[Federal Register Volume 71, Number 147 (Tuesday, August 1, 2006)]
[Proposed Rules]
[Pages 43386-43390]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-12301]



[[Page 43386]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25423; Directorate Identifier 2006-NM-029-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 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 A300 airplanes. The 
existing AD currently requires repetitive inspections for cracking and 
corrosion in the lower rim area of the rear pressure bulkhead and 
adjacent areas, repetitive inspections for cracking or corrosion in the 
service apertures and the upper rim area of the rear pressure bulkhead, 
and corrective actions if necessary. This proposed AD would remove 
certain repetitive inspections and reduce the repetitive interval of 
one inspection. This proposed AD would also require an inspection for 
missing or damaged sealant of the area between the outer attachment 
angle and circumferential joint doubler, and corrective action if 
necessary. This proposed AD would also require additional inspections 
for corrosion of certain areas and repetitive inspections for airplanes 
on which repairs have been done. This proposed AD results from reports 
of corrosion and cracking in the various components associated with the 
rear pressure bulkhead. We are proposing this AD to prevent reduced 
structural capability of the fuselage and consequent decompression of 
the airplane.

DATES: We must receive comments on this proposed AD by August 31, 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, FAA, Transport Airplane Directorate, 
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 ``Docket No. 
FAA-2006-25423; Directorate Identifier 2006-NM-029-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 January 8, 1990, we issued AD 90-03-08, amendment 39-6481 (55 FR 
1799, January 19, 1990), for all Airbus Model A300 series airplanes. 
That AD requires repetitive inspections for cracking and corrosion in 
the lower rim area of the rear pressure bulkhead and adjacent areas, 
repetitive inspections for cracking or corrosion in the service 
apertures and the upper rim area of the rear pressure bulkhead, and 
corrective actions if necessary. That AD resulted from reports of 
corrosion and cracking in the various components associated with the 
rear pressure bulkhead. We issued that AD to prevent reduced structural 
capability of the fuselage and subsequent decompression of the 
airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 90-03-08, we have issued AD 2005-26-16, 
amendment 39-14437 (70 FR 77307, December 30, 2005), for certain Airbus 
Model A300 B2 and A300 B4 series airplanes; A300 B4-600, B4-600R, and 
F4-600R series airplanes, and C4-605R Variant F airplanes (collectively 
called A300-600 series airplanes); and Airbus Model A310-200 and A310-
300 series airplanes. That AD requires repetitive inspections for 
corrosion on the rear pressure bulkhead between stringer (STGR) 27 
right hand (RH) and STGR 27 left hand (LH), and related investigative 
and corrective actions if necessary. The inspections for the Model A300 
B2 and A300 B4 series airplanes are done in accordance with Airbus 
Service Bulletin A300-53-0363, Revision 01, dated June 10, 2005. 
Service bulletin A300-53-0363 supersedes Airbus Service Bulletin A300-
53-0217, which is cited as an appropriate source of service information 
for doing the actions required by paragraphs A., B., and C. of AD 90-
03-08. Therefore, we have not included the requirements of paragraphs 
A., B., and C. of AD 90-03-08 in this proposed AD.

Relevant Service Information

    Airbus has issued service bulletin A300-53-0218, Revision 02, dated 
May 10, 2005. Airbus Service Bulletin A300-53-218, Revision 1, dated 
July 28, 1989, is cited as an appropriate source of service information 
for doing certain inspections required by AD 90-03-08. Revision 2 of 
the service bulletin describes the following procedures:
     Repetitive inspections for corrosion and cracking of the 
upper rim area of the rear pressure bulkhead from the aft face.
     Repetitive eddy current inspections for cracks and 
corrosion from the

[[Page 43387]]

outboard side in certain areas, as applicable.
     Repetitive inspections for cracks and corrosion of the 
service apertures in the rear pressure bulkhead.
     Repetitive eddy current inspections for cracks and 
corrosion of the apertures for the auxiliary power unit (APU) bleed-air 
and fuel.
     Repetitive inspections of the area between the outer 
attachment angle and circumferential joint doubler to determine if 
sealant is missing or damaged.
     If any cracking or corrosion is found during an 
inspection, the service bulletin specifies doing a repair or contacting 
the manufacturer.
    Revision 02 of the service bulletin provides basically the same 
procedures as Revision 1 for the inspections for corrosion and cracking 
in the area of the rear pressure bulkhead, and repair if necessary. 
However, Revision 02 of the service bulletin specifies reduced 
repetitive intervals for the eddy current inspections of the APU bleed-
air line. Revision 02 also removes certain airplanes from the 
inspection of the area between STGR 25 LH and RH and certain other 
airplanes from the inspection of the area between STGR 26 LH and RH.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, mandated the service information 
and issued French airworthiness directive F-2005-093 R1, dated August 
3, 2005, to ensure the continued airworthiness of these airplanes in 
France.

FAA's Determination and Requirements of the Proposed AD

    This airplane model is manufactured in France and is 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. 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 AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 90-03-08 and would remove 
certain requirements of the existing AD. This proposed AD would also 
reduce the repetitive interval of the eddy current inspections of the 
APU bleed-air line. This proposed AD would also require an inspection 
for missing or damaged sealant of the area between the outer attachment 
angle and circumferential joint doubler, and corrective action if 
necessary. This proposed AD would also require additional inspections 
for corrosion of certain areas and repetitive inspections for airplanes 
on which repairs have been done.

Differences Between the Proposed AD and the Service Bulletin

    Unlike the procedures described in the service bulletin, this 
proposed AD would not permit further flight if cracks or corrosion are 
detected within limits specified in the service bulletin. We have 
determined that, because of the safety implications and consequences 
associated with that cracking or corrosion, repairs must be done before 
further flight.
    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions using a method that we or the 
European Aviation Safety Agency (EASA) (or its delegated agent) 
approve. 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 EASA approve would be acceptable for compliance 
with this proposed AD.
    The service bulletin specifies to ``visually inspect'' for missing 
or damaged sealant. We have determined that this inspection should be 
described as a ``general visual inspection.'' Note 2 has been included 
in this proposed AD to define this type of inspection.

Clarification of Requirement of Certain Inspections

    Airbus Service Bulletin A300-53-218, Revision 1, describes 
repetitive inspections of the area between the outer attachment angle 
and circumferential joint doubler to determine if sealant is missing or 
damaged and corrective action if necessary. The corrective action 
includes removing damaged sealant and applying new sealant to areas 
where sealant is missing or removed. AD 90-03-08 did not specifically 
require that inspection. Revision 02 of Airbus Service Bulletin A300-
53-0218 also includes the inspection for missing or damaged sealant. To 
ensure that the inspection is being done we have added paragraphs (i) 
and (j) to this proposed AD. Doing this inspection and corrective 
action addresses the identified unsafe condition.
    Airbus Service Bulletin A300-53-218, Revision 1, describes 
procedures for doing initial and repetitive non-destructive test (NDT) 
inspections for corrosion and cracks of the outboard sides of certain 
stringers and of the apertures for the APU bleed-air and fuel. AD 90-
03-08 did not require an inspection for corrosion of those areas (AD 
90-03-08 requires NDT inspections of those areas for cracking only; 
certain NDT inspections cannot detect corrosion). Revision 02 of Airbus 
Service Bulletin A300-53-0218 also specifies procedures to do NDT 
inspections of those areas for cracking and corrosion. To inspect those 
areas for corrosion, detailed visual inspections must be done. 
Therefore, paragraph (l) has been included in this proposed AD to 
clarify that, for eddy current (NDT) inspections performed after the 
effective date of this AD, accomplishment of a detailed inspection for 
corrosion must be done at the same time as the eddy current inspection.

Clarification of Actions in AD 90-03-08

    In paragraphs D.1.a. and E.1. of AD 90-03-08 we specify doing 
initial and repetitive X-ray inspections for cracking of the rim area 
of the rear pressure bulkhead as a separate action. Upon further review 
of Airbus Service Bulletin A300-53-218, Revision 1, we have determined 
that these inspections are related investigative actions to the eddy 
current inspections specified in paragraphs D.1.c. and E.3 of AD 90-03-
08. Paragraph 3.B. (4) of Revision 02 of Airbus Service Bulletin A300-
53-0218 describes these inspections in the same manner. Therefore, we 
have removed the X-ray inspection specified in the existing AD and 
added paragraph (l) to this proposed AD to ensure that this inspection 
is done, if necessary, depending on the results of the inspections 
specified in paragraphs (f)(2) and (h)(2) of this AD (specified as 
paragraphs D.1c. and E.3 of AD 90-03-08).
    Revision 02 of Airbus Service Bulletin A300-53-0218 removes MSN 002 
from the inspection of the area between STGR 25 LH and RH and removes 
MSNs 009 through 018 from the inspection of the area between STGR 26 LH 
and RH. We have revised paragraphs (f)(2)(i) and (f)(2)(ii) 
accordingly.

Changes to Existing AD

    This proposed AD would retain certain requirements of AD 90-03-08. 
Since AD 90-03-08 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a

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result, the corresponding paragraph identifiers have changed in this 
proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
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                                            Corresponding requirement in
        Requirement in AD 90-03-08                this proposed AD
------------------------------------------------------------------------
Paragraph D...............................  Paragraphs (f) and (g).
Paragraph E...............................  Paragraph (h).
Paragraph F...............................  Paragraph (n).
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Explanation of Change to Applicability

    We have changed the airplane model designations in the 
applicability of this proposed AD to be consistent with the parallel 
French airworthiness directive.

Explanation of Change Made to Existing Requirements

    Where the service bulletin specifies to ``visually inspect,'' 
except for the inspection for missing or damaged sealant, and where AD 
90-03-08 specifies to do a ``visual inspection,'' we specify to do a 
``detailed inspection'' in this proposed AD. We have included the 
definition for a detailed inspection in Note 1 of this proposed AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD.

                                                                     Estimated Costs
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                                                                                           Number of
                                                      Average                                U.S.-
                Action                  Work hours   labor rate     Cost per airplane      registered                      Fleet cost
                                                      per hour                             airplanes
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Inspections (required by AD 90-03-08)           10          $80  $800, per inspection              51  $40,800, per inspection cycle.
                                                                  cycle.
New Inspections (required by this AD)           10           80  800, per inspection               51  $40,800, per inspection cycle.
                                                                  cycle.
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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 39-6481 (55 FR 1799, January 19, 1990) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-25423; Directorate Identifier 2006-NM-
029-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by August 
31, 2006.

Affected ADs

    (b) This AD supersedes AD 90-03-08.

Applicability

    (c) This AD applies to all Airbus Model A300 airplanes, 
certificated in any category; except the following airplanes:
    (1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes;
    (2) Model A300 B4-605R and B4-622R airplanes;
    (3) Model A300 F4-605R and F4-622R airplanes; and
    (4) Airbus Model A300 C4-605R Variant F airplanes.

Unsafe Condition

    (d) This AD results from reports of corrosion and cracking in 
the various components associated with the rear pressure bulkhead. 
We are issuing this AD to prevent reduced structural capability of 
the fuselage and consequent decompression of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Certain Requirements of AD 90-03-08 With New Repetitive 
Intervals

Initial Inspections

    (f) Within the time limits specified in paragraph (g) of this 
AD, conduct the inspections specified in paragraphs (f)(1) through 
(f)(4) of this AD in accordance with Airbus Service Bulletin

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A300-53-218, Revision 1, dated July 28, 1989; or Airbus Service 
Bulletin A300-53-0218, Revision 02, dated May 10, 2005. After the 
effective date of this AD, Airbus Service Bulletin A300-53-0218, 
Revision 02, dated May 10, 2005, must be used.
    (1) Perform a detailed inspection for corrosion and cracking of 
the upper rim area of the rear pressure bulkhead from the aft face.

    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.''

    (2) Perform an eddy current inspection for cracks from the 
outboard side in the applicable areas specified in paragraph 
(f)(2)(i) or (f)(2)(ii) of this AD.
    (i) For airplanes, manufacturer's serial number (MSN) 003 
through 008: Between Stringer (STGR) 25 left hand (LH) and right 
hand (RH).
    (ii) For airplanes, MSN 019 through 305: Between STGR 26 LH and 
RH.
    (3) Perform a detailed inspection for cracks and corrosion of 
the service apertures in the rear pressure bulkhead.
    (4) Perform an eddy current inspection for cracks of the 
apertures for the auxiliary power unit (APU) bleed-air and fuel.
    (g) At the applicable time specified in paragraph (g)(1) or 
(g)(2) of this AD, do the inspections required by paragraph (f) of 
this AD.
    (1) For airplanes having accumulated 26,000 landings or fewer as 
of February 23, 1990 (the effective date of AD 90-03-08): Perform 
the initial inspections required by paragraph (f) of this AD, prior 
to the accumulation of 24,000 landings or within 2,000 landings 
after February 23, 1990, whichever occurs later.
    (2) For airplanes having accumulated more than 26,000 landings 
as of February 23, 1990: Perform the initial inspections required by 
paragraph (f) of this AD, within 1,000 landings after February 23, 
1990.

Repetitive Inspections

    (h) If no cracking or corrosion is found during the inspections 
required by paragraph (f) of this AD, repeat the inspections 
specified in paragraphs (h)(1), (h)(2), (h)(3), (h)(4), and (h)(5) 
of this AD thereafter at the times specified in the paragraphs.
    (1) Repeat the detailed inspections of the upper rim area 
specified in paragraph (f)(1) of this AD thereafter at intervals not 
to exceed 8,000 landings.
    (2) Repeat the eddy current inspection from the outboard side 
between STGR 25 LH and RH, or STGR 26 LH and RH, as applicable, 
specified in paragraph (f)(2) of this AD thereafter at intervals not 
to exceed 8,000 landings.
    (3) Repeat the detailed inspection of the service apertures 
specified in paragraph (f)(3) of this AD thereafter at intervals not 
to exceed 6,000 landings.
    (4) Repeat eddy current inspections of APU fuel apertures 
specified in paragraph (f)(4) of this AD thereafter at intervals not 
to exceed 6,000 landings.
    (5) At the earlier of the times specified in paragraph (g)(5)(i) 
and (g)(5)(ii) of this AD, do the eddy current inspection of the APU 
bleed-air line service aperture specified in paragraph (f)(4) of 
this AD. Repeat the inspection thereafter at intervals not to exceed 
6,000 landing.
    (i) Within 12,000 landings since the last inspection of the APU 
bleed-air line service aperture specified in paragraph (f)(4) of 
this AD.
    (ii) Within 6,000 landings since the last inspection of the APU 
bleed-air line service aperture specified in paragraph (f)(4) of 
this AD or within 2,000 landings after the effective date of this 
AD, whichever occurs later.

New Requirements of This AD

Inspection for Sealant and Corrective Action

    (i) Within the time limits specified in paragraph (j) of this 
AD: Do a general visual inspection of the area between the outer 
attachment angle and circumferential joint doubler to determine if 
sealant is missing or damaged and do all applicable corrective 
actions in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-53-0218, Revision 02, dated May 10, 2005. Do 
all applicable corrective actions before further flight. Repeat the 
inspection thereafter at intervals not to exceed 6,000 landings.

    Note 2: 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.''

    (j) At the applicable time specified in paragraph (j)(1) or 
(j)(2) of this AD, do the inspections required by paragraph (i) of 
this AD.
    (1) For airplanes having accumulated 26,000 landings or fewer as 
of the effective date of this AD): Perform the initial inspection 
required by paragraph (i) of this AD, prior to the accumulation of 
24,000 landings or within 2,000 landings after the effective date of 
this AD, whichever occurs later.
    (2) For airplanes having accumulated more than 26,000 landings 
as of the effective date of this AD: Perform the initial inspection 
required by paragraph (i) of this AD, within 1,000 landings after 
the effective date of this AD.

Additional Inspections

    (k) For airplanes on which the inspections specified in 
paragraphs (f)(2), (f)(4), (h)(2), and (h)(4) of this AD are 
accomplished after the effective date of this AD: Where this AD 
requires an eddy current inspection for cracks, do a detailed 
inspection for corrosion at the same time as the eddy current 
inspection for cracks in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-0218, Revision 02, 
dated May 10, 2005.
    (l) For airplanes on which the inspections specified in 
paragraphs (f)(2) and (h)(2) of this AD are accomplished after the 
effective date of this AD: If any crack is found during any 
inspection required by paragraph (f)(2) or (h)(2), before further 
flight, do an X-ray inspection for cracking of the rim area of the 
rear pressure bulkhead in the area of STGR 21 LH and RH in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-0218, Revision 02, dated May 10, 2005.

New Repetitive Inspections

    (m) For airplanes on which a repair has been done in accordance 
with Airbus Service Bulletin A300-53-218, Revision 1, dated July 28, 
1989; or Airbus Service Bulletin A300-53-0218, Revision 02, dated 
May 10, 2005; before the effective date of this AD: At the later of 
the times specified in paragraphs (m)(1) and (m)(2) of this AD, do 
the inspections specified in paragraphs (h), (k), and (l) of this 
AD. Repeat the inspections specified in paragraphs (h), (k), and (l) 
of this AD thereafter at the applicable times specified in paragraph 
(h).
    (1) Within the times specified in paragraph (h) of this AD.
    (2) Within 2,000 landings after the effective date of this AD.

[[Page 43390]]

Corrective Actions for Cracking and Corrosion and Repetitive 
Inspections

    (n) If cracking or corrosion is found during any inspection 
required by paragraph (f), (h), (k), (l) or (m) of this AD, repair 
prior to further flight, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-218, Revision 1, 
dated July 28, 1989; or Airbus Service Bulletin A300-53-0218, 
Revision 02, dated May 10, 2005. As of the effective date of this 
AD, do the repair in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-0218, Revision 02, dated May 10, 
2005; except where the service bulletin specifies to contact the 
manufacturer to repair certain conditions, this AD requires 
repairing those conditions using a method approved by either the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or 
its delegated agent). As of the effective date of this AD, repeat 
the inspections specified in paragraphs (h), (k), and (l) of this AD 
thereafter at the applicable times specified in paragraph (h).

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, International Branch, ANM-116, 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.
    (3) AMOCs approved previously in accordance with AD 90-03-08 are 
not approved as AMOCs with this AD.

Related Information

    French airworthiness directive F-2005-093 R1, dated August 3, 
2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on July 21, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-12301 Filed 7-31-06; 8:45 am]
BILLING CODE 4910-13-P