[Federal Register: September 7, 2004 (Volume 69, Number 172)]
[Proposed Rules]
[Page 54063-54067]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07se04-19]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19002; Directorate Identifier 2003-NM-27-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series
Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes; and
Model C4-605R Variant F Airplanes (Collectively Called A300-600)
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for certain Airbus Model A300 B2 and A300 B4 series
airplanes; A300 B4-600, B4-600R, and F4-600R series airplanes; and
Model C4-605R Variant F airplanes (collectively called A300-600). That
AD currently requires repetitive inspections to detect cracks in Gear
Rib 5 of the main landing gear (MLG) attachment fittings at the lower
flange, and repair, if necessary. That AD also requires modification of
Gear Rib 5 of the MLG attachment fittings, which constitutes
terminating action for the repetitive inspections. This proposed AD
would reduce the compliance times for all inspections, and require that
you do the inspections in accordance with new revisions of the service
bulletins. This proposed AD is prompted by new service information that
was issued by the manufacturer and mandated by the French airworthiness
authority. We are proposing this AD to prevent fatigue cracking of the
MLG attachment fittings, which could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on this proposed AD by October 7, 2004.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For the service information identified in this proposed AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-19002;
Directorate Identifier 2003-NM-27-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.Examining
the Docket
You can examine the AD docket in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the DOT street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after the DMS
receives them.
Discussion
On February 29, 2000, we issued AD 2000-05-07, amendment 39-11616
(65 FR 12077, March 8, 2000), for certain Airbus Model A300 and A300-
600 series airplanes. That AD requires repetitive inspections to detect
cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings
at the lower flange, and repair, if necessary. That AD also requires
modification of Gear Rib 5 of the MLG attachment fittings, which
constitutes terminating action for the repetitive inspections. That AD
was
[[Page 54064]]
prompted by issuance of mandatory continuing airworthiness information
by the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France. We issued that AD to
prevent fatigue cracking of the MLG attachment fittings, which could
result in reduced structural integrity of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2000-05-07, Airbus has new service information,
which the DGAC mandated at reduced compliance times for all
inspections.
Relevant Service Information
Airbus has issued the following service bulletins:
Airbus Service Bulletin A300-57-6087, Revision 04, dated
February 19, 2002; and Airbus Service Bulletin A300-57-0234, Revision
05, dated February 19, 2002. The procedures in these revisions are
essentially the same as those in previous revisions of the service
bulletin, which were referenced in the AD 2000-05-07 for accomplishment
of the inspections. However, these new revisions change the compliance
thresholds and inspection intervals. These revisions also contain
certain corrections of airplane effectivity.
Airbus Service Bulletin A300-57-6088, Revision 03, dated
March 18, 2003; and Airbus Service Bulletin A300-57-0235, Revision 05,
dated December 3, 2003. The procedures in these revisions are
essentially the same as those in the previous revisions of the service
bulletins, which were referenced in the existing AD for accomplishment
of the modifications. These new revisions of the service bulletins add
a statement for operators who require assistance with installing
certain fasteners.
We have determined that accomplishment of the actions specified in
the service information will adequately address the unsafe condition.
The DGAC mandated the service information and issued French
airworthiness directive 2003-318(B), dated August 30, 2003, to ensure
the continued airworthiness of these airplanes in France.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would supersede AD 2000-
05-07 to continue to require repetitive inspections to detect cracks in
Gear Rib 5 of the MLG attachment fittings at the lower flange, and
repair, if necessary; and to continue to require modification of Gear
Rib 5 of the MLG attachment fittings, which constitutes terminating
action for the repetitive inspections. This proposed AD would also
reduce the compliance threshold and repetitive intervals for the
inspections in the same area. The proposed AD would require you to use
the service information described previously to perform these actions,
except as discussed under ``Difference Between the Proposed AD and the
French Airworthiness Directive,'' and ``Differences Between the
Proposed AD and the Service Information.''
Difference Between the Proposed AD and the French Airworthiness
Directive
The applicability of French airworthiness directive 2003-318(B)
excludes airplanes that accomplished Airbus Service Bulletin A300-57-
0235 or Airbus Service Bulletin A300-57-6088 in service. However, we
have not excluded those airplanes in the applicability of this proposed
AD; rather, this proposed AD includes a requirement to accomplish the
actions specified in those service bulletins. Such a requirement would
ensure that the actions specified in the service bulletin and required
by this proposed AD are accomplished on all affected airplanes.
Operators must continue to operate the airplane in the configuration
required by this proposed AD unless an alternative method of compliance
is approved.
Differences Between the Proposed AD and the Service Information
Although Airbus Service Bulletin A300-57-6088, Revision 03,
specifies that the manufacturer may be contacted for disposition of
certain repairs, this proposed AD would require the repair of those
conditions to be accomplished in accordance with a method approved
either by us or by the DGAC (or its delegated agent). In light of the
type of repair that would be required to address the identified unsafe
condition, and in consonance with existing bilateral airworthiness
agreements, we have determined that a repair approved by either us or
the DGAC (or its delegated agent) would be acceptable for compliance
with this proposed AD.
Operators should note that, although the Accomplishment
Instructions of the referenced service bulletins describe procedures
for submitting certain information to the manufacturer, this proposed
AD would not require those actions.
Clarification of Inspection Thresholds
The French airworthiness directive gives repetitive inspection
thresholds based on the original issue date of that airworthiness
directive. Due to some procedural differences in the way we express
compliance times, the thresholds in paragraph (i) of this proposed AD
are presented in a manner that differs from those in the French
airworthiness directive. However, the compliance times capture the
intent of the French airworthiness directive, and ensure that operators
of all affected airplanes are given sufficient time to accomplish the
inspections while still ensuring continued operational safety.
Changes to Existing AD
This proposed AD would retain all requirements of AD 2000-05-07.
Since AD 2000-05-07 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD as listed in the
following table:
Revised Paragraph Identifiers
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Corresponding requirement
Requirement in AD 2000-05-07 in this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
paragraph (c)............................. paragraph (h).
paragraph (e)............................. paragraph (p).
------------------------------------------------------------------------
We have changed all references to a ``detailed visual inspection''
in the existing AD to ``detailed inspection'' in this action.
We have revised the applicability of the existing AD to identify
model designations as published in the most recent type certificate
data sheet for the affected models.
In addition, we have reformatted the existing requirements in
paragraph (f) of this proposed AD (paragraph (a) of AD 2000-05-07) to
list service bulletin references in two tables. We included the tables
for clarity because we added several service bulletin revisions to this
paragraph.
[[Page 54065]]
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
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Number of
Average Cost per U.S.-
Action Work hours labor rate Parts airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Modification (required by AD 2000- 62 $65 $10,270 $14,300 164 $2,345,200
05-07)...........................
Inspections (new proposed action). 6 65 None 390 164 63,960
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Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing amendment 39-11616 (65 FR
12077, March 8, 2000) and adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2004-19002; Directorate Identifier 2003-NM-
27-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by October 7, 2004.
Affected ADs
(b) This AD supersedes AD 2000-05-07, amendment 39-11616.
Applicability
(c) This AD applies to Model A300 B2 and A300 B4 series
airplanes, as listed in Airbus Service Bulletin A300-57A0234,
Revision 05, dated February 19, 2002; and Model A300 B4-600, B4-
600R, and F4-600R series airplanes, and Model C4-605R Variant F
airplanes (collectively called A300-600), as listed in Airbus
Service Bulletin A300-75A6087, Revision 04, dated February 19, 2002;
except airplanes on which Airbus Modification 11912 or 11932 has
been installed; certificated in any category.
Unsafe Condition
(d) This AD was prompted by new service information that was
issued by the manufacturer and mandated by the French airworthiness
authority. We are issuing this AD to prevent fatigue cracking of the
main landing gear (MLG) attachment fittings, which could result in
reduced structural integrity of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of the Requirements of AD 2000-05-07
Repetitive Inspections
(f) Perform a detailed inspection and a high frequency eddy
current (HFEC) inspection to detect cracks in Gear Rib 5 of the MLG
attachment fittings at the lower flange, in accordance with the
Accomplishment Instructions of any applicable service bulletin
listed in Table 1 and Table 2 of this AD, at the time specified in
paragraph (f)(1) or (f)(2) of this AD. After April 12, 2000 (the
effective date of AD 2000-05-07, amendment 39-11616), only the
service bulletins listed in Table 2 of this AD may be used. Repeat
the inspections thereafter at intervals not to exceed 1,500 flight
cycles, until paragraph (h), (i), or (k) of this AD is accomplished.
Table 1.--Revision 01 of Service Bulletins
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Revision
Model Service bulletin level Date
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A300-600.............................. A300-57-6087............. 01 March 11, 1998.
A300 B2 and A300 B4................... A300-57-0234............. 01 March 11, 1998.
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Table 2.--Further Revisions of Service Bulletins
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Model Service bulletin Revision level Date
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A300-600.......................... A300-57A6087......... 02, including June 24, 1999.
Appendix 01. May 19, 2000.
03, including February 19, 2002.
Appendix 01.
04, including
Appendix 01.
[[Page 54066]]
A300 B2 and A300 B4............... A300-57A0234......... 02.................. June 24, 1999.
03, including September 2, 1999.
Appendix 01. May 19, 2000.
04, including February 19, 2002.
Appendix 01.
05, including
Appendix 01.
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(1) For airplanes that have accumulated 20,000 or more total
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, amendment 39-10298): Inspect within 500 flight cycles after
March 9, 1998.
(2) For airplanes that have accumulated less than 20,000 total
flight cycles as of March 9, 1998: Inspect prior to the accumulation
of 18,000 total flight cycles, or within 1,500 flight cycles after
March 9, 1998, whichever occurs later.
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 mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
Note 2: Accomplishment of the initial detailed and HFEC
inspections in accordance with Airbus Service Bulletin A300-57A0234
or A300-57A6087, both dated August 1, 1997, as applicable, is
considered acceptable for compliance with the initial inspections
required by paragraph (f) of this AD.
Repair
(g) If any crack is detected during any inspection required by
paragraph (f) of this AD, prior to further flight, accomplish the
requirements of paragraphs (g)(1) or (g)(2) of this AD, as
applicable.
(1) If a crack is detected at one hole only, and the crack does
not extend out of the spotface of the hole, repair in accordance
with the applicable service bulletin in Table 2 of this AD.
(2) If a crack is detected at more than one hole, or if any
crack at any hole extends out of the spotface of the hole, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate, or the
Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its
delegated agent).
Terminating Modification
(h) Prior to the accumulation of 21,000 total flight cycles, or
within 2 years after October 20, 1999 (the effective date of AD 99-
19-26, amendment 39-11313), whichever occurs later: Modify Gear Rib
5 of the MLG attachment fittings at the lower flange in accordance
with the applicable service bulletin in Table 3 of this AD. After
the effective date of this AD, only Revision 04 of Airbus Service
Bulletin A300-57-6088, and Revisions 04 and 05 of Airbus Service
Bulletin A300-57-0235 may be used. Accomplishment of this
modification constitutes terminating action for the repetitive
inspection requirements of this AD.
Table 3.--Service Bulletins for Terminating Modification
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Model Service bulletin Revision level Date
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A300-600.......................... A300-57-6088......... 01, including February 1, 1999.
Appendix 01. December 3, 2003.
04..................
A300 B2 and A300 B4............... A300-57-0235......... 01, including February, 1, 1999.
Appendix 01. March 13, 2003.
04.................. December 3, 2003.
05..................
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Note 3: Accomplishment of the modification required by paragraph
(h) of this AD prior to April 12, 2000 (the effective date of AD
2000-05-07), in accordance with Airbus Service Bulletin A300-57-6088
or A300-57-0235, both dated August 1, 1998; as applicable; is
acceptable for compliance with the requirements of that paragraph.
New Requirements of This AD
Repetitive Inspections
(i) For airplanes on which the modification specified in
paragraph (h) of this AD has not been done as of the effective date
of this AD, perform a detailed and a HFEC inspection to detect
cracks in Gear Rib 5 of the MLG attachment fittings at the lower
flange, in accordance with the applicable service bulletin in Table
4 of this AD. Perform the inspections at the applicable time
specified in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of this AD.
Repeat the inspections thereafter at intervals not to exceed 700
flight cycles until the terminating modification required by
paragraph (k) of this AD is accomplished. Accomplishment of the
inspections per paragraph (i) of this AD, terminates the inspection
requirements of paragraph (f) of this AD.
Table 4.--Service Bulletins for Repetitive Inspections
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Model Service bulletin Revision level Date
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A300-600.......................... A300-57-6087......... 04, including February 19, 2002.
Appendix 01.
A300 B2 and A300 B4............... A300-57-0234......... 05, including February 19, 2002.
Appendix 01.
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(1) For Models A300 B2 and A300 B4 series airplanes; A300 B4-
600, B4-600R, and F4-600R series airplanes; and Model C4-605R
Variant F airplanes (collectively called A300-600) that have
accumulated 18,000 or more total flight cycles as of the effective
date of this AD: Within 700 flight cycles after the effective date
of this AD.
(2) For Model A300 B2 series airplanes that have accumulated
less than 18,000 total flight cycles as of the effective date of
this AD: Prior to the accumulation of 18,000 total flight cycles, or
within 700 flight cycles after the effective date of this AD,
whichever occurs later.
(3) For Model A300 B4 series airplanes that have accumulated
less than 18,000 total flight cycles as of the effective date of
this AD: Prior to the accumulation of 14,500 total flight cycles, or
within 700 flight cycles after the effective date of this AD,
whichever occurs later.
(4) For Model A300 B4-600, B4-600R, and F4-600R series
airplanes; and Model C4-605R Variant F airplanes (collectively
called A300-600) that have accumulated less than
[[Page 54067]]
18,000 total flight cycles as of the effective date of this AD:
Prior to the accumulation of 11,600 total flight cycles, or within
700 flight cycles after the effective date of this AD, whichever
occurs later.
Repair
(j) If any crack is detected during any inspection required by
paragraph (i) of this AD, prior to further flight, accomplish the
requirements of paragraph (j)(1) and (j)(2) of this AD, as
applicable.
(1) If a crack is detected at only one hole, and the crack does
not extend out of the spotface of the hole, repair in accordance
with Airbus Service Bulletin A300-57A0234, Revision 05, including
Appendix 01, dated February 19, 2002 (for Models A300 B2 and A300
B4); or A300-57A6087, Revision 04, including Appendix 01, dated
February 19, 2002 (for Models A300-600); as applicable.
(2) If a crack is detected at more than one hole, or if any
crack at any hole extends out of the spotface of the hole, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, or the DGAC (or its delegated agent).
Terminating Modification
(k) For airplanes on which the terminating modification in
paragraph (h) of this AD has not been accomplished as of the
effective date of this AD: At the earlier of the times specified in
paragraphs (k)(1) and (k)(2) of this AD, modify Gear Rib 5 of the
MLG attachment fittings at the lower flange. Except as provided by
paragraph letter (l) of this AD, do the modification in accordance
with the applicable service bulletin in Table 3 of this AD.
(1) Prior to the accumulation of 21,000 total flight cycles, or
within 2 years after October 20, 1999, whichever is later.
(2) Within 15 months after the effective date of this AD.
(l) Where the applicable service bulletin in paragraph (k) of
this AD specifies to contact Airbus for modification instructions:
Prior to further flight, modify in accordance with a method approved
by the Manager, International Branch, ANM-116, or the DGAC (or its
delegated agent).
(m) For airplanes that were modified prior to the effective date
of this AD in accordance with paragraph (h) of this AD, and on which
repairs were made prior to the effective date of this AD per
paragraph (g) of this AD, or on which cracks were found during the
accomplishment of paragraph (h) of this AD: Within 15 months after
the effective date of this AD, repair in accordance with a method
approved by the Manager, International Branch, ANM-116, or the DGAC
(or its delegated agent).
Actions Accomplished Per Previous Issues of the Service Bulletins
(n) Actions accomplished before the effective date of this AD
per the service bulletins listed in Table 5 of this AD, are
considered acceptable for compliance with the corresponding action
specified in this AD.
Table 5.--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-57-0235............................. 02.......................... September 27, 1999.
03, including Appendix 01... September 5, 2002.
A300-57A6087............................. Original Issue.............. August 1, 1997.
A300-57-6088............................. 02.......................... September 5, 2000.
03.......................... March 13, 2003.
----------------------------------------------------------------------------------------------------------------
No Reporting Requirements
(o) Although the service bulletins A300-57A0234, A30057-0235,
A300-57A6087, and A300-57-6088 specify to submit certain information
to the manufacturer, this AD does not include such a requirement.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
(2) Alternative methods of compliance, approved previously per
AD 2000-05-07, amendment 39-11616, are approved as alternative
methods of compliance with this AD.
Related Information
(q) French airworthiness directive 2003-318(B), dated August 20,
2003, also addresses the subject of this AD.
Issued in Renton, Washington, on August 26, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-20211 Filed 9-3-04; 8:45 am]
BILLING CODE 4910-13-P