[Federal Register Volume 71, Number 64 (Tuesday, April 4, 2006)]
[Proposed Rules]
[Pages 16716-16721]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-4825]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24289; Directorate Identifier 2005-NM-186-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series 
Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, 
and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-
600 Series Airplanes); and A310-200 and -300 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 all Airbus airplanes identified above. This proposed AD would 
require improving the routing of certain electrical wire bundles in 
certain airplane zones, as applicable to the airplane model. This 
proposed AD results from fuel system reviews conducted by the 
manufacturer. We are proposing this AD 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.

DATES: We must receive comments on this proposed AD by May 4, 2006.

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: Thomas Stafford, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1622; 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 ``FAA-2006-
24289; Directorate Identifier 2005-NM-186-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

[[Page 16717]]

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

    The FAA has examined the underlying safety issues involved in 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 (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 
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.
    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 A300 B2 and A300 B4, 
A300-600, A310-200, and A310-300 series airplanes. The DGAC recommends 
improving the routing of certain electrical wire bundles in certain 
airplane zones to minimize the risk of explosion. We have determined 
that the actions identified in this 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.

Relevant Service Information

    Airbus has issued the service bulletins identified below. These 
service bulletins describe procedures for six different actions related 
to improving the routing of certain electrical wire bundles in certain 
airplane zones, as applicable to the airplane model. Each action is 
described in detail after the table.

                                            Airbus Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                                              Described in service   Prior or concurrent action--
               Action                 Applicable to model--        bulletin--
----------------------------------------------------------------------------------------------------------------
                                     A300 B2 and A300 B4     A300-28-0057, Revision  None.
                                      series airplanes.       02, dated January 8,
                                                              2001.
                                     A300-600 series         A300-28-6018, Revision  None.
                                      airplanes.              1, dated September
                                                              15, 1988.
2..................................  A300 B2 and A300 B4     A300-28-0070, Revision  None.
                                      series airplanes.       01, dated March 18,
                                                              1999.
                                     A300-600 series         A300-28-6048, dated     Do a visual inspection for
                                      airplanes.              September 19, 1996.     damage (chafing and burn
                                                                                      marks) of the protective
                                                                                      conduits behind specified
                                                                                      access doors, and replace
                                                                                      or repair any damaged
                                                                                      wires, in accordance with
                                                                                      Airbus Service Bulletin
                                                                                      A300-28-6010, Revision 1,
                                                                                      dated September 17, 1986.
                                     A310-200 and -300       A310-28-2112, dated     Do a visual inspection for
                                      Series Airplanes.       September 19, 1996.     damage (chafing and burn
                                                                                      marks) of the protective
                                                                                      conduits behind specified
                                                                                      access doors, and replace
                                                                                      or repair any damaged
                                                                                      wires, in accordance with
                                                                                      Airbus Service Bulletin
                                                                                      A310-28-2008, Revision 2,
                                                                                      dated May 14, 1990.

[[Page 16718]]

 
3..................................  A300 B2 and A300 B4     A300-24-0085, Revision  Do repetitive inspections
                                      series airplanes.       06, dated October 13,   of the wire looms on the
                                                              2005.                   wing trailing edge for
                                                                                      improperly held wires in
                                                                                      the clamps, repair any
                                                                                      damaged wires, restore the
                                                                                      electrical bundles to good
                                                                                      condition, and replace the
                                                                                      affected nylon clamps with
                                                                                      metallic clamps that have
                                                                                      white silicone lining, in
                                                                                      accordance with Airbus
                                                                                      Service Bulletin A300-24-
                                                                                      0073, Revision 04, dated
                                                                                      June 30, 1998.
                                     A300-600 series         A300-24-6043, Revision  Do repetitive inspections
                                      airplanes.              06, dated October 13,   of the wire looms on the
                                                              2005.                   wing trailing edge for
                                                                                      improperly held wires in
                                                                                      the clamps, repair any
                                                                                      damaged wires, restore the
                                                                                      electrical bundles to good
                                                                                      condition, and replace the
                                                                                      affected nylon clamps with
                                                                                      metallic clamps that have
                                                                                      white silicone lining, in
                                                                                      accordance with Airbus
                                                                                      Service Bulletin A300-24-
                                                                                      6004, Revision 03, dated
                                                                                      June 30, 1998.
4..................................  A300-600 series         A300-28-6056, dated     None.
                                      airplanes.              February 18, 1998.
5..................................  A300-600 series         A300-24-6004, Revision  None.
                                      airplanes.              03, dated June 30,
                                                              1998.
                                     A310-200 and -300       A310-24-2009, Revision  None.
                                      Series Airplanes.       03, dated June 30,
                                                              1998.
6..................................  A300 B2 and A300 B4     A300-24-0100, dated     None.
                                      series airplanes.       April 7, 2005.
                                     A300-600 series         A300-24-6084, Revision  None.
                                      airplanes.              01, dated June 28,
                                                              2005.
                                     A310-200 and -300       A310-24-2091, dated     None.
                                      Series Airplanes.       March 4, 2005.
----------------------------------------------------------------------------------------------------------------

    Action 1--Install a heat-shrinkable sleeve along the complete 
length of the electrical supply bundle of the fuel pumps. These 
electrical supply bundles are located in metallic protective conduits 
in zones 571 and 671.
    Action 2--Install a heat-shrinkable sleeve along the complete 
length of the electrical supply bundle of the fuel pumps. These 
electrical supply bundles are located in metallic protective conduits 
in zones 575 and 675.
    Action 3--Modify the retaining and protection system for the 
electrical bundles located at the wing-to-fuselage junctions, under the 
flap control screw jack. The modification involves installing a 
modified blanking plate and its related hardware, inspecting the 
bundles for damaged wires, repairing the wires if necessary, installing 
protective tape, and adding clamping to the bundles in order to improve 
their fastening capability. For some airplane models, Action 5 or 
Action 6 is necessary before or concurrently with this action.
    Action 4--Modify the electrical wiring of routes 1P and 2P (along 
the top panel of the shroud box and the rear spars of the wings) by 
extending the protective conduits up to the next support, and replace 
the two existing clamps on this support with new improved clamps.
    Action 5--Do repetitive inspections of the wire looms on the wing 
trailing edge for improperly held wires in the clamps, repair any 
damaged wires, restore the electrical bundles to good condition, and 
replace the affected nylon clamps with metallic clamps that have white 
silicone lining.
    Action 6--Replace the nylon clamps of the electrical routes in the 
hydraulic compartment and in the shroud box with new metallic clamps 
that have white silicone lining (for Model A310-200 and -300 series 
airplanes); or replace the nylon clamps and change the location of 
routes 1P and 2P to improve the retention of the wiring loom (for all 
other affected models).
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information and issued French airworthiness directive F-
2005-112 R1, dated September 14, 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 airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously.

Clarification of Inspection Terminology

    In this proposed AD, the ``inspection'' specified in Airbus Service 
Bulletins A300-24-0073, A300-24-0085, A300-24-6004, A300-24-6043, and 
A310-24-2009; and the ``visual inspection'' specified in Airbus Service 
Bulletin A310-28-2008; are referred to as a ``general visual 
inspection.'' We have included the definition for a general visual 
inspection in a note in the proposed AD.

Costs of Compliance

    This proposed AD would affect about 169 airplanes of U.S. registry. 
The following table provides the estimated costs for U.S. operators to 
comply with this proposed AD. The average labor rate is $80 per work 
hour.

[[Page 16719]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
For airplanes on which this action is
              required--                      Work hours                 Parts              Cost per airplane
----------------------------------------------------------------------------------------------------------------
Action 1, Install heat-shrinkable      10.....................  Operator Supplied......  $800.
 wrap (zones 571 and 671).
Action 2, Install heat-shrinkable      16 to 37...............  $1,533 to $1,790.......  $2,813 to $4,750.
 wrap (zones 575 and 675).
Action 3, Modify the retaining and     4 to 16................  $836 to $1,056.........  $1,156 to $2,336.
 protection system.
Action 4, Modify the electrical        2......................  $720...................  $880.
 wiring of routes 1P and 2P.
Action 5, Inspect the wire looms on    8......................  Operator Supplied......  $640.
 the wing trailing edge.
Action 6, Replace the nylon clamps of  44 to 98...............  $100 to $5,700.........  $3.620 to $13,540.
 the electrical routes in the
 hydraulic compartment and in the
 shroud box.
----------------------------------------------------------------------------------------------------------------

    Based on these figures, the estimated cost of the proposed AD for 
U.S. operators is up to $3,877,874, or up to $22,946 per airplane.
    The following table provides the estimated costs for U.S. operators 
to comply with the applicable prior or concurrent requirements in this 
proposed AD.

                                Estimated Costs--Prior or Concurrent Requirements
----------------------------------------------------------------------------------------------------------------
               Action--                       Work hours                 Parts              Cost per airplane
----------------------------------------------------------------------------------------------------------------
Inspect the wire looms on the wing     8......................  None...................  $640.
 trailing edge for improperly held
 wires, in accordance with Airbus
 Service Bulletin A300-24-6004.
Inspect for damage of the protective   4 to 7.................  None...................  $320 to $560.
 conduits behind specified access
 doors in accordance with Airbus
 Service Bulletin A300-28-6010 or
 A310-28-2008, as applicable.
Inspect the wire looms on the wing     8......................  None...................  $640.
 trailing edge for improperly held
 wires in accordance with Airbus
 Service Bulletin A300-24-0073.
----------------------------------------------------------------------------------------------------------------

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 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-24289; Directorate Identifier 2005-NM-
186-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by May 4, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-
3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, 
B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and 
Model C4-605R Variant F airplanes; and A310-203, -204, -221, -222, -
304, -322, -324, and -325 airplanes; certificated in any category.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD 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.

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.

Action 1--Install Heat-Shrinkable Sleeve, Zones 571 and 671

    (f) For all airplanes identified in paragraphs (f)(1) and (f)(2) 
of this AD: Within 26 months after the effective date of this AD, 
install a heat-shrinkable sleeve along the complete length of the 
electrical supply bundles for the fuel pumps. These electrical

[[Page 16720]]

supply bundles are located in metallic protective conduits in zones 
571 and 671.
    (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, 
and B4-203 airplanes: Do the action specified in paragraph (f) of 
this AD in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-28-0057, Revision 02, dated January 8, 2001.
    (2) For Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, 
B4-622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes; 
except those on which Airbus Modification 6803 has been done: Do the 
action specified in paragraph (f) of this AD in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-28-6018, 
Revision 1, dated September 15, 1988.

Action 2--Install Heat-Shrinkable Sleeve, Zones 575 and 675

    (g) For all airplanes identified in paragraphs (g)(1), (g)(2), 
and (g)(3) of this AD: Within 26 months after the effective date of 
this AD, install a heat-shrinkable sleeve along the complete length 
of the electrical supply bundles for the fuel pumps. These 
electrical supply bundles are located in metallic protective 
conduits in zones 575 and 675. For airplanes identified in 
paragraphs (g)(2) and (g)(3) of this AD: Prior to or concurrently 
with this installation, do a general visual inspection for damage of 
the protective conduits behind specified access doors, and do any 
applicable corrective action before further flight; in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-28-6010, Revision 1, dated September 17, 1986; or Airbus 
Service Bulletin A310-28-2008, Revision 2, dated May 14, 1990; as 
applicable.
    (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, 
and B4-203 airplanes: Do the actions specified in paragraph (g) of 
this AD in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-28-0070, Revision 01, dated March 18, 1999.
    (2) For Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, 
B4-622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes; 
except those on which Airbus Modification 10505 has been done: Do 
the actions specified in paragraph (g) of this AD in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-28-
6048, dated September 19, 1996.
    (3) For Model A310-203, -204, -221, -222, -304, -322, -324, and 
-325 airplanes, except those on which Airbus Modification 10505 has 
been done: Do the actions specified in paragraph (g) of this AD in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-38-2112, dated September 19, 1996.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

Action 3--Modify the Retaining and Protection System

    (h) For all airplanes identified in paragraphs (h)(1), and 
(h)(2) of this AD: Within 26 months after the effective date of this 
AD, modify the retaining and protection system for the electrical 
bundles located at the wing-to-fuselage junction, under the flap 
control screw jack. Prior to or concurrently with this action for 
airplanes identified in paragraphs (h)(1) and (h)(2) of this AD: Do 
a general visual inspection for improperly held wires of the wire 
looms on the wing trailing edge, restore the electrical bundles to 
good condition, and replace the affected nylon clamps with metallic 
clamps that have white silicone lining; and do any applicable 
corrective action before further flight; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-24-0073, 
Revision 04, dated June 30, 1998; or Airbus Service Bulletin A300-
24-6004, Revision 03, dated June 30, 1998; as applicable.
    (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, 
and B4-203 airplanes: Do the actions specified in paragraph (h) of 
this AD in accordance with the Accomplishment Instructions Airbus 
Service Bulletin A300-24-0085, Revision 06, dated October 13, 2005.
    (2) For Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, 
B4-622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes, 
except those on which Airbus Modification 11276 has been done: Do 
the action specified in paragraph (h) of this AD in accordance with 
the Accomplishment Instructions Airbus Service Bulletin A300-24-
6043, Revision 06, dated October 13, 2005.

Action 4--Modify the Electrical Wiring of Routes 1P and 2P

    (i) For Model A300 B4-601, B4-603, B4-620, B4-622, A300 B4-605R, 
B4-622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes; 
except those on which Airbus Modification 11741 has been done: 
Within 26 months after the effective date of this AD, modify the 
electrical wiring of routes 1P and 2P (along the top panel of the 
shroud box and the rear spars of the wings) by extending the 
protective conduits up to the next support, and replace the two 
existing clamps on this support with new improved clamps. Do all 
actions in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-28-6056, dated February 18, 1998.

Action 5--Inspect the Wire Looms

    (j) For all airplanes identified in paragraphs (j)(1) and (j)(2) 
of this AD: Within 24 months after the effective date of this AD, do 
a general visual inspection of the wire looms on the wing trailing 
edge for improperly held wires in the clamps, restore the electrical 
bundles to good condition, and replace the affected nylon clamps 
with metallic clamps that have an elastometer lining. Do any 
applicable corrective action before further flight. Repeat the 
inspection thereafter at intervals not to exceed 24 months until all 
clamps have been replaced.
    (1) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes; except 
those on which Airbus Modification 6478 has been done: Do the 
actions specified in paragraph (j) of this AD in accordance with the 
Accomplishment Instructions Airbus Service Bulletin A300-24-6004, 
Revision 03, dated June 30, 1998.
    (2) For Model A310-203, -204, -221, -222, -304, -322, -324, and 
-325 airplanes, except those on which Airbus Modification 478 has 
been done: Do the actions specified in paragraph (j) of this AD in 
accordance with the Accomplishment Instructions Airbus Service 
Bulletin A310-24-2009, Revision 03, dated June 30, 1998.

Action 6--Improve the Quality of the Electrical Routes

    (k) For all airplanes identified in paragraphs (k)(1), (k)(2), 
and (k)(3) of this AD: Within 26 months after the effective date of 
this AD, replace the nylon clamps of the electrical routes in the 
hydraulic compartment and in the shroud box with new metallic clamps 
that have white silicone lining (for airplanes identified in 
paragraph (k)(1) of this AD); or replace the nylon clamps and change 
the location of routes 1P and 2P to improve the retention of the 
wiring loom (for airplanes identified in paragraphs (k)(2) and 
(k)(3) of this AD).
    (1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, 
and B4-203 airplanes; except those on which Airbus Modification 
11763 has been done: Do the action specified in paragraph (k) of 
this AD in accordance with the Accomplishment Instructions Airbus 
Service Bulletin A300-24-0100, dated April 7, 2005.
    (2) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes; except 
those on which Airbus Modifications 11763 and 12995 have been done: 
Do the action specified in paragraph (k) of this AD in accordance 
with the Accomplishment Instructions Airbus Service Bulletin A300-
24-6084, Revision 01, dated June 28, 2005.
    (3) For Model A310-203, -204, -221, -222, -304, -322, -324, and 
-325 airplanes, except those on which Airbus Modification 11763 has 
been done: Do the action specified in paragraph (k) of this AD in 
accordance with the Accomplishment Instructions as identified in 
Airbus Service Bulletin A310-24-2091, dated March 4, 2005.

Parts Installation

    (l) After the effective date of this AD, no person may install 
on any airplane plate assemblies with part numbers A5351088000000 or 
A5351088000100 unless they have been modified in accordance with 
paragraph (h) of this AD.

[[Page 16721]]

Actions Accomplished According to Previous Revisions of Service 
Bulletins

    (m) Actions done before the effective date of this AD in 
accordance with the service bulletins identified in Table 1 of this 
AD are acceptable for compliance with the corresponding requirement 
in this AD.

            Table 1.--Previous Revisions of Service Bulletins
------------------------------------------------------------------------
   Airbus service bulletin       Revision level             Date
------------------------------------------------------------------------
A300-28-0070................  Original............  September 19, 1996.
A300-24-0073................  3...................  February 24, 1995.
A300-24-0085................  Original............  December 12, 1994.
A300-24-0085................  03..................  January 17, 1996.
A300-24-0085................  04..................  July 23, 1996.
A300-24-0085................  05..................  March 6, 2001.
A300-28-057.................  1...................  September 15, 1988.
A300-24-073.................  Original............  June 9, 1986.
A300-24-073.................  1...................  January 28, 1988.
A300-24-073.................  2...................  September 10, 1990.
A300-24-6004................  1...................  January 28, 1988.
A300-24-6004................  2...................  February 24, 1995.
A300-28-6018................  Original............  June 21, 1988.
A300-24-6043................  Original............  December 12, 1994.
A300-24-6043................  01..................  February 7, 1995.
A300-24-6043................  02..................  May 10, 1995.
A300-24-6043................  03..................  January 17, 1996.
A300-24-6043................  04..................  March 6, 2001.
A300-24-6043................  05..................  August 30, 2001.
A300-24-6084................  Original............  March 4, 2005.
A310-24-2009................  Original............  May 31, 1985.
A310-24-2009................  1...................  January 28, 1988.
A310-24-2009................  2...................  February 24, 1995.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (n)(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

    (o) French airworthiness directive F-2005-112 R1, dated 
September 14, 2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on March 24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-4825 Filed 4-3-06; 8:45 am]
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