[Federal Register: October 30, 2003 (Volume 68, Number 210)]
[Proposed Rules]
[Page 61768-61772]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30oc03-22]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-216-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes; Model A300 B4-600, B4-600R, and F4-600R (Collectively Called
A300-600) Series Airplanes; and Model A310 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Airbus Model A300 B2 and
B4 series airplanes; Model A300 B4-600, B4-600R, and F4-600R
(collectively called A300-600) series airplanes; and Model A310 series
airplanes. This proposal would require various modifications and
repetitive inspections of the throttle control system, and follow-on
actions if necessary. This action is necessary to prevent hard points
in the throttle control system that could lead to jamming of the
throttle control cable. Such jamming could result in an asymmetric
thrust condition and consequent reduced controllability of the
airplane. This action is intended to address the identified unsafe
condition.
DATES: Comments must be received by December 1, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-216-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-216-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 or 2000 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; 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 data, 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 the 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
[[Page 61769]]
Docket Number 2001-NM-216-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
Docket No. 2001-NM-216-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified the FAA that
an unsafe condition may exist on certain Airbus Model A300 B2 and B4
series airplanes; Model A300 B4-600, B4-600R, and F4-600R (collectively
called A300-600) series airplanes; and Model A310 series airplanes. The
DGAC advises that operators have reported hard points in the throttle
control system on these airplanes. These hard points have been
attributed to various discrepancies in the throttle control system,
such as accumulation and subsequent freezing of moisture in the
throttle control cable (also called the ``push-pull'' cable) assembly;
disconnection of the throttle control cable from the rack-box;
stiffness of the throttle controls due to excessive wear, chafing, or
other damage; or deterioration of the throttle control cable due to
exposure to excessive heat. These conditions, if not corrected, could
lead to jamming of the throttle control cable and result in an
asymmetric thrust condition and consequent reduced controllability of
the airplane.
Explanation of Relevant Service Information
Airbus has issued the following service bulletins:
[sbull] Service Bulletin A300-76-0007, Revision 06, dated August
23, 2001 (for certain Airbus Model A300 B2 and B4 series airplanes).
That service bulletin describes procedures for installing a flexible
ice protection boot on the upper fitting of the throttle and fuel shut-
off valve control cables. This boot is intended to prevent accumulation
of moisture at the end of the control cable assembly, which could
freeze and result in jamming of the control cable.
[sbull] Service Bulletins A300-76-0015, Revision 02, dated August
23, 2001 (for certain Airbus Model A300 B2 and B4 series airplanes);
and A310-76-2001, Revision 01, dated March 14, 2000 (for certain Model
A310-203, -204, -221, and -222 series airplanes). These service
bulletins describe procedures for installing a heating system for the
throttle control system. This heating system is intended to prevent
freezing and consequent jamming of the throttle controls.
[sbull] Service Bulletins A300-76-0016, Revision 03, dated August
23, 2001 (for certain Airbus Model A300 B2 and B4 series airplanes);
A300-76-6002, Revision 02, dated August 23, 2001 (for certain Airbus
Model A300 B4-620, B4-622, and C4-620 airplanes); and A310-76-2005,
Revision 01, dated March 14, 2000 (for certain Airbus Model A310-203, -
221, and -222 airplanes). These service bulletins describe procedures
for replacing (with new, improved parts) the roller and rotation pin of
the secondary relay lever of the throttle control system. This
replacement is intended to prevent stiffness of the throttle controls
if the roller fails to rotate.
[sbull] Service Bulletins A300-76-6003, Revision 04, dated February
26, 2002 (for certain Airbus Model A300 B4-620 airplanes); and A310-76-
2006, Revision 03, dated February 26, 2002 (for certain A310-221, -222,
and -322 airplanes). These service bulletins describe procedures for
repetitive inspections of the throttle control (push-pull) cable and
the rack-box connection to detect any discrepancies, including
excessive wear, damage, chafing of the cable in the area of the cable
guide, backlash due to excessive wear, and excessive play. If
discrepancies are found, the service bulletins specify replacement of
the affected part with a new part. These service bulletins refer to
Airbus Service Bulletins A300-76-6004, Revision 01, dated October 11,
2000; and A310-76-2007, Revision 02, dated November 24, 1988;
respectively; which describe procedures for replacing the existing
throttle control cable assembly with a new, improved assembly. Such
replacement would eliminate the need for the repetitive inspections
described previously.
[sbull] Service Bulletins A300-76-6007, Revision 01, dated March
14, 2000 (for certain A300 B4-601, -603, and ``605R airplanes); and
A310-76-2010, Revision 03, dated August 23, 2001 (for certain A310-204
and -304 airplanes). These service bulletins describe procedures for
installing a new cooling duct and a new cooling shroud for the throttle
control cable. This installation is intended to prevent deterioration
of the throttle control (push-pull) cable due to exposure to excessive
heat. These service bulletins refer to GE CF6-80C2 Service Bulletins
71-088, Revision 03, dated March 15, 1991; and 75-021, Revision 03,
dated August 5, 1992; for additional service information for
accomplishing the installation.
[sbull] Service Bulletins A300-76-6009, Revision 02, dated October
29, 1999 (for certain A300 B4-601, B4-603, B4'605R, and C4-605R Variant
F airplanes); and A310-76-2012, Revision 02, dated November 5, 2001
(for certain Airbus Model A310-203, -204, and -304 airplanes). These
service bulletins describe procedures for installing an elastomer plug
filled with grease on the end fitting of the throttle control cable.
This installation is intended to prevent accumulation of moisture
inside the control cable sleeve due to premature and uneven wear of the
throttle control bearing, which could result in freezing and jamming of
the throttle control cable.
[sbull] Service Bulletin A310-76-2004, Revision 03, dated August
23, 2001 (for certain Airbus Model A310-203 airplanes). This service
bulletin describes procedures for installing a sealing sleeve (also
called a sealing boot) on the flexible control ball joint of the
throttle control cable. The procedures include a visual inspection for
deterioration of the throttle control cable, and replacement of the
throttle control cable if necessary. The sealing sleeve is intended to
prevent accumulation of moisture at the ends of the throttle control
cable assembly, which could result in freezing and consequent jamming
of the throttle control cable.
Accomplishment of the actions specified in the applicable service
bulletins is intended to adequately address the identified unsafe
condition. The DGAC classified these service bulletins as mandatory and
issued French airworthiness directive 2001-072(B) R2, dated January 23,
2002, to ensure the continued airworthiness of these airplanes in
France.
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 us informed of the
situation described above. We have examined the findings of the DGAC,
reviewed all available information, and determined that AD action 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
[[Page 61770]]
develop on other airplanes of the same type design registered in the
United States, the proposed AD would require accomplishment of the
actions specified in the service bulletin described previously, except
as discussed below under the heading ``Difference Between Proposed AD
and Certain Service Bulletins.''
Consistent with the findings of the DGAC, the proposed AD would
allow repetitive inspections per Airbus Service Bulletin A300-76-6003,
Revision 04, or A310-76-2006, Revision 03, as applicable, to continue
in lieu of accomplishing the terminating action per Airbus Service
Bulletin A300-76-6004, Revision 01, or A310-76-2007, Revision 02, as
applicable. In making this determination, we considered that long-term
continued operational safety in this case will be ensured adequately by
repetitive inspections to detect any discrepancy of the throttle
control cable before it represents a hazard to the airplane.
Difference Between Proposed AD and Certain Service Bulletins
Although Airbus Service Bulletins A300-76-6003, Revision 04, and
A310-76-2006, Revision 03, specify to report the results of the
backlash check to the Airbus technical representative, this proposed AD
would not require such reporting.
Cost Impact
The table below contains the FAA's estimates of the cost impact on
U.S. operators of the actions that would be required by the proposed
AD, at an average labor rate of $65 per work hour.
Cost Impact: U.S.-Registered Airplanes
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Estimated
Actions in Airbus service number of Estimated cost Estimated
bulletin Work hours Parts cost airplanes of per airplane fleet cost
U.S. registry
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A300-76-0007, Revision 06....... 30 $0 36 $1,950 $70,200
A300-76-0015, Revision 02....... 11 1,726 36 2,441 87,876
A300-76-0016, Revision 03....... 1 193 24 258 6,192
A300-76-6002, Revision 02....... 1 80 83 145 12,035
A300-76-6007, Revision 01....... 8 None 71 520 36,920
A300-76-6009, Revision 02....... 6 28 67 418 28,006
A310-76-2001, Revision 01....... 11 4,469 33 5,184 171,072
A310-76-2004, Revision 03....... 25 26 25 1,651 41,275
A310-76-2005, Revision 01....... 1 153 46 218 10,028
A310-76-2006, Revision 03....... 2 None 16 130 2,080
A310-76-2012, Revision 02....... 6 28 25 418 10,450
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Currently, there are no airplanes on the U.S. Register that would
be affected by Airbus Service Bulletin A300-76-6003, Revision 04, or
A310-76-2010, Revision 03. However, if an affected airplane is imported
and placed on the U.S. Register in the future, the table below shows
the estimated cost of the actions that would be required by the
proposed AD for an affected airplane, at an average labor rate of $65
per work hour.
Potential Cost Impact: Airplane Added to U.S. Register in the Future
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Estimated cost
Airplanes subject to the actions in Airbus service bulletin Work hours Parts cost per airplane
----------------------------------------------------------------------------------------------------------------
A300-76-6003, Revision 04....................................... 2 $0 $130
A310-76-2010, Revision 03....................................... 8 0 520
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If an operator chooses to do the optional terminating action in
Airbus Service Bulletin A300-76-6004, Revision 01, or A310-76-2007,
Revision 02; rather than continue the repetitive inspections in Airbus
Service Bulletin A300-76-6003, Revision 04, or A310-76-2006, Revision
03, respectively; it would take about 20 work hours per airplane to
accomplish the optional terminating action, at an average labor rate of
$65 per work hour. Required parts would cost about $18,800 per
airplane. Based on these figures, we estimate the cost of this optional
terminating action to be $20,100 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the 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
[[Page 61771]]
contacting the Rules Docket at the 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 adding the following new
airworthiness directive:
Airbus: Docket 2001-NM-216-AD.
Applicability: Airplanes as listed in Table 1 of this AD,
certificated in any category.
Table 1.--Applicability
------------------------------------------------------------------------
As listed in Airbus Service
Airplane models Bulletin--
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A300 B2 and B4 series.................. A300-76-0007, Revision 06,
dated August 23, 2001.
A300 B2 and B4 series.................. A300-76-0015, Revision 02,
dated August 23, 2001.
A300 B2 and B4 series.................. A300-76-0016, Revision 03,
dated August 23, 2001.
A300 B4-620, B4-622, C4-620............ A300-76-6002, Revision 02,
dated August 23, 2001.
A300 B4-620............................ A300-76-6003, Revision 04,
dated February 26, 2002.
A300 B4-601, -603, and -605R........... A300-76-6007, Revision 01,
dated March 14, 2000.
A300 B4-601, B4-603, B4-605R, and C4- A300-76-6009, Revision 02,
605R Variant F. dated October 29, 1999.
A310-203, -204, -221, and -222......... A310-76-2001, Revision 01,
dated March 14, 2000.
A310-203............................... A310-76-2004, Revision 03,
dated August 23, 2001.
A310-203, -221, and -222............... A310-76-2005, Revision 01,
dated March 14, 2000.
A310-221, -222, and -322............... A310-76-2006, Revision 03,
dated February 26, 2002.
A310-204 and -304...................... A310-76-2010, Revision 03,
dated August 23, 2001.
A310-203, -204, and -304............... A310-76-2012, Revision 02,
dated November 5, 2001.
------------------------------------------------------------------------
Compliance: Required as indicated, unless accomplished
previously.
To prevent hard points in the throttle control system that could
lead to jamming of the throttle control cable, which could result in
an asymmetric thrust condition and consequent reduced
controllability of the airplane, accomplish the following:
Modifications
(a) Within 22 months after the effective date of this AD, do the
actions specified in paragraphs (a)(1), (a)(2), (a)(3), (a)(4),
(a)(5), and (a)(6) of this AD; as applicable.
(1) For airplanes listed in Airbus Service Bulletin A300-76-
0007, Revision 06, dated August 23, 2001: Install a flexible ice
protection boot on the upper fitting of the throttle and fuel shut-
off valve control cables in each engine pylon, per the
Accomplishment Instructions of that service bulletin.
(2) For airplanes listed in Airbus Service Bulletin A300-76-
0015, Revision 02, dated August 23, 2001; or A310-76-2001, Revision
01, dated March 14, 2000: Install a heating system for the throttle
control system in each engine pylon, per the Accomplishment
Instructions of the applicable service bulletin.
(3) For airplanes listed in Airbus Service Bulletin A300-76-
0016, Revision 03, dated August 23, 2001; A300-76-6002, Revision 02,
dated August 23, 2001; or A310-76-2005, Revision 01, dated March 14,
2000: Replace, with new improved parts, the roller and rotation pin
of the secondary relay lever of the throttle control system in each
engine pylon. Accomplish the replacement per the Accomplishment
Instructions of the applicable service bulletin.
(4) For airplanes listed in Airbus Service Bulletin A300-76-
6007, Revision 01, dated March 14, 2000; or A310-76-2010, Revision
03, dated August 23, 2001. Install a new cooling duct and a new
cooling shroud for the throttle control cable, per the instructions
in the ``Description'' section of Airbus Service Bulletin A300-76-
6007, Revision 01; or per the Accomplishment Instructions of A310-
76-2010, Revision 03; as applicable.
Note 1: Airbus Service Bulletins A300-76-6007, Revision 01; and
A310-76-2010, Revision 03; refer to GE CF6-80C2 Service Bulletins
71-088, Revision 03, dated March 15, 1991; and 75-021, Revision 03,
dated August 5, 1992; for additional service information for
accomplishing the installation of a new cooling duct and a new
cooling shroud for the throttle control cable.
(5) For airplanes listed in Airbus Service Bulletin A300-76-
6009, Revision 02, dated October 29, 1999; or A310-76-2012, Revision
02, dated November 5, 2001: Install an elastomer plug filled with
grease on the end fitting of the throttle control cable in each
engine pylon, per the Accomplishment Instructions of the applicable
service bulletin.
(6) For airplanes listed in Airbus Service Bulletin A310-76-
2004, Revision 03, dated August 23, 2001: Install a sealing sleeve
(also called a sealing boot) on the flexible control ball joint of
the throttle control cable in each engine pylon (including a
detailed inspection for deterioration of the throttle control cable,
and replacement of the throttle control cable, as applicable) by
doing all actions in the Accomplishment Instructions of the service
bulletin, per the Accomplishment Instructions of the service
bulletin. Replacement of the throttle control cable, if required,
must be accomplished before further flight.
Note 2: 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.''
Accomplishment of Required Actions per Previous Service Bulletin
Revisions
(b) Actions accomplished before the effective date of this AD
per previous service bulletin revisions are acceptable for
compliance with paragraph (a) of this AD; as specified in paragraph
(b)(1), (b)(2), (b)(3), (b)(4), (b)(5), and (b)(6) of this AD; as
applicable.
(1) Accomplishment of the installation required by paragraph
(a)(1) of this AD per Airbus Service Bulletin A300-76-007, Revision
05, dated March 14, 2000; is acceptable for compliance with
paragraph (a)(1) of this AD.
(2) Accomplishment of the replacement required by paragraph
(a)(2) of this AD per Airbus Service Bulletin A300-76-0015, Revision
01, dated March 14, 2000, is acceptable for compliance with
paragraph (a)(2) of this AD.
(3) Accomplishment of the replacement required by paragraph
(a)(3) of this AD per Airbus Service Bulletin A300-76-016, Revision
02, dated March 14, 2000; or A300-76-6002, Revision 01, dated March
14, 2000; as applicable; is acceptable for compliance with paragraph
(a)(3) of this AD.
(4) Accomplishment of the installation required by paragraph
(a)(4) of this AD per Airbus Service Bulletin A310-76-2010, Revision
02, dated March 14, 2000, is acceptable for compliance with
paragraph (a)(4) of this AD.
[[Page 61772]]
(5) Accomplishment of the installation required by paragraph
(a)(5) of this AD per Airbus Service Bulletin A300-76-6009, Revision
01, dated March 5, 1999; or A310-76-2012, Revision 01, dated March
5, 1999; as applicable; is acceptable for compliance with paragraph
(a)(5) of this AD.
(6) Accomplishment of all actions required by paragraph (a)(6)
of this AD (including a detailed inspection for deterioration of the
throttle control cable, and replacement of the throttle control
cable, as applicable) per Airbus Service Bulletin A310-76-2004,
Revision 02, dated March 14, 2000, is acceptable for compliance with
paragraph (a)(6) of this AD.
Repetitive Inspections and Corrective Actions if Necessary
(c) For airplanes listed in Airbus Service Bulletin A300-76-
6003, Revision 04, dated February 26, 2002; or A310-76-2006,
Revision 03, dated February 26, 2002: Within 500 flight hours after
the effective date of this AD, do the inspections and corrective
actions, as applicable, required by paragraphs (c)(1) and (c)(2) of
this AD, according to the Accomplishment Instructions of the
applicable service bulletin. Repeat the inspections and corrective
actions, as applicable, thereafter at intervals not to exceed 2,000
flight hours, until paragraph (d) of this AD is accomplished.
Although Airbus Service Bulletins A300-76-6003, Revision 04, and
A310-76-2006, Revision 03, specify to submit certain information to
the manufacturer, this AD does not include such a requirement.
(1) Perform a detailed inspection to detect discrepancies of the
throttle control cable (also called the ``push-pull'' cable) and the
rack-box connection in each engine pylon, especially in the area of
the cable guide having part number 221-1325-501. Discrepancies
include excessive wear, damage, chafing of the cable in the area of
a cable guide, backlash outside limits specified in the service
bulletin, or excessive play. If any discrepancy is found, before
further flight, replace the throttle control cable or the rack-box,
as applicable, per the applicable service bulletin.
(2) Perform a detailed inspection for wear or play of the power
lever of the hydromechanical control in the area where the rack-box
drive tang is installed in the power lever. If any wear or play is
found, before further flight, tighten the drive tang expansion screw
to take up play, per the applicable service bulletin.
Accomplishment of Required Actions per Previous Service Bulletin
Revisions
(d) Inspections and corrective actions accomplished before the
effective date of this AD per Airbus Service Bulletin A300-76-6003,
Revision 02, dated June 5, 2000; or Revision 03, dated November 9,
2000; or A310-76-2006, Revision 02, dated June 5, 2000; as
applicable; are acceptable for compliance with paragraph (c) of this
AD.
Optional Terminating Action
(e) Replacement of the existing throttle control cable assembly
with a new improved assembly, per the Accomplishment Instructions of
Airbus Service Bulletin A300-76-6004, Revision 01, dated October 11,
2000; or A310-76-2007, Revision 02, dated November 24, 1988; as
applicable; constitutes terminating action for the repetitive
inspections required by paragraph (c) of this AD.
Alternative Methods of Compliance
(f) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, is authorized
to approve alternative methods of compliance for this AD.
Note 3: The subject of this AD is addressed in French
airworthiness directive 2001-072(B) R2, dated January 23, 2002.
Issued in Renton, Washington, on October 24, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-27323 Filed 10-29-03; 8:45 am]
BILLING CODE 4910-13-P