side frame splice of the
fuselage, which could result in reduced
structural integrity of the frame and
adjacent lap joint. This reduced
structural integrity can increase loading
in the fuselage skin, which will
accelerate skin crack growth and result
in decompression of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2008–13–12, we
have determined that we inadvertently
omitted paragraph (j)(3) from that AD.
Paragraph (j)(3) provided operators with
a third option for doing an optional
terminating action, which terminates
the repetitive inspections required by
paragraph (f) of the existing AD.
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. For this reason, we are issuing
this AD to revise AD 2008–13–12. This
new AD retains the requirements of the
existing AD. This AD also adds an
optional terminating action
inadvertently omitted from the existing
AD.
Costs of Compliance
There are about 1,509 airplanes of the
affected design in the worldwide fleet.
This AD continues to affect about 524
airplanes of U.S. registry. The
inspections currently required by AD
2008–13–12 and retained in this AD
take between 18 and 38 work hours per
airplane, depending on airplane
configuration. The average labor rate is
$80 per work hour. Based on these
figures, the estimated cost of the
currently required inspections required
by this AD for U.S. operators is between
E:\FR\FM\14NOR1.SGM
14NOR1
]]>Agencies
[Federal Register Volume 73, Number 221 (Friday, November 14, 2008)]
[Rules and Regulations]
[Pages 67379-67383]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-25997]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27011; Directorate Identifier 2006-NM-175-AD;
Amendment 39-15722; AD 2008-23-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320, and A321
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Airbus Model A318, A319, A320, and A321
airplanes. That AD currently requires inspecting to determine the part
number and serial number of the fuel tank boost pumps and, for
airplanes with affected pumps, revising the airplane flight manual
(AFM) and the FAA-approved maintenance program. The existing AD also
provides for optional terminating action for compliance with the
revisions to the AFM and the maintenance program. This new AD requires
modifying or replacing the fuel tank boost pumps, which would terminate
the AFM limitations and the maintenance program revisions. This AD
results from a report that a fuel tank boost pump failed in service,
due to a detached screw of the boost pump housing that created a short
circuit between the stator and rotor of the boost pump motor and
tripped a circuit breaker. We are issuing this AD to prevent electrical
arcing in the fuel tank boost pump motor, which, in the presence of a
combustible air-fuel mixture in the pump, could result in an explosion
and loss of the airplane.
DATES: This AD becomes effective December 19, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 19,
2008.
On July 3, 2006 (71 FR 34814, June 16, 2006), the Director of the
Federal Register approved the incorporation by reference of a certain
other publication.
ADDRESSES: For service information identified in this AD, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; fax +33 5 61 93 44 51; e-mail: account.airworth-
eas@airbus.com; Internet https://www.airbus.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: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a supplemental notice of proposed rulemaking (NPRM)
to amend 14 CFR part 39 to include an AD that supersedes AD 2006-12-02,
amendment 39-14626 (71 FR 34814, June 16, 2006). The existing AD
applies to all Airbus Model A318, A319, A320, and A321 airplanes. That
supplemental NPRM was published in the Federal Register on March 13,
2008 (73 FR 13507). That supplemental NPRM proposed to supersede an
existing AD that currently requires inspecting to determine the part
number and serial number of the fuel tank boost pumps and, for
airplanes with affected pumps, revising the airplane flight manual
(AFM) and the FAA-approved maintenance program. The existing AD also
provides for optional terminating action for compliance with the
revisions to the AFM and the maintenance program. That supplemental
NPRM proposed to require modifying or replacing the fuel tank boost
pumps, which would terminate the AFM limitations and the maintenance
program revisions. That supplemental NPRM proposed to exclude certain
modified airplanes from the applicability, require the AFM/maintenance
program revisions on
[[Page 67380]]
additional airplanes, and require modification or replacement of
additional fuel tank boost pumps.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received on the
supplemental NPRM.
Request To Remove Paragraph (k) of the Supplemental NPRM
Airbus states a concern that we have introduced Airbus Modification
36734/Mandatory Service Bulletin A320-28-1153, dated May 5, 2006, as
terminating action to the AD. Airbus recognizes that this modification
and associated service bulletin were terminating action for AD 2006-12-
02, however Airbus points out that any modified pump installed
according to either Airbus Modification 36734 or Airbus Mandatory
Service Bulletin A320-28-1153 is two-way interchangeable with an
affected pump having a part number ending in -005, -002, or -001.
Airbus points out that Airbus Modification 37508 and Airbus Mandatory
Service Bulletin A320-28-1159, dated January 8, 2007, are the only
means to ensure that no affected pumps are on the airplanes. Further,
Airbus states that operators that do not use Airbus Mandatory Service
Bulletin A320-28-1159 will not be allowed to update their AFMs.
From these statements, we infer that Airbus is requesting that we
remove paragraph (k) of the supplemental NPRM, which provides credit
for actions done using Airbus Mandatory Service Bulletin A320-28-1153,
and that we remove reference to Airbus Modification 36734 from the
applicability statement of the supplemental NPRM. We do not agree. This
AD requires accomplishment of Airbus Mandatory Service Bulletin A320-
28-1159, which, as Airbus points out, allows operators to remove the TR
from the AFM. We have determined that any affected fuel pump modified
in accordance with the actions specified in Airbus Mandatory Service
Bulletin A320-28-1153 (Modification 36734) will be the same as any
affected fuel pump modified in accordance with Airbus Mandatory Service
Bulletin A320-28-1159. Therefore, paragraph (k) of this AD merely
provides credit to operators that have previously modified an affected
fuel pump before the effective date of this AD using Airbus Mandatory
Service Bulletin A320-28-1153 for that pump only. While we understand
Airbus' concern that the modified pumps may be interchanged with
unmodified pumps, we note that paragraph (j) of this AD allows removal
of the AFM TR only if all pumps have been replaced or modified.
Therefore, we have made no change to this AD in this regard.
Request To Refer to Latest Temporary Revision (TR)
Airbus notes that Airbus TR 4.03.00/28, Issue 02, dated May 18,
2007, to the Airbus A318/319/320/321 AFM has replaced Airbus TR
4.03.00/28, dated May 4, 2006. From this statement, we infer that
Airbus requests that we revise this AD to refer to Airbus TR 4.03.00/
28, Issue 02. Because Airbus TR 4.03.00/28, Issue 02, is already
referred to in paragraph (g)(2) of this AD, we do not agree that any
change to the AD is necessary in this regard.
Request To Remove Certain Fuel Boost Pumps
Air Transport Association (ATA), on behalf of one of its members,
Northwest Airlines (NWA), states that the proposed actions should not
apply to fuel boost pumps below serial number (S/N) 6137 and that no
operating restrictions should be placed on airplanes with those pumps.
NWA states that there have been no definitive findings of missing or
loose fasteners on pumps below S/N 6137. NWA further asserts that the
fuel boost pump vendor, Eaton, has indicated the cause of the unsecured
nuts was errors made by a robotic tool used during assembly, which was
not used prior to S/N 6137 and not used on any older pump part numbers.
From these statements, we infer that the commenters request that we
remove fuel boost pumps having S/N below S/N 6137 from the requirements
of this AD. We do not agree. While it is true that there have not been
any confirmed loose or missing fasteners found on the -001, -002, or -
005 Eaton fuel boost pump with a serial number below S/N 6137, these
pumps are vulnerable to the same unsafe condition. We, along with
Airbus and the European Aviation Safety Agency (EASA), have determined
that all of the subject fuel boost pumps might have had inadequate
torque applied to the screws during assembly, whether hand-driven
(below S/N 6137) or robotic-driven (above S/N 6137). Therefore, the
operational restriction must be applied to all airplanes with the
affected Eaton fuel boost pumps installed until the fuel boost pumps
are modified in accordance with the AD. We have made no change to the
AD in this regard.
Conclusion
We have carefully reviewed the available data, including the
comments received on the supplemental NPRM, and determined that air
safety and the public interest require adopting the AD as proposed in
the supplemental NPRM.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Average labor Cost per Number of U.S.-
Action Work hours rate per hour Parts airplane registered airplanes Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Identification of boost pumps...... 1 $80 None................. $80 670.................. $53,600.
Revisions to AFM and maintenance 1 80 None................. 80 Up to 670............ Up to $53,600.
program.
Modifications...................... 3 80 Eaton states that 240 Up to 670............ Up to $160,800.
pumps will qualify
for free repair.
--------------------------------------------------------------------------------------------------------------------------------------------------------
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,
[[Page 67381]]
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 FAA amends Sec. 39.13 by removing amendment 39-14626 (71 FR
34814, June 16, 2006) and by adding the following new AD:
2008-23-01 Airbus: Amendment 39-15722. Docket No. FAA-2007-27011;
Directorate Identifier 2006-NM-175-AD.
Effective Date
(a) This AD becomes effective December 19, 2008.
Affected ADs
(b) This AD supersedes AD 2006-12-02.
Applicability
(c) This AD applies to Airbus Model A318, A319, A320, and A321
airplanes, certificated in any category, except those airplanes on
which Airbus Modification 36734 or 37508 has been incorporated in
production.
Unsafe Condition
(d) This AD results from a report that a fuel tank boost pump
failed in service, due to a detached screw of the boost pump housing
that created a short circuit between the stator and rotor of the
boost pump motor and tripped a circuit breaker. We are issuing this
AD to prevent electrical arcing in the fuel tank boost pump motor,
which, in the presence of a combustible air-fuel mixture in the
pump, could result in an explosion and loss 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.
Restatement of Certain Requirements of AD 2006-12-02
Part and Serial Number Inspection
(f) Within 10 days after July 3, 2006 (the effective date of AD
2006-12-02), inspect to determine the part number (P/N) and serial
number (S/N) of each fuel tank boost pump installed in the wing and
center fuel tanks. A review of maintenance records may be performed
instead of the required inspection if the P/N and S/N of the fuel
boost pump can be conclusively determined from that review. Airbus
Mandatory Service Bulletin A320-28-1152, dated May 5, 2006; or
Revision 01, dated July 17, 2006; is acceptable for complying with
the requirements of this paragraph.
Revisions to Airplane Flight Manual (AFM)/Maintenance Program
P/N 568-1-27202-005 With S/Ns 6137 and Subsequent
(g) For airplanes equipped with one or more Eaton Aerospace
Limited (formerly FR-HITEMP Limited) fuel boost pumps, having P/N
568-1-27202-005 with S/N 6137 and subsequent: Prior to further
flight after accomplishing the inspection required by paragraph (f)
of this AD, do the actions specified in paragraphs (g)(1) and
(g)(2), as applicable of this AD, until the modifications/
replacements required by paragraph (j) of this AD have been done.
(1) Revise the Limitations section of the Airbus A318/319/320/
321 AFM (``the AFM'') and the FAA-approved maintenance program by
incorporating the following. This may be accomplished by inserting
copies of this AD into the AFM and the maintenance program.
``Apply the following procedure at each fuel loading:
Refueling:
Before refueling, all pumps must be turned off, in order to
prevent them from automatically starting during the refueling
process.
Ground fuel transfer:
For all aircraft, do not start a fuel transfer from any wing
tank, if it contains less than 700 kg (1,550 lb) of fuel.
For A318, A319, and A320 aircraft with a center tank, do not
start a fuel transfer from the center tank, if it contains less than
2,000 kg (4,500 lb) of fuel.
If a tank has less than the required quantity, it is necessary
to add fuel (via a transfer from another tank or refueling) to
enable a transfer to take place.
Defueling:
For all aircraft, when defueling the wings, do not start the
fuel pumps if the fuel quantity in the inner tank (wing tank for
A321) is below 700 kg (1,550 lb). If the fuel on the aircraft is not
sufficient to achieve the required fuel distribution, then transfer
fuel or refuel the aircraft to obtain the required fuel quantity in
the wing tank.
For A318, A319, and A320 aircraft with a center tank, when
performing a pressure defuel of the center tank, make sure that the
center tank contains at least 2,000 kg (4,500 lb) of fuel. If it has
less than the required quantity, then transfer fuel to the center
tank. Defuel the aircraft normally, and turn OFF the center tank
pumps immediately after the FAULT light on the corresponding
pushbutton-switch comes on.''
(2) For all airplanes equipped with a center tank (Modification
20024) excluding A321 models, revise the Limitations section of the
Airbus A318/319/320/321 AFM (``the AFM'') to incorporate the changes
specified in Airbus Temporary Revision (TR) 4.03.00/28, dated May 4,
2006; or 4.03.00/28, Issue 02, dated May 18, 2007. This may be
accomplished by inserting a copy of the TR into the AFM. When
general revisions of the AFM have been issued that incorporate the
revisions specified in the TR, the copy of the TR may be removed
from the AFM, provided the relevant information in the general
revision is identical to that in TR 4.03.00/28, dated May 4, 2006;
or 4.03.00/28, Issue 02, dated May 18, 2007.
New Requirements of This AD
Part and Serial Number Inspection
(h) For all airplanes: Within 10 days after the effective date
of this AD, inspect to determine the type and part number of each
fuel tank boost pump installed in the wing and center fuel tanks. A
review of maintenance records may be performed instead of the
required inspection if the part number and serial number of the fuel
boost pump can be conclusively determined from that review. Airbus
Mandatory Service Bulletin A320-28-1159, dated January 8, 2007, is
acceptable for complying with the requirements of this paragraph.
Revisions to AFM/Maintenance Program: P/Ns 568-1-27202-001 and -002;
and P/N 568-1-27202-005 With S/Ns Below 6137
(i) For airplanes equipped with one or more Eaton Aerospace
Limited (formerly FR-
[[Page 67382]]
HITEMP Limited) fuel boost pumps, having P/N 568-1-27202-001 or 568-
1-27202-002; or P/N 568-1-27202-005 with any serial number below
6137: Before further flight after accomplishing the inspection
required by paragraph (h) of this AD, do the actions specified in
paragraphs (g)(1) and (g)(2) of this AD, as applicable, until the
modifications/replacements required by paragraph (j) of this AD have
been done.
Terminating Action
(j) For airplanes equipped with one or more Eaton Aerospace
Limited (formerly FR-HITEMP Limited) fuel boost pumps, having P/N
568-1-27202-001, -002, or -005: Within 5,000 flight hours or 18
months, whichever occurs first after the effective date of this AD,
modify or replace affected fuel boost pumps in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-28-1159, dated January 8, 2007. Modification or replacement of
all affected fuel tank boost pumps on an airplane terminates the
requirements of this AD, and the limitations required by paragraph
(g) of this AD may be removed from the Airbus A318/319/320/321 AFM
and the maintenance program for that airplane.
Note 1: For additional sources of service information for the
fuel pump modification/replacement, Airbus Mandatory Service
Bulletin A320-28-1159, dated January 8, 2007, refers to EATON
Service Bulletin 8410-28-05, dated October 2, 2006.
Credit for Actions Done Using Alternative Service Information
(k) Modification of a fuel pump before the effective date of
this AD in accordance with Airbus Mandatory Service Bulletin A320-
28-1153, dated May 5, 2006, is acceptable for compliance with the
corresponding requirements of paragraph (j) of this AD, for that
pump only.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, ATTN: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-2141; fax (425) 227-1149; 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.
(3) AMOCs approved previously in accordance with AD 2006-12-02
are approved as AMOCs for the corresponding provisions of this AD.
Related Information
(m) European Aviation Safety Agency airworthiness directive
2007-0218, dated August 10, 2007, also addresses the subject of this
AD.
Material Incorporated by Reference
(n) You must use the service information specified in Table 1 of
this AD to perform the actions that are required by this AD, as
applicable, unless the AD specifies otherwise.
Table 1--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service information Revision/issue level Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin Original............................. May 5, 2006.
A320-28-1152, including Appendix
01.
Airbus Mandatory Service Bulletin Revision 01.......................... July 17, 2006.
A320-28-1152, including Appendix
01.
Airbus Mandatory Service Bulletin Original............................. January 8, 2007.
A320-28-1159.
Airbus Temporary Revision 4.03.00/ Original............................. May 4, 2006.
28.
Airbus Temporary Revision 4.03.00/ Issue 02............................. May 18, 2007.
28 to the Airbus A318/319/320/321
Airplane Flight Manual.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the documents specified in Table 2 of
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Table 2--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service information Revision/issue level Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin Original............................. May 5, 2006.
A320-28-1152, including Appendix
01.
Airbus Mandatory Service Bulletin Revision 01.......................... July 17, 2006.
A320-28-1152, including Appendix
01.
Airbus Mandatory Service Bulletin Original............................. January 8, 2007.
A320-28-1159.
Airbus Temporary Revision 4.03.00/ Issue 02............................. May 18, 2007.
28 to the Airbus A318/319/320/321
Airplane Flight Manual.
----------------------------------------------------------------------------------------------------------------
[[Page 67383]]
(2) On July 3, 2006 (71 FR 34814, June 16, 2006), the Director
of the Federal Register previously approved the incorporation by
reference of Airbus Temporary Revision 4.03.00/28, dated May 4,
2006.
(3) Contact Airbus, Airworthiness Office--EAS, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 44
51; e-mail: account.airworth-eas@airbus.com; Internet https://
www.airbus.com, 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/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on October 24, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-25997 Filed 11-13-08; 8:45 am]
BILLING CODE 4910-13-P
