[Federal Register Volume 69, Number 75 (Monday, April 19, 2004)]
[Rules and Regulations]
[Pages 20811-20815]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-8544]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-216-AD; Amendment 39-13578; AD 2004-08-09]
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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
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 AD requires 
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: Effective May 24, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 24, 2004.

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

FOR FURTHER INFORMATION CONTACT: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an 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; was published in the Federal Register on October 30, 2003 
(68 FR 61768). That action proposed to require various modifications 
and repetitive inspections of the throttle control system, and follow-
on actions if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. The FAA has given due consideration to 
the comments received.
    One commenter states that it will not be affected by the proposed 
AD.

Request To Revise Repetitive Inspection Interval

    One commenter requests that we revise the interval for the 
repetitive inspections in the proposed AD from 500 flight hours to 500 
flight cycles. The commenter's rationale is that it anticipates 
significant economic or operational impact due to incorporation of the 
requirements of the proposed AD.

[[Page 20812]]

    We do not concur because we find that we do not need to revise this 
final rule to meet the intent of the commenter's request. While the 
initial inspection is required within 500 flight hours after the 
effective date of this AD, the repetitive inspections are required at 
intervals not to exceed 2,000 flight hours. No change to the final rule 
is necessary.

Request To Consider Parts Availability

    The same commenter requests that we consider the availability of 
the parts necessary to accomplish the terminating action--replacement 
of the existing throttle control cable assembly with a new, improved 
assembly. The commenter states that, in the past, necessary parts have 
been unavailable from the manufacturer.
    We do not concur. The terminating action stated in paragraph (e) of 
this AD is optional. Therefore, there is no compliance time constraint 
in which parts availability should be a factor. No change to the final 
rule is necessary.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    The table below contains the FAA's estimates of the cost impact of 
the actions that are required by this AD on U.S. operators, at an 
average labor rate of $65 per work hour.

                                     Cost Impact: U.S.-Registered Airplanes
----------------------------------------------------------------------------------------------------------------
                                                                     Estimated
    Actions in Airbus service                                        number of    Estimated cost     Estimated
           bulletin--               Work hours      Parts cost     airplanes of    per airplane     fleet cost
                                                                   U.S. registry
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------

    Currently, there are no airplanes on the U.S. Register that are 
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 will be required by this 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
----------------------------------------------------------------------------------------------------------------
   Airplanes subject to the actions in Airbus service                                            Estimated cost
                       bulletin--                            Work hours         Parts cost        per airplane
----------------------------------------------------------------------------------------------------------------
A300-76-6003, Revision 04..............................                  2                 $0               $130
A310-76-2010, Revision 03..............................                  8                  0                520
----------------------------------------------------------------------------------------------------------------

    If an operator chooses to do the optional terminating action in 
Airbus Service Bulletin A300-76-6004, Revision 01, or A310-76-2007, 
Revision 2; 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 requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

[[Page 20813]]

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-08-09 Airbus: Amendment 39-13578. Docket 2001-NM-216-AD

    .Applicability: Airplanes as listed in Table 1 of this AD, 
certificated in any category.

                                             Table 1.--Applicability
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           Airplane models                              As listed in Airbus Service 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, and 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, dated October 29, 1999.
 605R Variant F.
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 3, dated March 15, 1991; and 75-021, Revision 3, 
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 and 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 installation 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.
    (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;

[[Page 20814]]

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 (e) 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 2, 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.

Incorporation by Reference

    (g) Unless otherwise specified in this AD, the actions shall be 
done in accordance with the applicable service bulletins listed in 
Table 2 of this AD. Table 2 of this AD follows:

          Table 2.--Service Bulletins Incorporated by Reference
------------------------------------------------------------------------
 Airbus service
    bulletin               Revision                      Date
------------------------------------------------------------------------
   A300-76-0007  Revision 06................  August 23, 2001.
   A300-76-0015  Revision 02................  August 23, 2001.
   A300-76-0016  Revision 03................  August 23, 2001.
   A300-76-6002  Revision 02................  August 23, 2001.
   A300-76-6003  Revision 04................  February 26, 2002.
   A300-76-6004  Revision 01................  October 11, 2000.
   A300-76-6007  Revision 01................  March 14, 2000.
   A300-76-6009  Revision 02................  October 29, 1999.
   A310-76-2001  Revision 01................  March 14, 2000.
   A310-76-2004  Revision 03................  August 23, 2001.
   A310-76-2005  Revision 01................  March 14, 2000.
   A310-76-2006  Revision 03................  February 26, 2002.
   A310-76-2007  Revision 2.................  November 24, 1988.
   A310-76-2010  Revision 03................  August 23, 2001.
   A310-76-2012  Revision 02................  November 5, 2001.
------------------------------------------------------------------------

    Airbus Service Bulletin A310-76-2005, Revision 01, contains the 
following effective pages:

------------------------------------------------------------------------
                                    Revision level
           Page number               shown on page    Date shown on page
------------------------------------------------------------------------
1-5.............................  01................  March 14, 2000.
6-11............................  Original..........  November 26, 1985.
------------------------------------------------------------------------

    Airbus Service Bulletin A300-76-6004, Revision 01, contains the 
following effective pages:

------------------------------------------------------------------------
                                    Revision level
           Page number               shown on page    Date shown on page
------------------------------------------------------------------------
1-3, 5..........................  01................  October 11, 2000.
4, 6-21.........................  Original..........  October 22, 1986.
------------------------------------------------------------------------

    Airbus Service Bulletin A310-76-2007, Revision 2, contains the 
following effective pages:

------------------------------------------------------------------------
                                    Revision level
           Page number               shown on page    Date shown on page
------------------------------------------------------------------------
1, 2, 11........................  2.................  November 24, 1988.
3-5, 9, 10, 19-21...............  1.................  November 19, 1986.
6-8, 12-18......................  Original..........  September 30,
                                                       1986.
------------------------------------------------------------------------

    This incorporation by reference was approved by the Director of 
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from Airbus, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 2001-072(B) R2, dated January 23, 2002.

Effective Date

    (h) This amendment becomes effective on May 24, 2004.



[[Page 20815]]

Issued in Renton, Washington, on April 6, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-8544 Filed 4-16-04; 8:45 am]
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