[Federal Register Volume 70, Number 64 (Tuesday, April 5, 2005)]
[Proposed Rules]
[Pages 17212-17215]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-6678]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 70, No. 64 / Tuesday, April 5, 2005 / 
Proposed Rules  

[[Page 17212]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20794; Directorate Identifier 2004-NM-172-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, 
and Model C4-605R Variant F Airplanes (Collectively Called A300-600 
Series Airplanes); and Model A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to all Airbus Model A300 B2 and B4 series 
airplanes; Model A300-600 series airplanes; and Model A310 series 
airplanes. The existing AD currently requires, among other actions, 
repetitive tests to detect desynchronization of the rudder servo 
actuators, and adjustment or replacement of the spring rods of the 
rudder servo actuators, if necessary. This proposed AD would require 
new repetitive tests/inspections/analyses of the rudder servo 
actuators, and related investigative/corrective actions if necessary. 
Accomplishment of the new actions ends the existing repetitive 
requirements. This proposed AD is prompted by new reports of 
desynchronization of the rudder servo actuators. We are proposing this 
AD to prevent desynchronization of one of the three rudder servo 
actuators, which, if combined with an engine failure could result in 
the loss of the related hydraulic system and could cause the loss of 
one of the two synchronized actuators. This condition could create 
additional fatigue loading and possible cracking on the attachment 
fittings and could result in the inability of the remaining 
synchronized actuator to maintain the commanded rudder deflection, 
which could result in reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by May 5, 2005.

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 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. This docket 
number is FAA-2005-20794; the directorate identifier for this docket is 
2004-NM-172-AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20794; 
Directorate Identifier 2004-NM-172-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 
can visit http://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://dms.dot.gov, or 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 June 16, 1998, we issued AD 98-13-33, amendment 39-10624 (63 FR 
34580, June 25, 1998), for all Airbus Model A300 B2 and B4 series 
airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, 
and Model C4-605R variant F airplanes (collectively called A300-600 
series airplanes); and Model A310 series airplanes. That AD requires 
repetitive tests to detect desynchronization of the rudder servo 
actuators, and adjustment or replacement of the spring rods of the 
rudder servo actuators, if necessary. For certain airplanes, that AD 
also requires repetitive inspections to detect cracking of the rudder 
attachments, and repair, if necessary; or modification of the rudder 
attachments. That AD was prompted by issuance of mandatory continuing 
airworthiness information by an international civil airworthiness

[[Page 17213]]

authority. We issued that AD to detect and correct desynchronization of 
the rudder servo actuators, which could result in reduced structural 
integrity of the rudder attachments and reduced controllability of the 
airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 98-13-33, the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, notified us that there have been new reports of 
desynchronization of the rudder servo actuators on in-service 
airplanes. The primary cause, which is not addressed by AD 98-13-33, is 
a malfunction or mis-adjustment of the input spring rods of the rudder 
servo actuators. With the hydraulic systems of all three rudder servo 
actuators pressurized, one desynchronized actuator, while having no 
noticeable effect on the operation of the rudder, could create an 
opposing force. This force is reacted by the structural attachments of 
the actuators and creates additional fatigue loading and possible 
cracking on the attachment fittings.
    If a desynchronized rudder servo actuator is combined with an 
engine failure, the loss of the related hydraulic system could cause 
the loss of one of the two synchronized actuators. This condition could 
create additional fatigue loading and possible cracking on the 
attachment fittings and could result in the inability of the remaining 
synchronized actuator to maintain the commanded rudder deflection, 
which could result in reduced controllability of the airplane.

Relevant Service Information

    Airbus has issued the following primary service bulletins:

                                            Primary Service Bulletins
----------------------------------------------------------------------------------------------------------------
        Airbus service bulletin--                                          For--
----------------------------------------------------------------------------------------------------------------
A300-27-0188, Revision 05, including       Model A300 B2 and B4 series airplanes.
 Appendix 01 and Reporting Sheet, dated
 April 16, 2004.
A300-27-6036, Revision 08, including       Model A300-600.
 Appendix 01 and Reporting Sheet, dated
 April 16, 2004.
A310-27-2082, Revision 05, including       Model A310 series airplanes.
 Appendix 01 and Reporting Sheet, dated
 April 16, 2004.
----------------------------------------------------------------------------------------------------------------

    The primary service bulletins describe the following procedures:
    1. Doing repetitive operational tests of the rudder system with 
each hydraulic system pressurized in turn;
    2. Doing repetitive static inspections for correct synchronization 
of the rudder servo controls with each hydraulic system;
    3. Doing repetitive inspections to find dead travel of the input 
lever of the rudder servo control for each hydraulic system;
    4. Analyzing the results of each inspection;
    5. Submitting a report to the airplane manufacturer; and
    6. Doing any applicable related investigative/corrective actions if 
necessary. The related investigative actions include doing inspections 
of the attachment fittings of the rudder servo actuators for cracks 
when the limits are exceeded in accordance with the applicable 
secondary service bulletin described below, and contacting the airplane 
manufacturer for disposition of repairs if necessary. The corrective 
actions include adjusting the spring rods, replacing the spring rods 
with new spring rods, and replacing the rudder servo control with a new 
servo control.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information and issued French airworthiness directive F-
2004-092, issued June 23, 2004, to ensure the continued airworthiness 
of these airplanes in France.
    The primary service bulletins refer to the following secondary 
service bulletins as additional sources of service information for 
accomplishing the related investigative actions for certain conditions:

                                           Secondary Service Bulletins
----------------------------------------------------------------------------------------------------------------
        Airbus service bulletin--                                          For--
----------------------------------------------------------------------------------------------------------------
A300-55-0044, Revision 03, dated April     Model A300 B2 and B4 series airplanes.
 16, 2004.
A310-55-2026, Revision 02, dated April     Model A310 series airplanes.
 16, 2004.
A300-55-6023, Revision 05, dated April     Model A300-600.
 16, 2004.
----------------------------------------------------------------------------------------------------------------

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 
Sec.  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.
    This proposed AD would supersede AD 98-13-33. This proposed AD 
would retain the requirements of the existing AD. This proposed AD 
would also require accomplishing the actions specified in the primary 
service bulletins described previously, except as discussed under 
``Differences Between the Proposed AD and Primary Service Bulletins.''

Differences Between the Proposed AD and the Primary Service Bulletins

    The primary service bulletins specify that you may contact the 
airplane manufacturer for instructions on how to repair certain 
conditions, but this proposed AD would require you to repair those 
conditions using a method that we or the DGAC (or its delegated agent) 
approve. In light of the type of repair that would be required to 
address the unsafe condition, and consistent with existing bilateral 
airworthiness agreements, we have determined that, for this proposed 
AD, a repair we or the DGAC approve would be acceptable for compliance 
with this proposed AD.

Change to Existing AD

    This proposed AD would retain all requirements of AD 98-13-33. 
Since AD

[[Page 17214]]

98-13-33 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
------------------------------------------------------------------------
                                             Corresponding  requirement
        Requirement in AD 98-13-33              in this  proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (f).
paragraph (b).............................  paragraph (g).
paragraph (c).............................  paragraph (h).
------------------------------------------------------------------------

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. The average labor rate is $65 per 
hour.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                     Cost per     Number of U.S.-
              Action                  Work hour        Parts      airplane,  per    registered      Fleet cost
                                                                       cycle         airplanes      (per cycle)
----------------------------------------------------------------------------------------------------------------
Tests (required by AD 98-13-13)..               1  None.........             $65             179         $11,635
Tests/inspections/analyses (new                 1  None.........              65             179          11,635
 proposed actions).
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

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 39-10624 (63 FR 
34580, June 25, 1998) and adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2005-20794; Directorate Identifier 2004-NM-
172-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by May 5, 2005.

Affected ADs

    (b) This AD supersedes AD 98-13-33, amendment 39-10624 (63 FR 
34580, June 25, 1998).

Applicability

    (c) This AD applies to all Airbus Model A300 B2 and B4 series 
airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, 
and Model C4-605R Variant F airplanes (collectively called A300-
600); and Model A310 series airplanes; certificated in any category.

Unsafe Condition

    (d) This AD was prompted by new reports of desynchronization of 
the rudder servo actuators. We are issuing this AD to prevent 
desynchronization of one of three rudder servo actuators, which, if 
combined with an engine failure, could result in the loss of the 
related hydraulic system and could cause the loss of one of the two 
synchronized actuators. This condition could create additional 
fatigue loading and possible cracking on the attachment fittings and 
could result in the inability of the remaining synchronized actuator 
to maintain the commanded rudder deflection, which could result in 
reduced controllability 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.

Requirements of AD 98-13-33

Repetitive Tests and Adjustment or Replacement

    (f) Prior to accumulation of 1,300 total flight hours, or within 
500 flight hours after July 30, 1998 (the effective date of AD 98-
13-33), whichever occurs later, and thereafter at intervals not to 
exceed 1,300 flight hours: Perform a test to detect 
desynchronization of the rudder servo actuators in accordance with 
Airbus Service Bulletin A300-27-0188, Revision 2, dated October 1, 
1997 (for Model A300 series airplanes); A300-27-6036, Revision 2, 
dated October 1, 1997 (for Model A300-600 series airplanes); or 
A310-27-2082, Revision 2, dated October 1, 1997 (for Model A310 
series airplanes); as applicable. If any desynchronization (rudder 
movement) is detected, prior to further flight, either adjust or 
replace, as applicable, the spring rod of the affected rudder servo 
actuator in accordance with the applicable service bulletin.

    Note 1: A test to detect desynchronization of the rudder servo 
actuators, if accomplished prior to the effective date of this AD in 
accordance with Airbus Service Bulletin A300-27-0188, dated October 
24, 1996, or Revision 1, dated November 5, 1996 (for Model A300 
series airplanes); A300-27-6036, dated October 24, 1996, or Revision 
1, dated November 5, 1996 (for Model A300-600 series airplanes); or 
A310-27-2082, dated October 24, 1996, or Revision 1, dated November 
5, 1996 (for Model A310 series airplanes); is considered acceptable 
for

[[Page 17215]]

compliance with the initial test required by paragraph (f) of this 
AD.

    (g) Except as provided by paragraph (h) of this AD, if any 
desynchronization (rudder movement) greater than the limit specified 
in Paragraph B of the Accomplishment Instructions of the applicable 
service bulletin is detected during any test required by paragraph 
(f), prior to further flight, accomplish either paragraph (g)(1) or 
(g)(2) of this AD, in accordance with Airbus Service Bulletin A300-
55-0044, dated October 22, 1996 (for Model A300 series airplanes); 
A300-55-6023, dated October 22, 1996 (for Model A300-600 series 
airplanes); or A310-55-2026, dated October 22, 1996 (for Model A310 
series airplanes); as applicable.
    (1) Conduct a visual inspection, high frequency eddy current 
inspection, or ultrasonic inspection, as applicable, to detect 
cracking of the rudder attachments; and repeat the inspection 
thereafter, as applicable, at the intervals specified in the 
applicable service bulletin. Or
    (2) Modify the rudder attachments to cold expand the rivet 
holes.
    (h) If any crack is found during any inspection or modification 
required by paragraph (g) of this AD, and the applicable service 
bulletin specifies to contact Airbus for an appropriate action: 
Prior to further flight, repair the affected structure in accordance 
with a method approved by the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate, or in accordance with a 
method approved by the Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC).

New Requirements of This AD

Service Bulletins

    (i) The term ``primary service bulletin,'' as hereafter used in 
this AD, means the Accomplishment Instructions of the applicable 
primary service bulletin in Table 1 of this AD.

                                       Table 1.--Primary Service Bulletins
----------------------------------------------------------------------------------------------------------------
        Airbus service bulletin--                                          For--
----------------------------------------------------------------------------------------------------------------
(1) A300-27-0188, including Appendix 01    Model A300 B2 and B4 series airplanes.
 and Reporting Sheet, Revision 05, dated
 April 16, 2004.
(2) A300-27-6036, including Appendix 01    Model A300-600 series airplanes.
 and Reporting Sheet, Revision 08, dated
 April 16, 2004.
(3) A310-27-2082, including Appendix 01    Model A310 series airplanes.
 and Reporting Sheet, Revision 05, dated
 April 16, 2004.
----------------------------------------------------------------------------------------------------------------

    (j) The primary service bulletin refers to the applicable 
secondary service bulletin in Table 2 of this AD as an additional 
source of service information for accomplishing the related 
investigative actions for certain conditions.

                                      Table 2.--Secondary Service Bulletins
----------------------------------------------------------------------------------------------------------------
        Airbus service bulletin--                                          For--
----------------------------------------------------------------------------------------------------------------
(1) A300-55-0044, Revision 03, dated       Model A300 B2 and B4 series airplanes.
 April 16, 2004.
(2) A310-55-2026, Revision 02, dated       Model A310 series airplanes.
 April 16, 2004.
(3) A300-55-6023, Revision 05, dated       Model A300-600 series airplanes.
 April 16, 2004.
----------------------------------------------------------------------------------------------------------------

Compliance Times

    (k) Do the actions specified in paragraph (l) of this AD at the 
following times:
    (1) Within 700 flight hours after the effective date of this AD 
or within 1,300 flight hours after the last inspection required by 
either paragraph (f) or (g) of this AD, whichever occurs first; and
    (2) Thereafter at intervals not to exceed 1,300 flight hours.

Tests/Inspections/Analyses and Related Investigative/Corrective 
Actions

    (l) Do the actions specified in paragraphs (l)(1) through (l)(4) 
of this AD and any applicable related investigative/corrective 
actions by doing all the actions in accordance with the primary 
service bulletin, except as required by paragraph (m) of this AD. 
Related investigative and corrective actions must be done before 
further flight. Accomplishing these actions ends the requirements of 
paragraphs (f) through (h) of this AD.
    (1) Do an operational test of the rudder system with each 
hydraulic system pressurized in turn.
    (2) Do a static inspection for correct synchronization of the 
rudder servo controls with each hydraulic system.
    (3) Inspect to find dead travel of the input lever of the rudder 
servo control for each hydraulic system.
    (4) Analyze the results of the static inspection required by 
paragraph (l)(2) of this AD and the inspection to find dead travel 
required by paragraph (l)(3) of this AD.
    (m) If the primary/secondary service bulletin recommends 
contacting Airbus for appropriate action: Before further flight, 
repair any discrepancy in accordance with a method approved by 
either the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate; or the DGAC (or its delegated agent).

Reporting

    (n) At the applicable time specified in paragraph (n)(1) or 
(n)(2) of this AD, submit a report in accordance with the primary 
service bulletin. Under the provisions of the Paperwork Reduction 
Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and 
Budget (OMB) has approved the information collection requirements 
contained in this AD and has assigned OMB Control Number 2120-0056.
    (1) If the action specified in the primary service bulletin was 
done after the effective date of this AD: Submit the report within 
30 days after the inspection.
    (2) If the action specified in the primary service bulletin was 
accomplished before the effective date of this AD: Submit the report 
within 30 days after the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) AMOCs approved previously according to AD 98-13-33 are not 
approved as AMOCs with this AD.

Related Information

    (p) French airworthiness directive F-2004-092, issued June 23, 
2004, also addresses the subject of this AD.

    Issued in Renton, Washington, on March 22, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-6678 Filed 4-4-05; 8:45 am]
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