[Federal Register: June 29, 2005 (Volume 70, Number 124)]
[Proposed Rules]
[Page 37296-37302]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29jn05-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21702; Directorate Identifier 2005-NM-024-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 and A340 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Airbus Model A330 and A340 series airplanes. This proposed
AD would require repetitive borescope inspections of the left and right
fuel tanks of the trimmable horizontal stabilizers (trim tanks) for
detached or damaged float valves; related investigative/corrective
actions if necessary; and the eventual replacement of all float valves
in the left and right trim tanks with new, improved float valves, which
terminates the need for the repetitive inspections. This proposed AD
would also require repetitive replacement of certain new, improved
float valves. This proposed AD is prompted by reports of detached and
damaged float valves in the trim tanks. We are proposing this AD to
prevent, in the event of a lightning strike to the horizontal
stabilizer, sparking of metal parts and debris from detached and
damaged float valves, or a buildup of static electricity, which could
result in ignition of fuel vapors and consequent fire or explosion.
DATES: We must receive comments on this proposed AD by July 29, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://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.
By 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.
For service information identified in this proposed AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-21702; the directorate identifier for this docket is
2005-NM-024-AD.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-21702;
Directorate Identifier 2005-NM-024-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://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 proposed AD. Using the search function of our
docket 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 can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at http://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 DMS receives them.
Discussion
We have examined the underlying safety issues involved in recent
fuel tank explosions on several large transport airplanes, including
the adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(67 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design approval
[[Page 37297]]
(i.e., type certificate (TC) and supplemental type certificate (STC))
holders to substantiate that their fuel tank systems can prevent
ignition sources in the fuel tanks. This requirement applies to type
design approval holders for large turbine-powered transport airplanes
and for subsequent modifications to those airplanes. It requires them
to perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
combination with another latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
The Joint Aviation Authorities (JAA) has issued a regulation that
is similar to SFAR 88. (The JAA is an associated body of the European
Civil Aviation Conference (ECAC) representing the civil aviation
regulatory authorities of a number of European States who have agreed
to co-operate in developing and implementing common safety regulatory
standards and procedures.) Under this regulation, the JAA stated that
all members of the ECAC that hold type certificates for transport
category airplanes are required to conduct a design review against
explosion risks.
We have determined that the actions identified in this proposed AD
are necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss of the airplane.
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified us that an
unsafe condition may exist on certain Airbus Model A330 and A340 series
airplanes. The DGAC advises that it has received reports of detached
and damaged float valves in the left and right fuel tanks of the
trimmable horizontal stabilizers (trim tanks). The left tank float
valves, part number (P/N) L87-13-001, are manufactured by
Intertechnique. The right tank float valves, P/N 61600, are
manufactured by Argo-Tech. The float valves are part of the fuel vent
system. The DGAC states that the affected float valves detached as a
result of environmental fatigue that exceeded the valves' qualification
standards. Certain float valves have metal parts which, when detached
and positioned in certain locations/orientations in the trim tank, may
create ignition sources in the trim tanks. If there is a lightning
strike to the horizontal stabilizer, the metal parts and debris from
detached and damaged float valves may cause sparking, or a buildup of
static electricity, which could result in ignition of fuel vapors and
consequent fire or explosion.
The DGAC also advises that a life limit of 24,500 flight cycles
must be imposed on Intertechnique vent float valves, P/N L87-13-002, if
installed in the left trim tank on Model A330 series airplanes.
Relevant Service Information
Airbus has issued the following service bulletins:
Relevant Service Information
------------------------------------------------------------------------
Airbus model Airbus service bulletin
------------------------------------------------------------------------
A330 series airplanes.................. A330-28-3086, dated July 24,
2003.
A330-28-3087, Revision 01,
dated August 16, 2004.
A330-28-3088, dated April 27,
2004.
A330-28-3089, Revision 02,
dated April 1, 2005.
A330-28-3094, dated April 7,
2005.
A340-200 and -300 series airplanes..... A340-28-4100, Revision 01,
dated August 16, 2004.
A340-28-4101, Revision 01,
dated August 16, 2004.
A340-28-4102, dated April 27,
2004.
A340-28-4103, Revision 02,
dated April 1, 2005.
A340-28-4111, dated April 6,
2005.
A340-541 and -642 airplanes............ A340-28-5007, May 7, 2004.
A340-28-5010, May 7, 2004.
A340-28-5021, dated April 6,
2005.
------------------------------------------------------------------------
Service Bulletins A330-28-3086 and A340-28-4100, Revision 01,
include procedures for performing repetitive borescope inspections of
the right trim tank for detached or damaged float valves, and related
investigative/corrective actions if necessary. Service Bulletins A330-
28-3087 and A340-28-4101, both Revision 01, include procedures for
doing those same actions for the left trim tank. If a float valve is
detached, or the arms are damaged, the related investigative/corrective
actions include:
Doing a detailed visual inspection for damage to the trim
tank structure;
Repairing structural damage in accordance with the
applicable Airbus Structural Repair Manual (SRM) and contacting Airbus
if the damage exceeds the limits specified in the SRM;
Removing a detached float valve and associated debris from
the trim tank;
Replacing the float valve; and
Reporting all findings to Airbus.
These service bulletins also provide the option of deactivating an
affected trim tank until the float valve can be replaced in accordance
with the operator's maintenance schedule. In addition, for airplanes on
which some floats are intact, Service Bulletin A340-28-4100, Revision
01, provides the option of contacting Airbus for the possible issuance
of an Airbus No Technical Objection (NTO) letter to allow continued
operation, for a specified number of flight cycles, without
deactivating the trim tank.
Service Bulletins A330-28-3088, A340-28-4102, and A340-28-5007
include procedures for installing a new, improved float valve, P/N
62015-1, manufactured by Argo-Tech, in the right trim tank. The
installation procedures include:
[[Page 37298]]
Removing the existing float valve and bonding leads;
Removing a detached float valve and associated debris from
the trim tank, if necessary;
Repairing structural damage in accordance with the
applicable Airbus Structural Repair Manual (SRM) and contacting Airbus
if the damage exceeds the limits specified in the SRM;
Preparing the airplane structure to accommodate the new
electrical bonding;
Installing P/N 62015-1; and
Performing a bonding test of the float valve.
Service Bulletin A330-28-3088 also specifies a life limit of 20,000
flight cycles since first installation for the new Argo-Tech float
valve, P/N 62015-1. Service Bulletins A330-28-3088 and A340-28-4102
state that any removed float valve having a certain part number should
be sent to Argo-Tech. In addition, Service Bulletin A330-28-3088
identifies Airbus Service Bulletin A330-55-3022, dated November 4,
1997, as a concurrent service bulletin; and Service Bulletin A340-28-
4102 identifies Airbus Service Bulletin A340-55-4023, dated November 4,
1997, as a concurrent service bulletin. The concurrent service
bulletins include procedures for installing Teflon gore joints in the
front spar panels.
Service Bulletin A330-28-3088 states that accomplishing the actions
specified in that service bulletin cancels the inspections specified in
Service Bulletin A330-28-3086. Service Bulletin A340-28-4102 states
that accomplishing the actions specified in that service bulletin
cancels the inspections specified in Service Bulletin A340-28-4100.
Procedures for installing a new, improved float valve, P/N L87-13-
002, manufactured by Intertechnique, in the left trim tank, are
included in the following service bulletins: A330-28-3089, Revision 02;
A340-28-4103, Revision 02; and A340-28-5010. The installation
procedures include:
Removing the existing float valve;
Removing a detached float valve and associated debris from
the trim tank, if necessary;
Repairing structural damage in accordance with the
applicable Airbus Structural Repair Manual (SRM) and contacting Airbus
for damage that exceeds the limits specified in the SRM;
Installing P/N L87-13-002; and
Performing a bonding test of the float valve.
Service Bulletin A330-28-3089, Revision 02, also specifies a life
limit of 24,500 flight cycles since first installation for the new
Intertechnique float valve, P/N L87-13-002. Service Bulletins A330-28-
3089, Revision 02; A340-28-4103, Revision 02; and A340-28-5010 also
state that removed float valves having a certain part number should be
sent to Intertechnique. In addition, Service Bulletin A330-28-3089
identifies Airbus Service Bulletin A330-55-3022 as a concurrent service
bulletin; and Service Bulletin A340-28-4103 identifies Airbus Service
Bulletin A340-55-4023 as a concurrent service bulletin.
Service Bulletin A330-28-3089, Revision 02, states that
accomplishing the actions in that service bulletin cancels the
inspections specified in Service Bulletin A330-28-3087. Service
Bulletin A340-28-4103, Revision 02, states that accomplishing the
actions in that service bulletin cancels the inspections specified in
Service Bulletin A340-28-4101.
Procedures for installing a new, improved float valve, P/N L87-13-
003, manufactured by Intertechnique, in the left trim tank, are
included in the following service bulletins: A330-28-3094, A340-28-
4111, and A340-28-5021. The installation procedures include:
Removing the existing float valve;
Removing a detached float valve and associated debris from
the trim tank, if necessary;
Repairing structural damage in accordance with the
applicable Airbus Structural Repair Manual (SRM) and contacting Airbus
for damage that exceeds the limits specified in the SRM;
Installing P/N L87-13-003; and
Performing a bonding test of the float valve.
Service Bulletin A330-28-3094 states that, if P/N L87-13-002 has
not been installed, accomplishing the actions specified in that service
bulletin eliminates the need for accomplishing the actions specified in
Service Bulletin A330-28-3089. Service Bulletin A340-28-4111 states
that, if P/N L87-13-002 has not been installed, accomplishing the
actions specified in that service bulletin eliminates the need for
accomplishing the actions specified in Service Bulletin A340-28-4103.
Service Bulletin A340-28-5021 states that, if P/N L87-13-002 has not
been installed, accomplishing the actions specified in that service
bulletin eliminates the need for accomplishing the actions specified in
Service Bulletin A340-28-5010.
The DGAC mandated the service information and issued French
airworthiness directives F-2005-003, dated January 5, 2005, and F-2005-
004 R1 and F-2005-005 R1, both dated April 27, 2005, to ensure the
continued airworthiness of these airplanes in France.
FAA's Determination and Requirements of the Proposed 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. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC'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 proposing this AD, which would require repetitive
borescope inspections of the left and right fuel tanks of the trimmable
horizontal stabilizers (trim tanks) for detached or damaged float
valves; related investigative/corrective actions if necessary; and the
eventual replacement of all float valves in the left and right trim
tanks with new, improved float valves, which terminates the need for
the repetitive inspections. This proposed AD would also require
repetitive replacement of certain new, improved float valves.
Differences Among the Proposed AD, French Airworthiness Directives, and
Service Information
All of the service bulletins specify that if the structural damage
caused by a detached float exceeds the limits in the applicable Airbus
SRM, you may contact the manufacturer for instructions on how to repair
the damage. This proposed AD would require you to contact us, or the
DGAC (or its delegated agent), for instructions on how to repair damage
that exceeds the limits in the SRM. Also, this proposed AD provides the
option of either repairing any structural damage in accordance with the
applicable service bulletin, or in accordance with a method approved by
us, or the DGAC (or its delegated agent). In light of the type of
repair that would be required to address the unsafe condition, and
consistent with existing bilateral airworthiness agreements, we have
determined that, for this proposed AD, a repair we or the DGAC approve
would be acceptable for compliance with this proposed AD.
Service Bulletin A340-28-4100, Revision 01, provides operators the
option of contacting Airbus for the possible issuance of an Airbus NTO
[[Page 37299]]
letter to allow continued operation without deactivating the trim tank
for a specified number of flight cycles. This proposed AD would not
allow that action. We can better ensure long-term continued operational
safety by having operators correct the source of the problem, the trim
tank. Anyone may apply for an AMOC and make a request to temporarily
operate an airplane without a deactivated trim tank.
Operators should note that, although the Accomplishment
Instructions of certain referenced service bulletins describe
procedures for submitting an inspection report sheet to Airbus, or
returning removed float valves to the float valve manufacturer, this
proposed AD would not require those actions.
Concurrent Service Information
Airbus Service Bulletins A330-28-3088 and A330-28-3089 identify
Airbus Service Bulletin A330-55-3022 as a concurrent service bulletin,
and Airbus Service Bulletins A340-28-4102 and A340-28-4103 identify
Airbus Service Bulletin A340-55-4023 as a concurrent service bulletin.
The concurrent service bulletins include procedures for installing
Teflon gore joints on front spar access panel 343ER. That action
reduces the number of work hours needed to remove and install the
access panel when the new, improved float valves are installed. The
French airworthiness directives do not mandate accomplishment of the
concurrent service bulletins and this proposed AD would not require
accomplishment of the concurrent service bulletins.
Clarification of Life Limit in Paragraph (h) of the Proposed AD
For Airbus Model A330 series airplanes, French airworthiness
directive F-2005-003, dated January 5, 2005, mandates a life limit of
24,500 flight cycles ``since new'' for Intertechnique float valve, P/N
L87-13-002. This P/N failed in a mode that potentially re-introduced
the possible ignition source, so a life limit is necessary. The DGAC
has informed us that it does not intend to issue a parallel French
airworthiness directive for Airbus Model A340 series airplanes. The
DGAC states that a float valve life limit of 24,500 flight cycles is
above the A340 design service goal of 20,000 flight cycles.
Intertechnique float valve, P/N L87-13-003, did not exhibit any failure
during qualification tests and does not have a life limit for Airbus
Model A330 or A340 series airplanes.
Clarification of Inspection Terminology
In this proposed AD, the ``detailed visual inspection'' specified
in the Airbus service bulletins is referred to as a ``detailed
inspection.'' We have included the definition for a detailed inspection
in Note 1 of this AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
of Model A330 series airplanes to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Borescope inspection, per 2 (1 hour per float, $65 None................. $130 25 $3,250, per
inspection cycle. 2 floats per inspection cycle.
airplane).
Installation of float valves....... 4 (2 per valve, 2 65 No charge............ 260 25 $6,500, per
valves per airplane). installation.
Bonding test (new, improved float 1.................... 65 None................. 65 25 $1,625.
valves, left trim tank only).
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Currently, there are no affected Model A340 series airplanes on the
U.S. Register. However, should an affected airplane be imported and
placed on the U.S. Register in the future, it would be subject to the
proposed actions of this AD. The estimated costs would be the same as
those listed above for the Model A330 series airplanes.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
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 proposed AD. 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
[[Page 37300]]
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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA-2005-21702; Directorate Identifier 2005-NM-
024-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by July 29, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330 and A340 series
airplanes, certificated in any category, as identified in Table 1 of
this AD.
Table 1.--Applicability
------------------------------------------------------------------------
Except those modified in
Airbus model production by airbus
modification
------------------------------------------------------------------------
A330 series airplanes.................. 51953 and either 52110 or 53081
A340-200 and -300 series airplanes..... 51953 and either 52110 or 53081
A340-541 and -642 airplanes............ 51951 and either 52109 or 53081
------------------------------------------------------------------------
Unsafe Condition
(d) This AD was prompted by reports of detached and damaged
float valves in the left and right fuel tanks of the trimmable
horizontal stabilizers (trim tanks). We are issuing this AD to
prevent, in the event of a lightning strike to the horizontal
stabilizer, sparking of metal parts and debris from detached and
damaged float valves, or a buildup of static electricity, which
could result in ignition of fuel vapors and consequent fire or
explosion.
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.
Borescope Inspection
(f) At the later of the times specified in paragraph (f)(1) and
(f)(2) of this AD: Do a borescope inspection for detached or damaged
float valves in the left and right trim tanks, by doing the
applicable actions in the Accomplishment Instructions of Airbus
Service Bulletins A330-28-3086, dated July 24, 2003; and A330-28-
3087, Revision 01, dated August 16, 2004 (for Model A330 series
airplanes); or A340-28-4100 and A340-28-4101, both Revision 01, both
dated August 16, 2004 (for Model A340-200 and -300 series
airplanes); as applicable.
(1) Prior to the accumulation of 2,500 total flight cycles or
15,000 total flight hours, whichever is first.
(2) Within 7,500 flight hours after the effective date of this
AD.
Related Investigative and Corrective Actions
(g) Depending on the results of the inspection required by
paragraph (f) of this AD: Do the applicable actions in accordance
with the Accomplishment Instructions of the applicable service
bulletin identified in Table 2 of this AD, at the times specified in
Table 2.
Table 2.--Inspection Results and Related Investigative/Corrective Actions
----------------------------------------------------------------------------------------------------------------
In accordance with Airbus
If inspection results reveal-- Then-- Service Bulletin--
----------------------------------------------------------------------------------------------------------------
Detached or damaged float valve in the Before further flight: (1) Remove the A330-28-3086, dated July
right trim tank. detached float and float debris from the 24, 2003.
trim tank and do a detailed inspection A340-28-4100, Revision 01,
for structural damage to the affected dated August 16, 2004.
trim tank tank. Repair any structural
damage to the trim tank or deactivate the
trim tank, before further flight, in
accordance with the applicable service
bulletin, or in accordance with a method
approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane
Directorate; or the Direction
G[eacute]n[eacute]rale de l'Aviation
Civile (DGAC) (or its delegated agent).
Where the service bulletin specifies to
contact the manufacturer, instead contact
the Manager, International Branch, ANM-
116, or the DGAC (or its delegated agent).
Before further flight, after doing the A330-28-3086, dated July
detailed inspection and repairing any 24, 2003.
structural damage: (2) Replace the A330-28-3088, dated April
affected float valve with a new unit 27, 2004.
having the same part number (P/N), or a A340-28-4100, Revision 01,
new, improved float valve, P/N 62015-1. dated August 16, 2004.
If a new unit of P/N 61600 is installed, A340-28-4102, dated April
thereafter, do the inspection required by 27, 2004.
paragraph (f) of this AD at intervals not
to exceed 2,500 flight cycles or 15,000
flight hours, whichever is first, after
the most recent inspection, until
paragraph (h) of this AD is accomplished.
Detached or damaged float valve in the Before further flight: (1) Remove the A330-28-3087, Revision 01,
left trim tank. detached float and float debris from the dated August 16, 2004.
trim tank and do a detailed inspection A340-28-4101, Revision 01,
for structural damage to the affected dated August 16, 2004.
trim tank. Repair any structural damage
to the trim tank or deactivate the trim
tank, before further flight, in
accordance with the applicable service
bulletin, or in accordance with a method
approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane
Directorate; or the DGAC (or its
delegated agent). Where the service
bulletin specifies to contact the
manufacturer, instead contact the
Manager, International Branch, ANM-116,
or the DGAC (or its delegated agent).
[[Page 37301]]
Before further flight, after doing the A330-28-3087, Revision 01,
detailed inspection and repairing any dated August 16, 2004.
structural damage: (2) Replace the A330-28-3089, Revision 02,
affected float valve with either a new dated April 1, 2005.
unit having that same P/N, or a new A330-28-3094, dated April
improved float valve, P/N L87-13-002 or P/ 7, 2005.
N L87-13-003. If a new unit of P/N L87-13- A340-28-4101, Revision 01,
001 is installed, thereafter, do the dated August 16, 2004.
inspection required by paragraph (f) of A340-28-4103, Revision 02,
this AD at intervals not to exceed 2,500 dated April 1, 2005.
flight cycles or 15,000 flight hours, A340-28-4111, dated April
whichever is first, after the most recent 6, 2005.
inspection, until paragraph (h) of this
AD is accomplished. For Airbus Model A330
series airplanes, if a float valve having
P/N L87-13-002 is installed, thereafter,
replace that float valve with a float
valve having that same P/N at intervals
not to exceed those specified in
paragraph (h) of this AD. Installation of
P/N L87-13-003 on Airbus Model A330
series airplanes terminates the
repetitive float valve replacement
required by paragraph (h) of this AD.
No damaged or detached float valve in Within 10,000 flight hours or 1,500 flight A330-28-3086, dated July
the right trim tank. cycles, whichever is first, from the 24, 2003.
initial float inspection done in A330-28-3088, dated April
accordance with paragraph (f) of this AD, 27, 2004.
replace the existing Argo-new Tech float A340-28-4100, Revision 01,
valve, P/N 61600, with either a unit dated August 16, 2004.
having that same P/N, or a new, improved A340-28-4102, dated April
float valve, P/N 62015-1. If a new unit 27, 2004.
of P/N 61600 is installed, thereafter,
repeat the inspection required by
paragraph (f) of this AD at intervals not
to exceed 2,500 flight cycles or 15,000
flight hours, whichever is first, until
paragraph (h) of this AD is accomplished.
No damaged detached float valve in the Within 10,000 flight hours or 1,500 flight A330-28-3087, Revision 01,
left trim tank. cycles, whichever is first, from the August 16, 2004.
initial inspection done in accordance A330-28-3089, Revision 02,
with paragraph (f) of this AD, replace dated April 1, 2005.
the existing trim tank Intertechnique A330-28-3094, dated April
float valve, P/N L87-13-001, with either 7, 2005.
a new unit having that same P/N, or a new A340-28-4101, Revision 01,
improved float valve, P/N L87-13-002 or P/ dated August 16, 2004.
N L87-13-003. If a new unit of P/N L87-13- A340-28-4103, Revision 02,
001 is installed, thereafter, do the dated April 1, 2005.
inspection required by paragraph (f) of A340-28-4111, dated April
this AD at intervals not to exceed 2,500 6, 2005.
flight cycles or 15,000 flight hours,
whichever is first, after the most recent
inspection, until paragraph (h) of this
AD is accomplished. For Airbus Model A330
series airplanes, if a float valve having
P/N L87-13-002 is installed, thereafter,
replace that float valve with a float
valve having that same P/N at intervals
not to exceed those specified in
paragraph (h) of this AD. Installation of
P/N L87-13-003 on Airbus Model A330
series airplanes terminates the
repetitive float valve replacement
required by paragraph (h) of this AD.
----------------------------------------------------------------------------------------------------------------
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Installation of New, Improved Float Valves
(h) Within 50 months after the effective date of this AD:
Replace any Argo-Tech float valve, P/N 61600, with a new, improved
float valve, P/N 62015-1; replace any Intertechnique float valve, P/
N L87-13-001, with a new, improved float valve, P/N L87-13-002 or P/
N L87-13-003; and do any applicable corrective action; by
accomplishing the actions specified in the Accomplishments
Instructions of the applicable service bulletin in Table 3 of this
AD. Do any applicable corrective action before further flight. For
Airbus Model A330 series airplanes, if P/N L87-13-002 is installed,
replace the float valve thereafter at intervals not to exceed 24,500
flight cycles. Installation of P/N L87-13-003 on Airbus Model A330
series airplanes terminates the repetitive float valve replacement
required by this paragraph. Installation of either P/N L87-13-002 or
P/N L87-13-003 terminates the borescope inspections required by
paragraphs (f) and (g) of this AD. Where the service bulletin
specifies to contact the manufacturer, instead contact the Manager,
International Branch, ANM-116, or the DGAC (or its delegated agent).
Table 3.--Service Information for New Float Valves
------------------------------------------------------------------------
Airbus service
Airbus model Float valve P/N bulletin
------------------------------------------------------------------------
A330 series airplanes......... 62015-1.......... A330-28-3088, dated
L87-13-002....... April 27, 2004.
L87-13-003....... A330-28-3089,
Revision 02, dated
April 1, 2005.
A330-28-3094, dated
April 7, 2005.
340-200 and -300 series 62015-1.......... A340-28-4102, dated
airplanes. L87-13-002....... April 27, 2004.
L87-13-003....... A340-28-4103,
Revision 02, dated
April 1, 2005.
A340-28-4111, dated
April 6, 2005.
A340-541 and -642 airplanes... 62015-1.......... A340-28-5007, dated
L87-13-002....... May 7, 2004.
L87-13-003....... A340-28-5010, dated
May 7, 2004.
A340-28-5021, dated
April 6, 2005.
------------------------------------------------------------------------
[[Page 37302]]
Actions Accomplished Previously
(i) Inspections and related investigative and corrective actions
accomplished before the effective date of this AD, in accordance
with any applicable Airbus service bulletin identified in Table 4 of
this AD, are acceptable for compliance with the corresponding
actions specified in this AD.
Table 4.--Service Information For Actions Accomplished Previously
------------------------------------------------------------------------
Airbus model Airbus service bulletin
------------------------------------------------------------------------
A330 series airplanes.................. A330-28-3087, dated July 24,
2003.
A330-28-3089, Revision 01,
dated May 12, 2004.
A340-200 and -300 series airplanes..... A340-28-4100, dated July 24,
2003.
A340-28-5010, dated May 7,
2004.
A340-28-5021, dated April 6,
2005.
------------------------------------------------------------------------
No Submission of Information/Parts
(j) Where any Airbus service bulletin specifies to submit
information to Airbus, or send removed float valves to either Argo-
Tech or Intertechnique, those actions are not required by this AD.
Alternative Methods of Compliance (AMOCs)
(k) 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.
Related Information
(l) French airworthiness directives F-2005-003, dated January 5,
2005, and F-2005-004 R1 and F-2005-005 R1, both dated April 27,
2005, also address the subject of this AD.
Issued in Renton, Washington, on June 22, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-12839 Filed 6-28-05; 8:45 am]
BILLING CODE 4910-13-P