[Federal Register Volume 69, Number 77 (Wednesday, April 21, 2004)]
[Rules and Regulations]
[Pages 21397-21401]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-8540]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-111-AD; Amendment 39-13574; AD 2004-08-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 Series Airplanes; 
A300 B4 Series Airplanes; A300 B4-600, B4-600R, F4-600R, and C4-605R 
Variant F (Collectively Called A300-600) Series Airplanes; and A310 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A300 series airplanes, that 
currently requires either a one-time ultrasonic inspection, or 
repetitive visual inspections and eventual ultrasonic inspection, to 
detect cracking of the longitudinal skin splice above the mid-passenger 
door panels, and corrective actions if necessary. This amendment 
requires repetitive ultrasonic inspections to detect cracking of 
certain skin lap joints in additional areas of the fuselage and repair 
if necessary. This amendment also expands the applicability of the 
existing AD to include additional airplanes. The actions specified by 
this AD are intended to detect and correct cracking of certain skin lap 
joints, which could result in reduced structural integrity and 
decompression of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Effective May 26, 2004.
    The incorporation by reference of certain publications, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of May 26, 2004.
    The incorporation by reference of a certain other publication, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of February 22, 2000 (65 FR 5756, February 7, 
2000).

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Anthony Jopling, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2190; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-02-39, 
amendment 39-11557 (65 FR 5756, February 7, 2000), which is applicable 
to certain Airbus Model A300 series airplanes, was published in the 
Federal Register on December 18, 2003 (68 FR 70464). The action 
proposed to continue to require either a one-time ultrasonic 
inspection, or repetitive visual inspections and eventual ultrasonic 
inspection, to detect cracking of the longitudinal skin splice above 
the mid-passenger door panels, and corrective actions if necessary. The 
action also proposed to require repetitive ultrasonic inspections to 
detect cracking of certain skin lap joints in additional areas of the 
fuselage and repair if necessary. In addition, the action proposed to 
expand the applicability of the existing AD to include additional 
airplanes.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

[[Page 21398]]

Request To Reference Latest Service Information

    The commenter requests that the proposed AD be revised to reference 
Revision 03, dated February 25, 2003, of Airbus Service Bulletin A300-
53-6129 (for Model A300-600 series airplanes); and Revision 01, dated 
February 25, 2003, of Airbus Service Bulletin A310-53-2112 (for Model 
A310 series airplanes); for accomplishment of the applicable actions 
specified in the proposed AD. The commenter states that, because the 
repair kits have been identified with these latest revisions, adding 
them to the AD will eliminate requests for alternative methods of 
compliance in order to accomplish the latest kit installation.
    The FAA concurs with the commenter's request. We have reviewed 
Airbus Service Bulletin A300-53-6129, Revision 03, dated February 25, 
2003; and Airbus Service Bulletin A310-53-2112, Revision 01, dated 
February 25, 2003; and find them to be acceptable methods of compliance 
for accomplishment of the actions required by this AD. The final rule 
has been revised to require accomplishment of the applicable actions 
per either Revision 02 (which was referenced in the proposed AD as the 
applicable source of service information for the applicable actions) or 
Revision 03 of Airbus Service Bulletin A300-53-6129 (for Model A300-600 
series airplanes); or the original issue (which was referenced in the 
proposed AD as the applicable source of service information for the 
applicable actions) or Revision 01 of Airbus Service Bulletin A310-53-
2112 (for Model A310 series airplanes).

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 128 airplanes of U.S. registry that will be 
affected by this AD.
    The ultrasonic inspection that is currently required by AD 2000-02-
39 takes approximately 4 work hours per airplane to accomplish, at an 
average labor rate of $65 per work hour. Based on these figures, the 
cost impact of the currently required actions is estimated to be $260 
per airplane.
    The detailed inspection that is currently required by AD 2000-02-39 
takes approximately 2 work hours per airplane to accomplish, at an 
average labor rate of $65 per work hour. Based on these figures, the 
cost impact of the currently required actions is estimated to be $130 
per airplane.
    The ultrasonic inspection required in this AD action will take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $65 per work hour. Based on these figures, the cost 
impact of this inspection on U.S. operators is estimated to be $8,320, 
or $65 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by removing amendment 39-11557 (65 FR 5756, 
February 7, 2000), and by adding a new airworthiness directive (AD), 
amendment 39-13574, to read as follows:

2004-08-05 Airbus: Amendment 39-13574. Docket 2001-NM-111-AD. 
Supersedes AD 2000-02-39, Amendment 39-11557.

    Applicability: Model A300 B2 series airplanes; A300 B4 series 
airplanes; A300 B4-600, B4-600R, F4-600R, and C4-605R Variant F 
(collectively called A300-600) series airplanes; and A310 series 
airplanes; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracking of certain skin lap joints, which 
could result in reduced structural integrity and decompression of 
the airplane, accomplish the following:

Restatement of Certain Requirements of AD 2000-02-39

Ultrasonic or Detailed Visual Inspection

    (a) For Model A300 series airplanes having serial numbers (S/N) 
0003 through 0156 inclusive: Within 14 days after January 31, 2000 
(the effective date of AD 2000-02-39, amendment 39-11557), 
accomplish the requirements of either paragraph (a)(1) or (a)(2) of 
this AD, in accordance with Airbus All Operators Telex (AOT) A300-
53A0352, dated January 4, 2000.
    (1) Perform a one-time ultrasonic inspection to detect cracking 
of the longitudinal skin splice above the mid-passenger door panels 
below stringer 11 (left- and right-hand) and between frames 28A and 
30A.
    (i) If no cracking is detected: No further action is required by 
this paragraph.
    (ii) If any cracking is detected: Before further flight, 
accomplish the requirements of paragraph (b) of this AD.
    (2) Perform a detailed inspection to detect cracking of the 
longitudinal skin splice above the mid-passenger door panels below 
stringer 11 (left- and right-hand) and between frames 28A and 30A.

    Note 1: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good

[[Page 21399]]

lighting at intensity deemed appropriate by the inspector. 
Inspection aids such as mirrors, magnifying lenses, etc., may be 
used. Surface cleaning and elaborate access procedures may be 
required.''

    (i) If no cracking is detected: Accomplish the requirements of 
paragraphs (a)(2)(i)(A) and (a)(2)(i)(B) of this AD.
    (A) Repeat the detailed inspection thereafter at intervals not 
to exceed 80 flight cycles; and
    (B) Within 90 days after January 31, 2000: Accomplish the 
requirements of paragraph (a)(1) of this AD.
    (ii) If any cracking is detected: Before further flight, 
accomplish the requirements of paragraph (b) of this AD.

Corrective Actions

    (b) For airplanes on which any cracking is detected during any 
inspection required by paragraph (a)(1) or (a)(2) of this AD: Before 
further flight, install either a temporary or final repair, in 
accordance with Airbus AOT A300-53A0352, dated January 4, 2000.
    (1) If a temporary repair is installed: Prior to the 
accumulation of 2,000 flight cycles after the installation of the 
temporary repair, install the final repair.
    (2) If a final repair is installed: No further action is 
required by paragraphs (a) and (b) of this AD.

New Requirements of This AD

Inspections and Corrective Actions: Model A300 B2 and B4 Series 
Airplanes

    (c) For Model A300 B2 and A300 B4 series airplanes with S/Ns 
0003 through 0305 inclusive: From the airplane interior, do an 
ultrasonic inspection to detect cracking of the skin lap joint 
located above the mid-passenger door panel below stringer 11, 
between frames 28A and 31, on the left and right sides of the 
airplane, as applicable, per the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-0354, Revision 02, dated December 
13, 2001. Do the inspection at the times specified in paragraph 
(c)(1) or (c)(2) of this AD, as applicable. Accomplishment of this 
inspection terminates the repetitive inspections required by 
paragraph (a)(2)(i)(A) of this AD.
    (1) For airplanes with S/Ns 0003 through 0156 inclusive, except 
those airplanes on which the final repair in AOT A300-53A0352, dated 
January 4, 2000; or Airbus Service Bulletin A300-53-0354, Revision 
02, dated December 13, 2001, has been accomplished: Do the 
inspection within 2,500 flight cycles after the inspection per 
paragraph (a) of this AD, or within 14 days after the effective date 
of this AD, whichever occurs later. If no cracking is detected, 
repeat the inspection thereafter at intervals not to exceed 2,500 
flight cycles.
    (2) For airplanes with S/Ns 0157 through 0305 inclusive, except 
those airplanes on which the final repair in Airbus Service Bulletin 
A300-53-0354, Revision 02, dated December 13, 2001, has been 
accomplished: Do the initial inspection at the applicable time 
specified in paragraph (c)(2)(i) or (c)(2)(ii) of this AD. If no 
cracking is detected, repeat the inspection thereafter at intervals 
not to exceed 6,500 flight cycles.
    (i) For airplanes with less than 20,500 flight cycles as of the 
effective date of this AD: Inspect before the accumulation of 20,500 
total flight cycles or within 19 months after the effective date of 
this AD, whichever occurs later.
    (ii) For airplanes with 20,500 total flight cycles or more, but 
less than 26,500 total flight cycles as of the effective date of 
this AD: Inspect within 500 flight cycles after the effective date 
of this AD.
    (d) Accomplishment of the actions specified in Airbus Service 
Bulletin A300-53-0354, Revision 01, dated December 26, 2000, before 
the effective date of this AD, is considered acceptable for 
compliance with the requirements of paragraph (c) of this AD.
    (e) If any cracking is detected during any inspection per 
paragraph (c) of this AD: Do paragraphs (e)(1) and (e)(2) of this 
AD, as applicable.
    (1) If any crack is detected in Area A as defined in Figure 1 of 
Airbus Service Bulletin A300-53-0354, Revision 02, dated December 
13, 2001: Before further flight, repair per a method approved by 
either 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 agent).
    (2) If any crack is detected in Area B as defined in Figure 1 of 
Airbus Service Bulletin A300-53-0354, Revision 02, dated December 
13, 2001: Before further fight, do a temporary repair or final 
repair, as applicable, per the Accomplishment Instructions of the 
service bulletin.
    (f) For Model A300 B2 and A300 B4 series airplanes with S/Ns 
0003 through 0305 inclusive which have been repaired per paragraph 
(d)(2) of this AD: Do paragraph (f)(1) or (f)(2) of this AD, as 
applicable.
    (1) If a temporary repair has been accomplished: Within 2,000 
flight cycles after doing the temporary repair, do the final repair 
per the Accomplishment Instructions of Airbus Service Bulletin A300-
53-0354, Revision 02, dated December 13, 2001.
    (2) If a final repair has been accomplished: Perform repetitive 
inspections per a method and at intervals approved by either the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, or the DGAC (or its delegated agent).
    (g) For Model A300 B2 and A300 B4 series airplanes, except those 
airplanes with Airbus Modification 2611 accomplished in production: 
Prior to the accumulation of 30,300 total flight cycles, or within 
19 months after the effective date of this AD, whichever occurs 
later, do the inspections in paragraphs (g)(1) and (g)(2) of this 
AD.
    (1) From the airplane interior: Do an ultrasonic inspection to 
detect cracking of the skin lap joint located below the mid-
passenger door panel, below stringer 27, between frames 28A and 30A, 
on the left and right sides of the airplane, as applicable, per the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-0356, 
dated December 26, 2000.
    (i) If no cracking is detected: Repeat the inspection required 
by paragraph (g)(1) of this AD thereafter at intervals not to exceed 
4,100 flight cycles.
    (ii) If any cracking is detected in area A as defined in Figure 
1 of Airbus Service Bulletin A300-53-0356: Before further flight, 
repair the affected area per a method approved by either the 
Manager, International Branch, ANM-116, or the DGAC (or its 
delegated agent). Upon completion of the repair, do repetitive 
inspections of the affected area per a method and at intervals 
approved by one of the airworthiness authorities listed above.
    (2) Do an external ultrasonic inspection to detect cracking of 
the skin lap joint located in the lower fuselage, aft of the wing, 
below the mid-passenger door panel, below stringer 52, between 
frames 56 and 58, on the left and right sides of the airplane, as 
applicable, per the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-0356, dated December 26, 2000. If an internal or 
external repair doubler approved by the FAA or the DGAC (or its 
delegated agent), of Airbus design origin, has been installed in 
this area, the doubler does not need to be removed for inspection of 
this area.
    (i) If no cracking is detected: Repeat the inspection required 
by paragraph (g)(2) of this AD thereafter at intervals not to exceed 
4,100 flight cycles.
    (ii) If any cracking is detected in Area B as defined in Figure 
1 of Airbus Service Bulletin A300-53-0356: Before further flight, do 
a final repair per the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-0356.
    (h) For Model A300 B2 and A300 B4 series airplanes, except those 
on which Airbus Service Bulletin A300-53-0209 has been accomplished: 
From the airplane interior, do an ultrasonic inspection to detect 
cracking of the skin lap joint located below the aft-passenger door 
panel, below stringer 28, between frames 72 and 76 on the left and 
right sides of the airplane, as applicable, per the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-0357, dated December 
26, 2000. If an internal or external repair doubler is installed in 
this area, inspection of this area is not required. Perform the 
inspection at the later of the times specified in paragraphs (h)(1) 
and (h)(2) of this AD.
    (1) Prior to the accumulation of 24,100 total flight cycles for 
S/Ns 0003 through 0156 inclusive, or 29,500 total flight cycles for 
S/Ns 0157 through 0305 inclusive.
    (2) Within 2,000 flight cycles or 19 months after the effective 
date of this AD, whichever occurs first.
    (i) If no cracking is detected during the inspection required by 
paragraph (h) of this AD: Repeat the inspection required by 
paragraph (h) of this AD at the intervals specified in paragraphs 
(i)(1) and (i)(2) of this AD, as applicable.
    (1) For Model A300 B2 and A300 B4 series airplanes with S/Ns 
0003 through 0156 inclusive: Repeat the inspection thereafter at 
intervals not to exceed 3,400 flight cycles.
    (2) For Model A300 B2 and A300 B4 series airplanes with S/Ns 
0157 through 0305 inclusive: Repeat the inspection thereafter at 
intervals not to exceed 5,400 flight cycles.
    (j) For all Model A300 B2 and A300 B4 series airplanes; if any 
cracking is detected during the inspection required by paragraph (h) 
of this AD: Before further flight, repair the affected area, per a 
method approved by either the Manager, International Branch,

[[Page 21400]]

ANM-116, or the DGAC (or its delegated agent).

Inspections and Corrective Actions: Model A310 Series Airplanes

    (k) For Model A310 series airplanes; prior to the accumulation 
of 29,500 total flight cycles, or within 19 months after the 
effective date of this AD, whichever occurs later: From the airplane 
interior, do an ultrasonic inspection to detect cracking of the skin 
lap joint located below the aft-passenger door panel, below stringer 
28, between frame 72 and frame 76, on the right and left sides of 
the airplane, as applicable, per the Accomplishment Instructions of 
Airbus Service Bulletin A310-53-2112, dated December 26, 2000; or 
Airbus Service Bulletin A310-53-2112, Revision 01, dated February 
25, 2003. If an internal or external repair doubler is installed in 
any inspection area, inspection of that specific area is not 
required.
    (1) If no cracking is detected: Repeat the inspection thereafter 
at intervals not to exceed 5,400 flight cycles.
    (2) If any cracking is detected: Before further flight, repair 
the affected area, per a method and at repetitive intervals approved 
by either the Manager, International Branch, ANM-116, or the DGAC 
(or its delegated agent).

Inspections and Corrective Actions: Model A300-600 Series Airplanes

    (l) For Model A300-600 series airplanes: From the airplane 
interior, do an ultrasonic inspection to detect cracking of the skin 
lap joint located above the mid-passenger door panel, below stringer 
11, between frames 28A and 31, on the right and left sides of the 
airplane, as applicable, per the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-6129, Revision 02, dated December 
13, 2001; or Airbus Service Bulletin A300-53-6129, Revision 03, 
dated February 25, 2003. Do the inspection at the applicable time 
specified in paragraph (l)(1), (l)(2), or (l)(3) of this AD. If no 
cracking is detected, repeat the inspection thereafter at intervals 
not to exceed 6,500 flight cycles.
    (1) For airplanes with less than 20,500 flight cycles as of the 
effective date of this AD: Inspect before the accumulation of 20,500 
total flight cycles or within 19 months after the effective date of 
this AD, whichever occurs later.
    (2) For airplanes with 20,500 total flight cycles or more, but 
less than 26,500 total flight cycles as of the effective date of 
this AD: Inspect within 500 flight cycles after the effective date 
of this AD.
    (3) For airplanes with 26,500 total flight cycles or more as of 
the effective date of this AD: Inspect within 200 flight cycles or 
30 days after the effective date of this AD, whichever occurs later.
    (m) If any cracking is detected during any inspection per 
paragraph (l) of this AD: Do paragraphs (m)(1) and (m)(2) of this 
AD, as applicable.
    (1) If any crack is detected in Area A as defined in Figure 1 of 
Airbus Service Bulletin A300-53-6129, Revision 02, dated December 
13, 2001; or Revision 03, dated February 25, 2003: Before further 
flight, repair per a method approved by either the Manager, 
International Branch, ANM-116, or the DGAC (or its delegated agent).
    (2) If any crack is detected in Area B as defined in Figure 1 of 
Airbus Service Bulletin A300-53-6129, Revision 02, dated December 
13, 2001; or Revision 03, dated February 25, 2003: Before further 
fight, do a temporary repair or final repair, as applicable, per the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6129, 
Revision 02, dated December 13, 2001; or Revision 03, dated February 
25, 2003.
    (n) For airplanes which have been repaired per paragraph (m)(2) 
of this AD: Do paragraph (n)(1) or (n)(2) of this AD, as applicable.
    (1) If a temporary repair has been accomplished: Within 2,000 
flight cycles after doing the temporary repair, do the final repair 
per the Accomplishment Instructions of Airbus Service Bulletin A300-
53-6129, Revision 02, dated December 13, 2001; or Airbus Service 
Bulletin A300-53-6129, Revision 03, dated February 25, 2003.
    (2) If a final repair has been accomplished: Perform repetitive 
inspections per a method and at intervals approved by either the 
Manager, International Branch, ANM-116, or the DGAC (or its 
delegated agent).

Credit for Previous Service Bulletin Revision

    (o) Accomplishment of the actions specified in Airbus Service 
Bulletin A300-53-6129, Revision 01, dated December 26, 2000, before 
the effective date of this AD, is considered acceptable for 
compliance with the requirements of paragraph (l) of this AD.

Submission of Inspection Results to Manufacturer Not Required

    (p) Although the service bulletins referenced in this AD specify 
to submit information to the manufacturer, this AD does not include 
such a requirement.

Alternative Methods of Compliance

    (q)(1) In accordance with 14 CFR 39.19, the Manager, 
International Branch, ANM-116, is authorized to approve alternative 
methods of compliance for this AD.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 2000-02-39, amendment 39-11557, are approved as 
alternative methods of compliance with the applicable actions in 
this AD.

Incorporation by Reference

    (r) Unless otherwise specified in this AD, the actions shall be 
done in accordance with the Airbus documents listed in Table 1 of 
this AD, as applicable:

          Table 1.--Service Documents Incorporated by Reference
------------------------------------------------------------------------
   Airbus document number      Revision level             Date
------------------------------------------------------------------------
All Operators Telex A300-     Original.......  January 4, 2000.
 53A0352.
Airbus Service Bulletin A300- 02.............  December 13, 2001.
 53-0354, excluding Appendix
 01.
Airbus Service Bulletin A300- Original.......  December 26, 2000.
 53-0356, excluding Appendix
 01.
Airbus Service Bulletin A300- Original.......  December 26, 2000.
 53-0357, excluding Appendix
 01.
Airbus Service Bulletin A310- Original.......  December 26, 2000.
 53-2112, excluding Appendix
 01.
Airbus Service Bulletin A310- 01.............  February 25, 2003.
 53-2112, excluding Appendix
 01.
Airbus Service Bulletin A300- 02.............  December 13, 2001.
 53-6129, excluding Appendix
 01.
Airbus Service Bulletin A300- 03.............  February 25, 2003.
 53-6129, excluding Appendix
 01.
------------------------------------------------------------------------

    (1) The incorporation by reference of the Airbus documents 
listed in Table 2 of this AD is approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51:

        Table 2.--New Service Documents Incorporated by Reference
------------------------------------------------------------------------
       Airbus document         Revision level             Date
------------------------------------------------------------------------
Airbus Service Bulletin A300- 02.............  December 13, 2001.
 53-0354, excluding Appendix
 01.
Airbus Service Bulletin A300- Original.......  December 26, 2000.
 53-0356, excluding Appendix
 01.
Airbus Service Bulletin A300- Original.......  December 26, 2000.
 53-0357, excluding Appendix
 01.
Airbus Service Bulletin A310- Original.......  December 26, 2000.
 53-2112, excluding Appendix
 01.
Airbus Service Bulletin A310- 01.............  February 25, 2003.
 53-2112, excluding Appendix
 01.
Airbus Service Bulletin A300- 02.............  December 13, 2001.
 53-6129, excluding Appendix
 01.

[[Page 21401]]

 
Airbus Service Bulletin A300- 03.............  February 25, 2003.
 53-6129, excluding Appendix
 01.
------------------------------------------------------------------------

    (2) The incorporation by reference of All Operators Telex A300-
53A0352, dated January 4, 2000, was approved previously by the 
Director of the Federal Register as of February 22, 2000 (65 FR 
5756, February 7, 2000).
    (3) Copies may be obtained from Airbus, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

    Note 2: The subject of this AD is addressed in French 
airworthiness directive 2002-639(B), dated December 24, 2002.

Effective Date

    (s) This amendment becomes effective on May 26, 2004.

    Issued in Renton, Washington, on April 6, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-8540 Filed 4-20-04; 8:45 am]
BILLING CODE 4910-13-P