Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 34814-34817 [06-5425]
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Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
2000, are considered acceptable for
compliance with the initial inspections
required by paragraph (f) of this AD.
(g) Within 4,500 flight cycles or 6,000 flight
hours, whichever comes first, after doing the
initial inspections required by paragraph (f)
of this AD: Do the free-play inspections of the
elevator tab assembly on the left and right
sides of the airplane to find any damage or
discrepancy per Work Package III of Boeing
Service Bulletin 737–55A1070, Revision 1,
dated May 10, 2001. Repeat the inspections
after that at intervals not to exceed 4,500
flight cycles or 6,000 flight hours, whichever
comes first, until paragraph (i) of this AD has
been accomplished.
Corrective Actions
(h) If any damage or discrepancy is found
after doing any inspection required by
paragraph (f) or (g) of this AD, before further
flight, do the applicable corrective action per
the Accomplishment Instructions of Boeing
Service Bulletin 737–55A1070, Revision 1,
dated May 10, 2001.
New Requirements of This AD
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Initial/Repetitive Inspections/Corrective
Actions
(i) Do the applicable inspections of the
elevator tab assembly on the left and right
sides of the airplane to find any damage or
discrepancy by doing all the actions,
including rework and all corrective actions,
as specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–55A1070, Revision 2, dated April 20,
2006, except as provided by paragraphs (j)
and (k) of this AD. Do the applicable actions
at the applicable time specified in Table 1,
Table 2, or Table 3 of paragraph 1.E.,
‘‘Compliance,’’ of the service bulletin; except
that where the service bulletin specifies a
time frame ‘‘after the release date’’ of the
service bulletin, this AD requires compliance
within the specified compliance time after
the effective date of this AD. All corrective
actions must be done before further flight.
Repeat the inspections specified in Table 3
of paragraph 1.E., ‘‘Compliance,’’ of the
service bulletin at the applicable time
specified in the table. Accomplishing the
actions required by paragraph (i) of this AD
ends the requirements of paragraphs (f), (g),
and (h) of this AD.
(j) If any damage or discrepancy is found
during any inspection required by paragraph
(i) of this AD, and the service bulletin
specifies to contact Boeing for appropriate
action: Before further flight, repair using a
method approved in accordance with the
procedures specified in paragraph of (m) of
this AD.
(k) Where Boeing Alert Service Bulletin
737–55A1070, Revision 1, dated May 10,
2001, or Revision 2, dated April 20, 2006,
specifies reporting the inspection results to
the manufacturer, this AD does not require
such reporting.
Actions Done in Accordance With Revision 1
of Service Bulletin
(l) Footnote (a) in Table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–55A1070, Revision 2, specifies
the following: ‘‘For airplanes on which the
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initial actions required by Table 1 are due
within 30 days after the release date of
Service Bulletin 737–55A1070, Revision 2,
the inspections and corrective actions
defined by Service Bulletin 737–55A1070
Rev. 1 may be used.’’ This paragraph of this
AD provides a corresponding 30-day deferral
before Revision 2 must be used to do the
initial actions, except that the 30-day time
frame begins at the effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(m)(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) AMOCs approved previously in
accordance with AD 2002–01–01, are
approved as AMOCs for the corresponding
provisions of paragraphs (f), (g), and (h) of
this AD.
(3) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(4) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane.
Material Incorporated by Reference
(n) You must use Boeing Service Bulletin
737–55A1070, Revision 1, including
appendices A, B, and C, dated May 10, 2001;
or Boeing Alert Service Bulletin 737–
55A1070, Revision 2, dated April 20, 2006;
as applicable; to perform the actions that are
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
Boeing Alert Service Bulletin 737–55A1070,
Revision 2, dated April 20, 2006, in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On February 19, 2002 (67 FR 1603,
January 14, 2002), the Director of the Federal
Register approved the incorporation by
reference of Boeing Service Bulletin 737–
55A1070, Revision 1, including appendices
A, B, and C, dated May 10, 2001.
(3) Contact Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124–
2207, for a copy of this service information.
You may review copies at the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
Room PL–401, Nassif Building, Washington,
DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.
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Issued in Renton, Washington, on June 7,
2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5430 Filed 6–15–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24949; Directorate
Identifier 2006–NM–110–AD; Amendment
39–14626; AD 2006–12–02]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and
A321 airplanes. This AD 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. This AD also
provides for optional terminating action
for compliance with the revisions to the
AFM and the maintenance program.
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
ensure that the flightcrew is aware of
procedures to prevent the presence of a
combustible air-fuel mixture in the fuel
tank boost pump, which, in the event of
electrical arcing in the pump motor,
could result in an explosion and loss of
the airplane.
DATES: This AD becomes effective July
3, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of July 3, 2006.
We must receive comments on this
AD by August 15, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
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Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 227–2141; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
could result in an explosion and loss of
the airplane.
compliance with the revisions to the
AFM and the maintenance program.
Relevant Service Information
Differences Between the EASA
Emergency Airworthiness Directive and
This AD
The EASA emergency airworthiness
directive specifies to revise the AFM
‘‘from the effective date of this AD;’’
however, this AD requires revising the
AFM within 10 days after the effective
date of this AD.
The EASA emergency airworthiness
directive applies to Airbus Model A318,
A319, A320, and A321 airplanes
equipped with Eaton Aerospace Limited
fuel pumps, having part number (P/N)
568–1–27202–005 with serial number
(S/N) 6137 and subsequent. However,
this AD applies to all Model A318,
A319, A320, and A321 airplanes, and
requires that operators perform an
inspection to determine the P/N and S/
N of the fuel tank boost pumps within
10 days after the effective date of this
AD.
In addition, the EASA emergency
airworthiness directive does not specify
a terminating action; however, this AD
specifies that replacing all subject fuel
tank boost pumps with boost pumps not
having the identified P/N and S/N is
acceptable as an optional terminating
action for compliance with the revisions
specified for the AFM and maintenance
program revisions.
Airbus has issued Temporary
Revision (TR) 4.03.00/28, dated May 4,
2006. The TR describes a revision to the
Airbus A318/A319/A320/A321 AFM.
The revision specifies conditions under
which the center tank fuel boost pumps
must be turned off to ensure that the
center tank fuel boost pumps remain
immersed in fuel during flight.
The EASA mandated the TR to ensure
that the center fuel tank boost pumps
are immersed in fuel at all times during
flight. The EASA also mandated ‘‘AFM
and Airworthiness limitations’’ to
ensure that the pumps are turned off
during refueling and that the pumps are
immersed in fuel at all times during
ground fuel transfer and defueling. The
EASA issued emergency airworthiness
directive 2006–0106–E, dated May 2,
2006, to ensure the continued
airworthiness of these airplanes in the
European Union.
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Discussion
FAA’s Determination and Requirements
of This AD
The European Aviation Safety Agency
(EASA) notified us that an unsafe
condition may exist on certain Airbus
Model A318, A319, A320, and A321
airplanes. The EASA advises that an
operator reported the failure of a fuel
tank boost pump in service. Subsequent
investigation revealed that one of two
screws that hold the gas return
connector to the top of the boost pump
housing had become unscrewed. The
screw fell into the boost pump motor
and created a short circuit between the
stator and rotor, which caused a circuit
breaker to trip.
It was determined from further
investigation that the screw came loose
because of an inadequate screw locking
mechanism and because the screw had
not been tightened to the correct torque
value. This failure mode was not
identified during the design review
conducted by the manufacturer in
accordance with Special Federal
Aviation Regulation No. 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 21–83). This
condition, if not corrected, could lead to
a screw becoming detached, which
could compromise the integrity of the
explosion-proof housing of the boost
pump motor and create a potential
ignition source. We are issuing this AD
to ensure that the flightcrew is aware of
procedures to prevent the presence of a
combustible air-fuel mixture in the fuel
tank boost pump, which, in the event of
electrical arcing in the pump motor,
These airplane models are
manufactured in France and are type
certificated for operation in the United
States under the provisions of section
21.29 of the Federal Aviation
Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness
agreement. As described in FAA Order
8100.14A, ‘‘Interim Procedures for
Working with the European Community
on Airworthiness Certification and
Continued Airworthiness,’’ dated
August 12, 2005, the EASA has kept the
FAA informed of the situation described
above. We have examined the EASA’s
findings, evaluated all pertinent
information, and determined that we
need to issue an AD for products of this
type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to
ensure that the flightcrew is aware of
procedures to prevent the presence of a
combustible air-fuel mixture in the fuel
tank boost pump, which, in the event of
electrical arcing in the pump motor,
could result in an explosion and loss of
the airplane. This AD requires
inspecting to determine the part number
and serial number of the fuel tank boost
pumps and, for airplanes with affected
pumps, revising the AFM to require
including the information in the TR,
and revising the AFM and the FAAapproved maintenance program to
mandate the limitations described
earlier. This AD also provides for
optional terminating action for
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34815
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Interim Action
We consider this AD interim action. If
final action is later identified, we may
consider further rulemaking then.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD; therefore, providing notice and
opportunity for public comment before
the AD is issued is impracticable, and
good cause exists to make this AD
effective in less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
relevant written data, views, or
arguments regarding this AD. Send your
comments to an address listed in the
ADDRESSES section. Include ‘‘Docket No.
FAA–2006–24949; Directorate Identifier
2006–NM–110–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD that might suggest a
need to modify it.
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Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of that Web site, anyone
can find and read the comments in any
of our dockets, including the name of
the individual who sent the comment
(or signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System receives them.
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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.
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For the reasons discussed above, I
certify that the regulation:
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
2006–12–02 Airbus: Amendment 39–14626.
Docket No. FAA–2006–24949;
Directorate Identifier 2006–NM–110–AD.
Effective Date
(a) This AD becomes effective July 3, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model
A318, A319, A320, and A321 airplanes,
certificated in any category.
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 ensure that the flightcrew is aware of
procedures to prevent the presence of a
combustible air-fuel mixture in the fuel tank
boost pump, which, in the event of electrical
arcing in the pump motor, 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
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the compliance times specified, unless the
actions have already been done.
Part and Serial Number Inspection
(f) Within 10 days after the effective date
of this AD, 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.
For any airplane not equipped with any
Eaton Aerospace Limited (formerly FR–
HITEMP Limited) fuel pump having P/N
568–1–27202–005 with S/N 6137 and
subsequent: No further action is required by
this AD for that airplane except as described
in paragraph (i) of this AD.
Revisions to the Airplane Flight Manual
(AFM) and the Maintenance Program
(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) of
this AD.
(1) Revise the Limitations section of the
Airbus A318/A319/A320/A321 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 (1550 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.’’
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Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
(2) Revise the Limitations section of the
AFM to incorporate the changes specified in
Airbus Temporary Revision (TR) 4.03.00/28,
dated May 4, 2006. 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.
Optional Terminating Action
Parts Installation
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(k) The European Aviation Safety Agency
(EASA) emergency airworthiness directive
2006–0106–E, dated May 2, 2006, also
addresses the subject of this AD.
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. FAA–2006–24431; Directorate
Identifier 2006–NM–011–AD; Amendment
39–14648; AD 2006–12–22]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A319, A320, and A321 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
(i) As of the effective date of this AD, no
person may install a boost pump, P/N 568–
1–27202–005, having S/N 6137 and
subsequent, on any airplane.
Material Incorporated by Reference
(l) You must use Airbus Temporary
Revision 4.03.00/28, dated May 4, 2006, to
perform the actions that are required by this
AD, unless the AD specifies otherwise. (The
approval date of Airbus Temporary Revision
4.03.00/28 is only indicated on page one of
the document.) 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 Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
16:11 Jun 15, 2006
BILLING CODE 4910–13–P
Federal Aviation Administration
(h) Replacement of all subject fuel boost
pumps on any airplane with boost pumps
having a P/N other than P/N 568–1–27202–
005; or with boost pumps, P/N 568–1–27202–
005, having a S/N other than 6137 and
subsequent; constitutes terminating action for
this AD, and the limitations required by
paragraph (g) of this AD may be removed
from the AFM and the maintenance program
for that airplane.
VerDate Aug<31>2005
Issued in Renton, Washington, on June 7,
2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5425 Filed 6–15–06; 8:45 am]
Jkt 208001
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A319, A320, and A321
airplanes. This AD requires a detailed
inspection for cracks and marks on the
carbon blades of the ram air turbine
(RAT), and replacement of the RAT with
a new or serviceable RAT if necessary.
This AD results from a report of three
chord-wise cracks on the aft side of one
carbon blade of a certain RAT. We are
issuing this AD to detect and correct
cracks and/or marks on the RAT carbon
blades, which could result in reduced
structural integrity of the carbon blade,
and consequent loss of the RAT as a
source of hydraulic and electrical power
in an emergency.
DATES: This AD becomes effective July
21, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of July 21, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2141;
fax (425) 227–1149.
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
34817
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Airbus Model A319,
A320, and A321 airplanes. That NPRM
was published in the Federal Register
on April 13, 2006 (71 FR 19136). That
NPRM proposed to require a detailed
inspection for cracks and marks on the
carbon blades of the ram air turbine
(RAT), and replacement of the RAT with
a new or serviceable RAT if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the one comment received.
The commenter, Airbus, supports the
NPRM.
Conclusion
We have carefully reviewed the
available data, including the comment
received, and determined that air safety
and the public interest require adopting
the AD as proposed.
Costs of Compliance
This AD will affect about 34 airplanes
of U.S. registry. The required inspection
will take about 1 work hour per
airplane, at an average labor rate of $80
per work hour. Based on these figures,
the estimated cost of this AD for U.S.
operators is $2,720, or $80 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
E:\FR\FM\16JNR1.SGM
16JNR1
]]>Agencies
[Federal Register Volume 71, Number 116 (Friday, June 16, 2006)]
[Rules and Regulations]
[Pages 34814-34817]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5425]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24949; Directorate Identifier 2006-NM-110-AD;
Amendment 39-14626; AD 2006-12-02]
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; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and A321 airplanes. This AD 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.
This AD also provides for optional terminating action for compliance
with the revisions to the AFM and the maintenance program. 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 ensure that the
flightcrew is aware of procedures to prevent the presence of a
combustible air-fuel mixture in the fuel tank boost pump, which, in the
event of electrical arcing in the pump motor, could result in an
explosion and loss of the airplane.
DATES: This AD becomes effective July 3, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of July 3, 2006.
We must receive comments on this AD by August 15, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the
[[Page 34815]]
instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency (EASA) notified us that an
unsafe condition may exist on certain Airbus Model A318, A319, A320,
and A321 airplanes. The EASA advises that an operator reported the
failure of a fuel tank boost pump in service. Subsequent investigation
revealed that one of two screws that hold the gas return connector to
the top of the boost pump housing had become unscrewed. The screw fell
into the boost pump motor and created a short circuit between the
stator and rotor, which caused a circuit breaker to trip.
It was determined from further investigation that the screw came
loose because of an inadequate screw locking mechanism and because the
screw had not been tightened to the correct torque value. This failure
mode was not identified during the design review conducted by the
manufacturer in accordance with Special Federal Aviation Regulation No.
88 (``SFAR 88,'' Amendment 21-78, and subsequent Amendments 21-82 and
21-83). This condition, if not corrected, could lead to a screw
becoming detached, which could compromise the integrity of the
explosion-proof housing of the boost pump motor and create a potential
ignition source. We are issuing this AD to ensure that the flightcrew
is aware of procedures to prevent the presence of a combustible air-
fuel mixture in the fuel tank boost pump, which, in the event of
electrical arcing in the pump motor, could result in an explosion and
loss of the airplane.
Relevant Service Information
Airbus has issued Temporary Revision (TR) 4.03.00/28, dated May 4,
2006. The TR describes a revision to the Airbus A318/A319/A320/A321
AFM. The revision specifies conditions under which the center tank fuel
boost pumps must be turned off to ensure that the center tank fuel
boost pumps remain immersed in fuel during flight.
The EASA mandated the TR to ensure that the center fuel tank boost
pumps are immersed in fuel at all times during flight. The EASA also
mandated ``AFM and Airworthiness limitations'' to ensure that the pumps
are turned off during refueling and that the pumps are immersed in fuel
at all times during ground fuel transfer and defueling. The EASA issued
emergency airworthiness directive 2006-0106-E, dated May 2, 2006, to
ensure the continued airworthiness of these airplanes in the European
Union.
FAA's Determination and Requirements of This AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
Therefore, we are issuing this AD to ensure that the flightcrew is
aware of procedures to prevent the presence of a combustible air-fuel
mixture in the fuel tank boost pump, which, in the event of electrical
arcing in the pump motor, could result in an explosion and loss of the
airplane. This AD requires inspecting to determine the part number and
serial number of the fuel tank boost pumps and, for airplanes with
affected pumps, revising the AFM to require including the information
in the TR, and revising the AFM and the FAA-approved maintenance
program to mandate the limitations described earlier. This AD also
provides for optional terminating action for compliance with the
revisions to the AFM and the maintenance program.
Differences Between the EASA Emergency Airworthiness Directive and This
AD
The EASA emergency airworthiness directive specifies to revise the
AFM ``from the effective date of this AD;'' however, this AD requires
revising the AFM within 10 days after the effective date of this AD.
The EASA emergency airworthiness directive applies to Airbus Model
A318, A319, A320, and A321 airplanes equipped with Eaton Aerospace
Limited fuel pumps, having part number (P/N) 568-1-27202-005 with
serial number (S/N) 6137 and subsequent. However, this AD applies to
all Model A318, A319, A320, and A321 airplanes, and requires that
operators perform an inspection to determine the P/N and S/N of the
fuel tank boost pumps within 10 days after the effective date of this
AD.
In addition, the EASA emergency airworthiness directive does not
specify a terminating action; however, this AD specifies that replacing
all subject fuel tank boost pumps with boost pumps not having the
identified P/N and S/N is acceptable as an optional terminating action
for compliance with the revisions specified for the AFM and maintenance
program revisions.
Interim Action
We consider this AD interim action. If final action is later
identified, we may consider further rulemaking then.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
24949; Directorate Identifier 2006-NM-110-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD that might
suggest a need to modify it.
[[Page 34816]]
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of that Web
site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
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:
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):
2006-12-02 Airbus: Amendment 39-14626. Docket No. FAA-2006-24949;
Directorate Identifier 2006-NM-110-AD.
Effective Date
(a) This AD becomes effective July 3, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model A318, A319, A320, and
A321 airplanes, certificated in any category.
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 ensure that the flightcrew is aware of procedures to prevent
the presence of a combustible air-fuel mixture in the fuel tank
boost pump, which, in the event of electrical arcing in the pump
motor, 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.
Part and Serial Number Inspection
(f) Within 10 days after the effective date of this AD, 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. For any airplane not
equipped with any Eaton Aerospace Limited (formerly FR-HITEMP
Limited) fuel pump having P/N 568-1-27202-005 with S/N 6137 and
subsequent: No further action is required by this AD for that
airplane except as described in paragraph (i) of this AD.
Revisions to the Airplane Flight Manual (AFM) and the Maintenance
Program
(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)
of this AD.
(1) Revise the Limitations section of the Airbus A318/A319/A320/
A321 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 (1550 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.''
[[Page 34817]]
(2) Revise the Limitations section of the AFM to incorporate the
changes specified in Airbus Temporary Revision (TR) 4.03.00/28,
dated May 4, 2006. 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.
Optional Terminating Action
(h) Replacement of all subject fuel boost pumps on any airplane
with boost pumps having a P/N other than P/N 568-1-27202-005; or
with boost pumps, P/N 568-1-27202-005, having a S/N other than 6137
and subsequent; constitutes terminating action for this AD, and the
limitations required by paragraph (g) of this AD may be removed from
the AFM and the maintenance program for that airplane.
Parts Installation
(i) As of the effective date of this AD, no person may install a
boost pump, P/N 568-1-27202-005, having S/N 6137 and subsequent, on
any airplane.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Related Information
(k) The European Aviation Safety Agency (EASA) emergency
airworthiness directive 2006-0106-E, dated May 2, 2006, also
addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Airbus Temporary Revision 4.03.00/28, dated May
4, 2006, to perform the actions that are required by this AD, unless
the AD specifies otherwise. (The approval date of Airbus Temporary
Revision 4.03.00/28 is only indicated on page one of the document.)
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 Airbus, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on June 7, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5425 Filed 6-15-06; 8:45 am]
BILLING CODE 4910-13-P
