[Federal Register: December 18, 2003 (Volume 68, Number 243)]
[Proposed Rules]
[Page 70464-70468]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18de03-17]
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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:
9-anm-nprmcomment@faa.gov. 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]
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