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

[Federal Register Volume 73, Number 11 (Wednesday, January 16, 2008)]
[Rules and Regulations]
[Pages 2803-2807]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-25503]


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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; 
Amendment 39-15316; AD 2007-26-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 Airplanes; and 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: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Airbus Model A300 B2 and B4 series 
airplanes; and all Model A300 B4-600, B4-600R, and F4-600R 
(collectively called A300-600) series airplanes. That AD currently 
requires repetitive inspections to detect cracking of the upper radius 
of the forward fitting of frame 47, and repair if necessary. This new 
AD retains those requirements, but reduces inspection thresholds and 
repetitive intervals, and adds related investigative and corrective 
actions. This AD also provides an optional terminating action for the 
repetitive inspections only for airplanes with cracking that is within 
certain limits, and a post-repair inspection program following the 
optional terminating action. This AD results from reports of additional 
cracking in airplanes that were inspected in accordance with the 
existing AD. 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.

DATES: This AD becomes effective February 20, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of February 20, 
2008.
    On May 1, 2003 (68 FR 14894, March 27, 2003), the Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the AD.

ADDRESSES: For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Thomas Stafford, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2003-06-04, amendment 
39-13091 (68 FR 14894, March 27, 2003). The existing AD applies to all 
Airbus Model A300 B2 and B4 series airplanes; and all Model A300 B4-
600, B4-600R, and F4-600R (collectively called A300-600) series 
airplanes. That NPRM was published in the Federal Register on April 20, 
2007 (72 FR 19818). That NPRM proposed to continue to require 
repetitive inspections to detect cracking of the upper radius of the 
forward fitting of frame 47, and repair if necessary. That NPRM also 
proposed to reduce

[[Page 2804]]

inspection thresholds and repetitive intervals, and to add related 
investigative and corrective actions. That NPRM also proposed to 
provide an optional terminating action for the repetitive inspections 
only for airplanes with cracking that is within certain limits.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Clarify Requirements of Paragraph (l) of the NPRM

    Air Transport Association (ATA), on behalf of its member American 
Airlines (AA), and supported by Airbus, points out that paragraph 
(l)(2) of the NPRM specifies performing repetitive inspections on 
airplanes with cracks ``30 millimeters (mm) (1.181 inch) or less in 
length.'' AA believes that the length should be 50 mm. AA explains that 
Table 2 (Figure 1, Sheet 1) of Airbus Service Bulletin A300-53-6029, 
Revision 08, dated October 19, 2005 (for Model A300-600 series 
airplanes), allows repetitive inspections for cracks equal to or less 
than 50 mm. AA also points out that the table titled ``Related 
Investigative and Corrective Actions Following Eddy Current 
Inspection'' in the ``Relevant Service Information'' section of the 
NPRM states that repetitive inspections are applicable for cracks equal 
to or less than 50 mm in size.
    We agree that paragraph (l)(2) of the NPRM needs to be clarified. 
Therefore, we have revised paragraph (l)(2) of the AD to clarify the 
crack size that applies to each model.

Request To Apply Certain Actions Only to Airplanes With Known Cracks

    ATA, on behalf of its member AA, states that paragraph (m), 
``Abnormal Load Events,'' of the NPRM should apply only to airplanes 
with known cracks. Airbus supports this statement. AA explains that 
Figure 1, Sheet 1, of Airbus Service Bulletin A300-53-6029, Revision 
08, requires the inspections only if a crack exists. AA also points out 
that the table titled ``Related Investigative and Corrective Actions 
Following Eddy Current Inspection'' in the ``Relevant Service 
Information'' section of the NPRM states that the inspection is for an 
``abnormal load event on an airplane with any crack finding.''
    We agree with the commenters for the reasons stated by the 
commenters. Paragraph (m) of the AD should apply only to airplanes with 
known cracks. We have revised paragraph (m) of this AD to state that it 
applies only to airplanes on which any crack was found during any 
inspection required by this AD.

Request To Refer to Latest Revision of Service Bulletin

    Airbus states that Airbus Service Bulletin A300-53-6144, dated July 
16, 2004, which we referred to in the NPRM as the appropriate source of 
service information for accomplishing the optional terminating action, 
has now been revised. Airbus requests that we refer to Airbus Service 
Bulletin A300-53-6144, Revision 01, dated October 15, 2007.
    We agree with the request to refer to Revision 01 of Airbus Service 
Bulletin A300-53-6144. The procedures in Revision 01 and the original 
issue are essentially the same. Revision 01 revises the effectivity of 
the service bulletin, but states that no additional work is required 
for airplanes modified in accordance with the previous issue. We have 
revised paragraph (n) of this AD to refer to Revision 01 of the service 
bulletin. We have also revised paragraph (r) of this AD to give credit 
to operators that have accomplished the actions in accordance with the 
previous issue of the service bulletin.

Request To Revise Contact Information

    Airbus requests that we revise the address for submitting reports 
of inspection findings in paragraph (q) of the NPRM. We have revised 
paragraph (q) of the AD to include the information provided by Airbus.

Explanation of Clarifications

    We have clarified paragraph (m) of the AD by replacing the ``or'' 
with an ``and'' in the statement ``Do the actions in paragraph (m)(1), 
(m)(2), or (m)(3), as applicable * * *'' An ``and'' in this case more 
clearly conveys the intent of the paragraph because it is possible that 
operators might need to do more than one of those actions.
    We have also revised paragraph (s)(2) of the AD to clarify the 
appropriate procedure for notifying the principal inspector before 
using any approved AMOC on any airplane to which the AMOC applies.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 163 U.S.-registered airplanes that are affected by 
this AD. The following table provides the estimated costs for U.S. 
operators to comply with this 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 cycle...................  $117,360, per inspection cycle.
Inspection (new action)..............          1         $0  $80, per inspection cycle....................  $13,040, per inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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

[[Page 2805]]

products identified in this rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13091 (68 FR 14894, March 27, 2003) and by adding 
the following new airworthiness directive (AD):

2007-26-14 Airbus: Amendment 39-15316. Docket No. FAA-2007-27926; 
Directorate Identifier 2006-NM-050-AD.

Effective Date

    (a) This AD becomes effective February 20, 2008.

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, including Appendix 01, 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, Transport Airplane Directorate, FAA; 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 A300-53-6029, Revision 05, including Appendix 01, 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, 
including Appendix 01, 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 required 
by paragraph (j) of this AD is done.
    (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 required 
by 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.

[[Page 2806]]

    (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 required 
by 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 the size specified 
in paragraph (l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD: Do 
the next inspection at the applicable times specified in paragraph 
(l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD, as applicable.
    (i) For Airbus Model A300 airplanes on which the crack is 30 
millimeters (mm) (1.181 inch) or less in length: 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) For Airbus Model A300 airplanes on which the crack is 
greater than 30 millimeters (mm) (1.181 inch) in length, but less 
than or equal to 50 mm in length (1.97 inch): At the next repetitive 
interval specified in paragraph (l) of this AD (Figure 1, Sheet 1, 
of the Accomplishment Instructions of the applicable service 
bulletin).
    (iii) 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 on 
which the crack is 50 mm (1.97 inch) or less in length: At the next 
repetitive interval specified in the service bulletin specified in 
paragraph (j)(2) of this AD; without, however, exceeding the 
previous inspection interval specified in paragraph (g) of this AD.

Abnormal Load Events

    (m) For airplanes on which any crack was found during any 
inspection required by this AD and on which any abnormal load event 
occurs after the effective date of this AD: Do the actions in 
paragraphs (m)(1), (m)(2), and (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, Revision 01, including Appendix 01, dated July October 15, 
2007; 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: Davide Cavazzini, 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), (j), and (n) of this AD.

[[Page 2807]]



                                 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-      A300-53-6029  05...........................  April 11, 2001.
 622, B4-605R, 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.
                                      A300-53-6144  Original.....................  July 16, 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) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (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.

Material Incorporated by Reference

    (u) You must use the service information listed in Table 2 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise.

                                Table 2.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
        Airbus Service Bulletin                     Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A300-53-0246, including Appendix 01....  03.................................  April 11, 2001.
A300-53-0246, including Appendix 01....  06.................................  October 19, 2005.
A300-53-0370, including Appendix 01....  Original...........................  July 16, 2004.
A300-53-6029...........................  02.................................  November 7, 1994.
A300-53-6029, including Appendix 01....  05.................................  April 11, 2001.
A300-53-6029, including Appendix 01....  08.................................  October 19, 2005.
A300-53-6144, including Appendix 01....  Original...........................  July 16, 2004.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the documents listed in Table 3 of 
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

                                Table 3.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
        Airbus Service Bulletin                     Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A300-53-0246, including Appendix 01....  06.................................  October 19, 2005.
A300-53-0370, including Appendix 01....  Original...........................  July 16, 2004.
A300-53-6029, including Appendix 01....  08.................................  October 19, 2005.
A300-53-6144, including Appendix 01....  Original...........................  July 16, 2004.
----------------------------------------------------------------------------------------------------------------

    (2) On May 1, 2003 (68 FR 14894, March 27, 2003), the Director 
of the Federal Register approved the incorporation by reference of 
the documents listed in Table 4 of this AD.

                           Table 4.--Material Incorporated by Reference in Previous AD
----------------------------------------------------------------------------------------------------------------
        Airbus Service Bulletin                     Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A300-53-0246, including Appendix 01....  03.................................  April 11, 2001.
A300-53-6029, including Appendix 01....  05.................................  April 11, 2001.
----------------------------------------------------------------------------------------------------------------

    (3) On October 16, 1996 (61 FR 47808, September 11, 1996), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus Service Bulletin A300-53-6029, Revision 02, 
dated November 7, 1994.
    (4) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 19, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-25503 Filed 1-15-08; 8:45 am]
BILLING CODE 4910-13-P

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