[Federal Register: January 25, 2007 (Volume 72, Number 16)]
[Proposed Rules]
[Page 3371-3373]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr25ja07-17]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 3371]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27011; Directorate Identifier 2006-NM-175-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320, and A321
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 supersede an existing airworthiness
directive (AD) that applies to all Airbus Model A318, A319, A320, and
A321 airplanes. The existing 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 proposed AD would require modifying or replacing the fuel tank
boost pumps, which would allow removal of the limitations from the AFM
and the maintenance program. This proposed 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 proposing 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: We must receive comments on this proposed AD by February 26,
2007.
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.
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 proposed 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:
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 in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2007-27011; Directorate Identifier 2006-NM-175-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 received 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
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 http://dms.dot.gov.
Examining the Docket
You may 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 Docket Management System
receives them.
Discussion
On June 7, 2006, we issued AD 2006-12-02, amendment 39-14626 (71 FR
34814, June 16, 2006), for all Airbus Model A318, A319, A320, and A321
airplanes. That 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. That AD also provides for optional
terminating action for compliance with the revisions to the AFM and the
maintenance program. That AD resulted 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 issued that 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.
Actions Since Existing AD Was Issued
We considered AD 2006-12-02 interim action and were considering
further rulemaking if final action were later identified. We now have
determined that further rulemaking is necessary, and this proposed AD
follows from that determination. Airbus has developed a modification to
prevent the screws from coming loose and
[[Page 3372]]
issued new service information that addresses the identified unsafe
condition.
Relevant Service Information
Airbus has issued the following service bulletins:
Service Bulletins
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Airbus Service Bulletin Revision Date
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A320-28-1152...................... Original May 5, 2006.
01 July 17, 2006.
A320-28-1153...................... 01 July 13, 2006.
------------------------------------------------------------------------
Service Bulletin A320-28-1152 describes procedures for determining
the type, part number, and serial number of the fuel pumps of the wing
and center tanks by either checking airplane records or inspecting the
pump amendment label. The service bulletin recommends modifying
affected fuel pumps in accordance with Service Bulletin A320-28-1153.
Service Bulletin A320-28-1153 describes procedures for modifying the
affected fuel pumps by replacing the nuts and bolts from the gas return
outlet with new nuts and bolts, applying the correct torque to the
nuts, and applying locktite adhesive, or replacing affected pumps with
pumps having a serial number other than 6137 and subsequent.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The European
Aviation Safety Agency (EASA), which is the aviation authority for the
European Union, mandated the service information and issued
airworthiness directive 2006-0222, dated July 20, 2006, to ensure the
continued airworthiness of these airplanes in the European Union.
Service Bulletin A320-28-1153 refers to Eaton Service Bulletin
8410-28-04, dated May 2, 2006, as an additional source of service
information for the modification.
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
Sec. 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
airplanes of this type design that are certificated for operation in
the United States.
This proposed AD would supersede AD 2006-12-02 and would retain the
requirements and provisions of the existing AD. This proposed AD would
also require modifying affected fuel pumps, which would allow removal
of the limitations from the AFM and the maintenance program.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD. The parts manufacturer states that it
will modify the pump free of charge.
Estimated Costs
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Number of
Average Cost per U.S.-
Action Work hours labor rate Parts airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Identify boost pumps, as 1 $80 None $80 727 $58,160
required by AD 2006-12-02..
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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 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 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, 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:
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14626 (71 FR 34814, June 16, 2006) and adding the
following new airworthiness directive (AD):
Airbus: Docket No. FAA-2007-27011; Directorate Identifier 2006-NM-
175-AD.
[[Page 3373]]
Comments Due Date
(a) The FAA must receive comments on this AD action by February
26, 2007.
Affected ADs
(b) This AD supersedes AD 2006-12-02.
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 prevent electrical arcing in the fuel tank boost pump motor,
which in the presence of a combustible air-fuel mixture in the fuel
tank boost 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 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.
Accomplishment of the inspection or records review as specified in
Airbus Service Bulletin A320-28-1152, dated May 5, 2006; or Revision
01, dated July 17, 2006; is one approved method for conducting this
inspection or records 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 (j) 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, until the modification required by paragraph (h) of this
AD has been done.
(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.''
(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.
New Requirements of This AD
Terminating Action
(h) 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: At the applicable time
specified in paragraph (h)(1) or (h)(2) of this AD, either modify or
replace affected fuel boost pumps in accordance with Airbus Service
Bulletin A320-28-1153, Revision 01, dated July 13, 2006.
Modification or replacement of all affected fuel tank boost pumps on
an airplane terminates the requirements of paragraph (g) of 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.
(1) For the center tank fuel pumps: Within 1,000 flight hours or
3 months after the effective date of this AD, whichever occurs
first.
(2) For the wing tank fuel pumps: Within 2,000 flight hours or 6
months after the effective date of this AD, whichever occurs first.
Note 1: Airbus Service Bulletin A320-28-1153 refers to Eaton
Service Bulletin 8410-28-04, dated May 2, 2006, as an additional
source of service information for the fuel pump modification.
Previous Accomplishment
(i) Modification of a fuel pump before the effective date of
this AD in accordance with Airbus Service Bulletin A320-28-1153,
dated May 5, 2006, is acceptable for compliance with the
requirements of paragraph (h) of this AD for that pump only.
Parts Installation
(j) As of the effective date of this AD, no person may install a
boost pump, P/N 568-1-27202-005, having any S/N 6137 and subsequent,
on any airplane, unless the boost pump has been modified in
accordance with this AD.
Alternative Methods of Compliance (AMOCs)
(k)(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
(l) European Aviation Safety Agency airworthiness directive
2006-0222, dated July 20, 2006, also addresses the subject of this
AD.
Issued in Renton, Washington, on January 12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-1093 Filed 1-24-07; 8:45 am]
BILLING CODE 4910-13-P