[Federal Register Volume 68, Number 243 (Thursday, December 18, 2003)]
[Proposed Rules]
[Pages 70464-70468]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31194]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-111-AD]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Airbus Model A300 
series airplanes, that currently requires either a one-time

[[Page 70465]]

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 action would require repetitive ultrasonic inspections 
to detect cracking of certain skin lap joints in additional areas of 
the fuselage and repair if necessary. This action also would expand the 
applicability of the existing AD to include additional airplanes. The 
actions specified by the proposed 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: Comments must be received by January 20, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-111-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-111-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written, views, or arguments as they 
may desire. Communications shall identify the Rules Docket number and 
be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of comments received.
    Submit comments using the following format:
    [sbull] Organize comments issue-by issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-111-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docked No. 2001-NM-111-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On January 31, 2000, the FAA issued AD 2000-02-39, amendment 39-
11557 (65 FR 5756, February 7, 2000), applicable to certain Airbus 
Model A300 series airplanes, 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. 
That action was prompted by notification from the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, that during a routine maintenance 
check on an Airbus Model A300 series airplane, a horizontal crack of 
35.6 inches was detected in the surrounding panel above the right mid-
passenger door. The requirements of that AD are intended to detect and 
correct cracking of the longitudinal skin splice (skin lap joint) above 
the mid-passenger door panels, which could result in reduced structural 
integrity of the fuselage pressure vessel.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, further analysis by the manufacturer 
revealed that additional areas with similar stress loading and design 
may also be affected by cracking. Because of the similar stress loading 
and design, cracking of certain skin lap joints may exist on all Airbus 
Model A300 B4-600, B4-600R, F4-600R, C4-605R Variant F (collectively 
called A300-600), and A310 series airplanes; therefore, those airplanes 
may also be subject to the same unsafe condition described above. The 
DGAC issued French airworthiness directive 2002-639(B), dated December 
24, 2002, to ensure the continued airworthiness of these airplanes in 
France. That French airworthiness directive supersedes French 
airworthiness directives 2000-001-300(B)R1 and 2001-071(B).

Explanation of Relevant Service Information

    For Model A300 B2 and A300 B4 series airplanes, Airbus has issued 
Service Bulletins A300-53-0354, Revision 02, dated December 13, 2001; 
A300-53-0356, dated December 26, 2000; and A300-53-0357, dated December 
26, 2000. These service bulletins describe procedures for repetitive 
ultrasonic inspections to detect cracking in certain skin lap joints, 
and repair if necessary.
    [sbull] Service Bulletin A300-53-0354 describes procedures for 
repetitive inspections of skin lap joints located above the mid-
passenger doors. If repair is necessary, operators are instructed to do 
temporary or final repair, as applicable, per the applicable repair 
drawing.
    [sbull] Service Bulletin A300-53-0356 describes procedures for 
repetitive inspections of skin lap joints located below the mid-
passenger doors and in the lower fuselage aft of the wing. If repairs 
is necessary, operators are instructed to do a final repair per the 
applicable Airbus structural repair manual. The effectivity of this 
specific service bulletin excludes those airplanes modified by Airbus 
Modification 2611 in production.
    [sbull] Service Bulletin A300-53-0357 describes procedures for 
repetitive inspections on skin lap joints located above the aft-
passenger doors. If repair

[[Page 70466]]

is necessary, operators are instructed to contact Airbus for repair 
instructions.
    For Model A300-600 series airplanes, Airbus has issued Service 
Bulletin A310-53-6129, Revision 02, dated December 13, 2001, which 
describes procedures for repetitive ultrasonic inspections to detect 
cracking in skin lap joints located above the mid-passenger doors, and 
repair if necessary.
    For Model A310 series airplanes, Airbus has issued Service Bulletin 
A310-53-2112, dated December 26, 2000, which describes procedures for 
repetitive ultrasonic inspections to detect cracking in skin lap joints 
located below the aft passenger door, and repair if necessary.
    Accomplishment of the actions specified in the service bulletins 
are intended to adequately address the identified unsafe condition.

FAA's Conclusions

    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. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
actions is necessary for products of this type design that are 
certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would supersede AD 2000-02-39 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 proposed AD would 
also require repetitive ultrasonic inspections to detect cracking of 
certain skin lap joints in additional areas of the fuselage, and repair 
if necessary. The actions would be required to be accomplished in 
accordance with the service bulletins described previously, except as 
discussed below.

Explanation of Change Made to Existing Requirements

    The FAA has changed all references to a ``detailed visual 
inspection'' in the existing AD to ``detailed inspection'' in this 
action.

Explanation of Change to Applicability

    In this proposed AD the FAA has revised the applicability of 
affected Airbus Model A300 series airplanes to ``Airbus Model A300 B2 
Series Airplanes'' and ``Airbus Model A300 B4 Series Airplanes'' to 
match the most recent type certificate data sheet for the affected 
models.
    Also, for Model A300 series airplanes, the applicability of the 
existing AD includes serial numbers ``1 through 156 inclusive.'' In 
this action the applicability for Airbus Model A300 B2 and B4 series 
airplanes has been changed to include serial numbers ``0003 through 
0156 inclusive.'' The airplanes with serial numbers 1 and 2 were 
destroyed by the manufacturer.

No Flight With Cracks

    Airbus Service Bulletins A300-53-0354, Revision 02; A300-53-0356; 
and A300-53-6129, Revision 02; allow flight with cracking of certain 
lengths, as specified in the applicable service bulletin. This proposed 
AD would not allow flight with any cracking, regardless of crack 
length. We have determined that because of the safety implications and 
consequences associated with such cracking, any cracking must be 
repaired before further flight.

Difference Between the Proposed AD and the Service Information

    Operators should note that, although the service bulletins specify 
that the manufacturer may be contacted for disposition of certain 
repair conditions and repetitive inspections after a final repair, this 
proposal would require the repair of those conditions to be 
accomplished in accordance with a method approved by either the FAA, or 
the DGAC (or its delegated agent). In light of the type of repair that 
would be required to address the identified unsafe condition, and 
consonance with existing bilateral airworthiness agreements, the FAA 
has determined that, for this proposed AD, a repair approved by either 
the FAA or the DGAC would be acceptable for compliance with this 
proposed AD.

Cost Impacts

    There are approximately 128 airplanes of U.S. registry that would 
be affected by this proposed AD.
    The ultrasonic inspection that is currently required by AD 200-02-
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 2000-01-39 
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 that is proposed in this AD action would 
take approximately 1 work hour per airplane to accomplish, at an 
average rate of $65 per work hour. Based on these figures, the cost 
impact of this proposed 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 current or proposed 
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 proposed herein 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.Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this 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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the

[[Page 70467]]

location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

Airbus: 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, 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 number (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 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 A300-53A0532, 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 
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 paragraphs 
(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 Sevice 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 flight, 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) of (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 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.

[[Page 70468]]

    (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 paragraph 
(i)(1) and (i)(2) of this AD, as applicable.
    (1) For Model A300 B2 and A300 B4 series airplanes with S/Ns 003 
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 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, 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. 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 Corrections 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. 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 A300-53-619, Revision 02, dated December 13, 
2001: 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: 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.
    (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.
    (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 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 (1) of this AD.

Submission of Inspection Results to Manufacture Not Required

    (p) Although the service bulletins referenced in this AD specify 
to submit information to the manufacture, 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.

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


    Dated: Issued in Renton, Washington, on December 11, 2003.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-31194 Filed 12-17-03; 8:45 am]
BILLING CODE 4910-13-M