[Federal Register Volume 72, Number 76 (Friday, April 20, 2007)]
[Proposed Rules]
[Pages 19818-19823]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-7516]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27926; Directorate Identifier 2006-NM-050-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 Airplanes; and Airbus 
Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-
605R Variant F Airplanes (Collectively Called A300-600 Series 
Airplanes)

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Airbus Model A300 B2 and B4 series 
airplanes; and Model A300 B4-600, B4-600R, and F4-600R (collectively 
called A300-600) series airplanes. The existing AD currently requires 
repetitive inspections to detect cracking of the upper radius of the 
forward fitting of frame 47, and repair if necessary. This proposed AD 
would reduce inspection thresholds and repetitive intervals, and add 
related investigative and corrective actions. This proposed AD also 
would provide an optional terminating action for the repetitive 
inspections only for airplanes with cracking that is within certain 
limits. This proposed AD results from reports of additional cracking in 
airplanes that were inspected in accordance with the existing AD. We 
are proposing this AD to detect and correct fatigue cracking of the 
left and right upper radius at frame 47, which could propagate and 
result in reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by May 21, 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: Thomas Stafford, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; 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-2007-27926; Directorate Identifier 2006-NM-050-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 March 18, 2003, we issued AD 2003-06-04, amendment 39-13091 (68 
FR 14894, March 27, 2003), for all Airbus Model A300 B2 and B4 series 
airplanes, and Model A300 B4-600, B4-600R, and F4-600R (collectively 
called A300-600) series airplanes. That AD requires repetitive 
inspections to detect cracking of the upper radius of the forward 
fitting of frame 47, and repair if necessary. That AD resulted from 
issuance of mandatory continuing airworthiness information by a civil 
airworthiness authority. We issued that AD to detect and correct such 
fatigue cracking, which could result in propagation of the cracking to 
the rear fitting and reduced structural integrity of fuselage frame 47.

Actions Since Existing AD Was Issued

    Since we issued AD 2003-06-04, cracks were found on the left and 
right upper radius at frame 47 at 48,000 simulated flights, and at 
18,000 total flights on an in-service airplane. In-service experience 
up to 2001 showed there was no propagation of cracking between 30 
millimeters (mm) and 40 mm in size. In mid-2001, a crack of 110 mm in 
size was found on a scrapped Model A300 B4-200 airplane with 23,700 
total flights. Further sampling inspections revealed two Model A300 
airplanes with cracks greater in size than the defined limit of 50 mm. 
Based on these last investigation results, Airbus established a revised 
inspection program that:
     Redefines the threshold and repetitive interval values; 
and
     Introduces corrective measures in the event of abnormal 
load events (e.g., hard landing and flight with turbulence). 
Definitions of abnormal load events are in the applicable airplane 
maintenance manual.

Relevant Service Information

    Airbus has issued the service bulletins described in the following 
table.

[[Page 19819]]



                        Airbus Service Bulletins
------------------------------------------------------------------------
                                 For model A300      For model A300-600
    Service bulletin type           airplanes         series airplanes
------------------------------------------------------------------------
Inspection service bulletins  A300-53-0246,         A300-53-6029,
                               Revision 06,          Revision 08,
                               including Appendix    including Appendix
                               01, dated October     01, dated October
                               19, 2005.             19, 2005.
Optional terminating service  A300-53-0370,         A300-53-6144,
 bulletins.                    including Appendix    including Appendix
                               01, dated July 16,    01, dated July 16,
                               2004.                 2004.
------------------------------------------------------------------------

    The inspection service bulletins are newer revisions of the service 
bulletins that were referenced as the appropriate sources of service 
information for accomplishing the actions required by AD 2003-06-04. 
The newer revisions take into account the latest investigation results 
from Airbus, described above, and establish a revised inspection 
program. The inspection service bulletins specify reporting all 
inspection results to Airbus.
    The inspection service bulletins describe procedures for repetitive 
eddy current inspections to detect cracking of the upper radius of the 
forward fitting of frame 47, and applicable related investigative and 
corrective actions, as described in the following table.

   Related Investigative and Corrective Actions Following Eddy Current
                               Inspection
------------------------------------------------------------------------
                                                           Related
    Finding or occurrence       Corrective action   investigative action
------------------------------------------------------------------------
No crack....................  Modify the fairing    Eddy current
                               attachment profile    inspection for
                               by cutting and        cracking of the
                               removing the          upper radius (after
                               fairing attachment    the keel beam has
                               profile between       been trimmed and
                               frame 47 and frame    while the
                               48, and trimming      attachment profile
                               the keel beam at      is removed).
                               frame 47. This
                               action is specified
                               only after the
                               first eddy current
                               inspection.
More than one crack.........  Contact Airbus for    Detailed visual
                               repair instructions.  inspection for
                                                     cracking of the aft
                                                     fitting around the
                                                     fasteners.
Crack less than or equal to   Do the repetitive     None.
 8 mm in size.                 eddy current
                               inspection at a
                               reduced interval.
Crack greater than 8 mm in    Remove, modify, and   Ultrasonic
 size, but less than or        reinstall the         inspection for
 equal to 20 mm in size.       sealing fitting and   cracking of the
                               sealing shim. This    forward fitting.
                               action is specified
                               only after the
                               first eddy current
                               inspection with a
                               crack finding of
                               this size. Do the
                               repetitive eddy
                               current inspection
                               at a reduced
                               interval.
Crack greater than 20 mm in   Contact Airbus for    Detailed visual
 size, but less than or        repair instructions   inspection for
 equal to 50 mm in size.       if any crack is       cracking of the aft
                               found during the      fitting around the
                               detailed visual       fasteners.
                               inspection; if no
                               further cracking is
                               found, do the
                               repetitive eddy
                               current inspection
                               at a reduced
                               interval.
Crack greater than 50 mm in   Repair in accordance  None.
 size.                         with the optional
                               terminating service
                               bulletins and
                               contact Airbus for
                               repair instructions.
Abnormal load event on an     Report the event to   None.
 airplane with any crack       Airbus and do the
 finding.                      next repetitive
                               eddy current
                               inspection within 3
                               months after the
                               event; or, if the
                               first eddy current
                               inspection has not
                               yet been done,
                               contact Airbus
                               before further
                               flight.
------------------------------------------------------------------------

    As noted in the table above, the repetitive intervals for the 
special detailed inspection vary according to the crack finding. The 
following table is a summary of the repetitive intervals given in 
Figure 1, Sheet 1, of the inspection service bulletins.

               Repetitive Intervals Based on Crack Finding
------------------------------------------------------------------------
               Finding                        Repetitive interval
------------------------------------------------------------------------
No crack............................  4,150 flight cycles.
Crack less than or equal to 30 mm...  1,400 flight cycles.
Crack greater than 30 mm but less     750 flight cycles.
 than or equal to 40 mm.
Crack greater than 40 mm but less     250 flight cycles.
 than or equal to 50 mm.
------------------------------------------------------------------------

    The optional terminating service bulletins apply only if a crack is 
greater than 30 mm but less than or equal to 50 mm in size. The 
optional terminating service bulletins specify contacting Airbus for 
repair instructions, special tooling, and the use of trained personnel 
for accomplishing the repair because of the high risk of serious damage 
to the frame 47 forward fitting, which could lead to a repair beyond 
the economical limit.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe

[[Page 19820]]

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-2006-
016, dated January 18, 2006, 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 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 2003-06-04, and would continue 
to require repetitive inspections to detect cracking of the upper 
radius of the forward fitting of frame 47, and repair if necessary. 
This proposed AD would also continue to require the report to Airbus 
that was required by the existing AD.
    This proposed AD would reduce inspection thresholds and repetitive 
intervals, and add related investigative and corrective actions. This 
proposed AD also would provide an optional terminating action for the 
repetitive inspections only for airplanes with cracking that is within 
certain limits. This proposed AD would require accomplishing the 
actions specified in the service information described previously, 
except as discussed under ``Differences Among the Proposed AD, the 
Service Information, and the French Airworthiness Directive.''

Differences Among the Proposed AD, the Service Information, and the 
French Airworthiness Directive

    The inspection service bulletins referenced by the French 
airworthiness directive specify contacting Airbus for certain 
instructions. This proposed AD would require doing those actions 
according to a method that we or the European Aviation Safety Agency 
(EASA) (or its delegated agent) approve. In light of the actions 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 method we or the EASA approve would be 
acceptable for compliance with this proposed AD.
    The French airworthiness directive does not specify repair 
instructions for crack findings of greater than 50 mm, and the 
inspection service bulletins specify doing actions in the optional 
terminating service bulletins and contacting Airbus for repair 
instructions. This proposed AD would instead require repairing those 
conditions using a method that we approve.
    Where the optional terminating service bulletins specify sending a 
geometrical plan to Airbus after doing the repair, this proposed AD 
would require providing a post-repair inspection program to us for 
approval within 6 months after doing the repair.
    These differences have been coordinated with EASA.

Flight With Cracking

    Operators should note that this proposed AD permits further flight 
with cracking within certain limits. While it is not the FAA's policy 
to allow flight with known cracking, we have determined that, for the 
purposes of this proposed AD, repair may be deferred for certain crack 
lengths. In making this determination, we considered that long-term 
continued operational safety in this case will be adequately ensured by 
repetitive inspections to detect cracking before it represents a hazard 
to the airplane, and by repair if the crack exceeds the specified 
limit.
    We also considered that cracks that are less than 30 mm in size are 
not physically accessible and would require removing frame 47 to 
repair, which is not economically viable. The proposed inspection 
program will mitigate any safety concerns for cracks of this size.
    Cracks of 30 mm to 50 mm in size are also acceptable for flight, 
but this proposed AD would require a more rigorous inspection program 
for cracks of this size. If operators strictly observe the crack size 
limits and perform repetitive inspections at required intervals, 
operators can detect any cracks that grow beyond the limits and take 
corrective action before the crack size creates an unacceptable risk of 
structural failure.
    The DGAC concurs with these findings. In consideration of these 
findings and the FAA's criteria for flight with known cracking, further 
flight with cracking within certain limits is permissible for an 
interim period in this case.

Changes to Existing AD

    This proposed AD would retain certain requirements of AD 2003-06-
04. Since AD 2003-06-04 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                              Corresponding  requirement
        Requirement in AD 2003-06-04             in this  proposed AD
------------------------------------------------------------------------
Paragraph (a)..............................  paragraph (f).
Paragraph (b)..............................  paragraph (g).
Paragraph (c)..............................  paragraph (h).
Paragraph (d)..............................  paragraph (i).
Paragraph (e)..............................  paragraph (q).
------------------------------------------------------------------------

    We have also clarified the applicability of the proposed AD in the 
following ways:
     To match more closely the applicability of the parallel 
French airworthiness directive.
     To identify model designations as published in the most 
recent type certificate data sheet for the affected models.
    We have revised this proposed AD to clarify the appropriate 
procedure for notifying the principal inspector before using any 
approved alternative method of compliance (AMOC) on any airplane to 
which the AMOC applies.

Costs of Compliance

    There are about 163 U.S.-registered airplanes that would be 
affected by this proposed AD. 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.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                           Work
                Action                    hours      Parts        Cost per airplane            Fleet cost
----------------------------------------------------------------------------------------------------------------
Actions required by AD 2003-06-04.....          9         $0  $720, per inspection      $117,360, per inspection
                                                               cycle.                    cycle.
Inspection (new proposed action)......          1          0  $80, per inspection       $13,040, per inspection
                                                               cycle.                    cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 19821]]

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 39-13091 (68 FR 14894, March 27, 2003) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-27926; Directorate Identifier 2006-NM-
050-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by May 21, 
2007.

Affected ADs

    (b) This AD supersedes AD 2003-06-04.

Applicability

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

Unsafe Condition

    (d) This AD results from reports of additional cracking in 
airplanes that were inspected in accordance with AD 2003-06-04. We 
are issuing this AD to detect and correct fatigue cracking of the 
left and right upper radius at frame 47, which could propagate and 
result in reduced structural integrity 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.

Requirements of AD 2003-06-04

Model A300-600: Inspection

    (f) For Model A300-600 series airplanes: At the earlier of the 
times specified by paragraphs (f)(1) and (f)(2) of this AD, perform 
an eddy current inspection to detect cracking of the upper radius of 
the left and right forward fitting of frame 47, in accordance with 
Airbus Service Bulletin A300-53-6029, Revision 02, dated November 7, 
1994; Revision 05, dated April 11, 2001; or Revision 08, including 
Appendix 01, dated October 19, 2005. After the effective date of 
this AD, only Revision 08 of the service bulletin may be used.
    (1) Before the accumulation of 17,300 total flight cycles, or 
within one year after October 16, 1996 (the effective date of AD 96-
18-18, amendment 39-9744), whichever occurs later.
    (2) At the later of the times specified by paragraphs (f)(2)(i) 
and (f)(2)(ii) of this AD.
    (i) Before the accumulation of 10,000 total flight cycles or 
26,000 total flight hours, whichever occurs first.
    (ii) Within 750 flight cycles or 1,900 flight hours, whichever 
occurs first after May 1, 2003 (the effective date of AD 2003-06-
04).

Model A300-600: Follow-On (Repetitive) Inspections

    (g) For Model A300-600 series airplanes on which no cracking is 
found during any inspection required by paragraph (f) of this AD, 
repeat the inspection required by paragraph (f) of this AD at the 
applicable times specified in paragraphs (g)(1) and (g)(2) of this 
AD until the inspection required by paragraph (j) of this AD is 
done.
    (1) If the initial inspection was accomplished before May 1, 
2003, repeat the inspection at the later of the times specified in 
paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. Thereafter, repeat 
the inspection at intervals not to exceed 6,100 flight cycles or 
15,600 flight hours, whichever occurs first.
    (i) Re-inspect within 6,100 flight cycles after the initial 
inspection.
    (ii) Re-inspect within 750 flight cycles or 1,900 flight hours, 
whichever occurs first after May 1, 2003.
    (2) If the initial inspection was not accomplished before May 1, 
2003, repeat the inspection thereafter at intervals not to exceed 
6,100 flight cycles or 15,600 flight hours, whichever occurs first.

Model A300-600: Corrective Action

    (h) For Model A300-600 series airplanes on which any cracking is 
found during any inspection required by paragraph (f) of this AD: 
Before further flight, contact 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 
representative), or the European Aviation Safety Agency (EASA) (or 
its delegated agent); for instructions regarding repair or for an 
applicable re-inspection interval, in accordance with Airbus Service 
Bulletin A300-52-6029, Revision 05, dated April 11, 2001; or 
Revision 08, including Appendix 01, dated October 19, 2005. After 
the effective date of this AD, only Revision 08 may be used. Repair 
and/or re-inspection accomplished before May 1, 2003, in accordance 
with a method approved by the Manager, International Branch, ANM-
116, is acceptable for compliance with the requirements of paragraph 
(h) of this AD.

Model A300 B2 and B4: Repetitive Inspections and Follow-On Actions

    (i) For Model A300 B2 and B4 series airplanes: At the applicable 
time specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, 
perform repetitive eddy current inspections to detect cracking of 
the upper radius of the forward fitting of frame 47, left and right 
sides, per Airbus Service Bulletin A300-53-0246, Revision 03, dated 
April 11, 2001; or Revision 06, including Appendix 01, dated October 
19, 2005. After the effective date of this AD, only Revision 06 may 
be used. Accomplishing this requirement terminates the corresponding 
inspection requirement of the A300 Supplemental Structural 
Inspection Document (SSID) for Model A300 B2 and B4 series 
airplanes. (That SSID is mandated by AD 96-13-11, amendment 39-
9679.)
    (1) For Model A300 B2 series airplanes: Perform the initial 
inspection at the later of the times specified by paragraphs 
(i)(1)(i) and (i)(1)(ii) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 10,400 flight cycles or 13,300 
flight hours, whichever occurs first, until the inspection in 
paragraph (j) of this AD is done.

[[Page 19822]]

    (i) Before the accumulation of 16,500 total flight cycles or 
21,000 total flight hours, whichever occurs first.
    (ii) Within 1,000 flight cycles or 1,300 flight hours after May 
1, 2003, whichever occurs first.
    (2) For Model A300 B4-100 series airplanes: Perform the initial 
inspection at the later of the times specified by paragraphs 
(i)(2)(i) and (i)(2)(ii) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 8,500 flight cycles or 16,400 
flight hours, whichever occurs first, until the inspection in 
paragraph (j) of this AD is done.
    (i) Before the accumulation of 10,300 total flight cycles or 
19,800 total flight hours, whichever occurs first.
    (ii) Within 750 flight cycles or 1,500 flight hours after May 1, 
2003, whichever occurs first.
    (3) For Model A300 B4-200 series airplanes: Perform the initial 
inspection at the later of the times specified by paragraphs 
(i)(3)(i) and (i)(3)(ii) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 7,000 flight cycles or 13,600 
flight hours, whichever occurs first, until the inspection in 
paragraph (j) of this AD is done.
    (i) Before the accumulation of 11,000 total flight cycles or 
21,200 total flight hours, whichever occurs first.
    (ii) Within 750 flight cycles or 1,500 flight hours after May 1, 
2003, whichever occurs first.

New Requirements of This AD

Inspections and Corrective Actions

    (j) At the applicable time in paragraph (k) or (l) of this AD: 
Except as provided by paragraphs (n) and (p) of this AD, do an eddy 
current inspection to detect cracking of the upper radius of the 
forward fitting of frame 47, and do all applicable related 
investigative and corrective actions, by accomplishing all the 
applicable actions specified in the Accomplishment Instructions of 
the applicable service bulletin specified in paragraph (j)(1) or 
(j)(2) of this AD. Do all applicable investigative and corrective 
actions before further flight. Where the service bulletins specify 
to contact Airbus for repair instructions: Before further flight, 
repair using a method approved by either the Manager, International 
Branch, ANM-116; or the EASA (or its delegated agent). Doing the 
inspections required by this paragraph terminates the inspections 
required by paragraphs (f), (g), and (i) of this AD.
    (1) For Airbus Model A300 airplanes: Airbus Service Bulletin 
A300-53-0246, Revision 06, including Appendix 01, dated October 19, 
2005.
    (2) For Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: 
Airbus Service Bulletin A300-53-6029, Revision 08, including 
Appendix 01, dated October 19, 2005.
    (k) For airplanes on which the inspection required by paragraph 
(f), (g), or (i) of this AD, as applicable, has not been done prior 
to the effective date of this AD: Do the initial inspection required 
by paragraph (j) of this AD before the accumulation of 10,000 total 
flight cycles, or within 1,400 flight cycles after the effective 
date of this AD, whichever occurs later. Repeat the inspection 
thereafter at the applicable interval specified in Figure 1, Sheet 
1, of the Accomplishment Instructions of the applicable service 
bulletin.
    (l) For airplanes on which the inspection required by paragraph 
(f), (g), or (i) of this AD, as applicable, has been done prior to 
the effective date of this AD: Inspect at the applicable times 
specified in paragraph (l)(1) or (l)(2) of this AD. Repeat the 
inspection thereafter at the applicable interval specified in Figure 
1, Sheet 1, of the Accomplishment Instructions of the applicable 
service bulletin.
    (1) For airplanes on which no cracking was found during any 
inspection required by this AD: Do the next inspection at the 
earlier of the times specified in paragraphs (l)(1)(i) and 
(l)(1)(ii) of this AD.
    (i) At the next repetitive interval specified in the applicable 
service bulletin specified in paragraph (j)(1) or (j)(2) of this AD, 
or within 1,400 flight cycles after the effective date of this AD, 
whichever occurs later.
    (ii) At the next repetitive interval specified in paragraph (g) 
or (i) of this AD, as applicable.
    (2) For airplanes on which any crack was found during any 
inspection required by this AD, and the crack is 30 millimeters (mm) 
(1.181 inch) or less in length: Do the next inspection at the 
applicable times specified in paragraph (l)(2)(i) or (l)(2)(ii) of 
this AD.
    (i) For Airbus Model A300 airplanes: At the next repetitive 
interval specified in the service bulletin specified in paragraph 
(j)(1) of this AD, or within 500 flight cycles after the effective 
date of this AD, whichever occurs later.
    (ii) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: At the 
next repetitive interval specified in the service bulletin specified 
in paragraph (j)(2) of this AD.

Abnormal Load Events

    (m) For airplanes on which any abnormal load event occurs after 
the effective date of this AD, do the actions in paragraph (m)(1), 
(m)(2), or (m)(3) of this AD, as applicable, at the time specified 
in the applicable paragraph.
    (1) Within 3 months after the event, or at the next applicable 
repetitive interval required by paragraph (k) or (l) of this AD, 
whichever occurs first: Do the next repetitive inspection required 
by paragraph (j) of this AD.
    (2) Before further flight following any additional abnormal load 
event that occurs following the first event but before the next 
repetitive inspection required by paragraph (k) or (l) of this AD: 
Contact the Manager, International Branch, ANM-116, or the EASA (or 
its delegated agent) for further instructions.
    (3) Within 3 months after any abnormal load event: Report the 
event to Airbus in accordance with the requirements of paragraph (q) 
of this AD.

Optional Terminating Action (Repair) for Certain Cracks

    (n) Repairing any crack greater than 30 mm but less than or 
equal to 50 mm in size in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-0370, including 
Appendix 01, dated July 16, 2004; or Airbus Service Bulletin A300-
53-6144, including Appendix 01, dated July 16, 2004; as applicable; 
terminates the repetitive inspection requirements of paragraph (k) 
or (l) of this AD for that area only. Where the service bulletins 
specify to contact Airbus for repair instructions: Repair the crack 
using a method approved by either the Manager, International Branch, 
ANM-116; or the EASA (or its delegated agent).

Repetitive Inspections Following Optional Terminating Action

    (o) Within 6 months after repair in accordance with paragraph 
(n) of this AD: Submit a post-repair inspection program for 
monitoring the repair to the Manager, International Branch, ANM-116, 
for approval.

Repair of Any Crack Greater than 50 mm in Size

    (p) If any crack that is greater than 50 mm in size is found 
during any inspection required by paragraph (j), (k), or (l) of this 
AD: Before further flight, repair according to a method approved by 
the Manager, International Branch, ANM-116.

Reporting Requirement

    (q) At the applicable time specified in paragraph (q)(1) or 
(q)(2) of this AD: Submit a report of all results of each inspection 
required by this AD to Airbus, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France, Attention: Jacques Leborgne, fax 33-5-61-93-
36-14. The report must include the inspection results, a description 
of any discrepancies found, the airplane serial number, and the 
number of landings and flight hours on the airplane. Information 
collection requirements contained in this AD have been approved by 
the Office of Management and Budget (OMB) under the provisions of 
the Paperwork Reduction Act (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.
    (1) For airplanes on which the inspection is accomplished after 
the effective date of this AD: Submit the report within 30 days 
after performing the inspection.
    (2) For airplanes on which the inspection has been accomplished 
before the effective date of this AD: Submit the report within 30 
days after the effective date of this AD.

Actions Accomplished in Accordance With Previous Issues of Service 
Bulletins

    (r) Actions done before the effective date of this AD in 
accordance with the service bulletins listed in Table 1 of this AD 
are acceptable for compliance with the corresponding requirements of 
paragraphs (i) and (j) of this AD.

[[Page 19823]]



                                 Table 1.--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                               Airbus Service
                    Model                         Bulletin       Revision level                Date
----------------------------------------------------------------------------------------------------------------
A300 airplanes..............................      A300-53-0246                03  April 11, 2001.
                                                  A300-53-0246                04  November 12, 2002.
                                                  A300-53-0246                05  January 19, 2004.
A300 B4-601, B4-603, B4-620, B4-622, B4-          A300-53-6029                05  April 11, 2001.
 605R, B4-622R, F4-605R, F4-622R, and C4-
 605R Variant F airplanes.
                                                  A300-53-6029                06  November 12, 2002.
                                                  A300-53-6029                07  January 19, 2004.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (s)(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 2003-06-04 
are approved as AMOCs with this AD until paragraph (j) of this AD is 
accomplished.

Related Information

    (t) French airworthiness directive F-2006-016, dated January 18, 
2006, also addresses the subject of this AD.

    Issued in Renton, Washington, on April 12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-7516 Filed 4-19-07; 8:45 am]
BILLING CODE 4910-13-P