[Federal Register Volume 68, Number 103 (Thursday, May 29, 2003)]
[Proposed Rules]
[Pages 31991-31994]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-13389]


 ========================================================================
 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. 68, No. 103 / Thursday, May 29, 2003 / 
Proposed Rules  

[[Page 31991]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-187-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 and A340 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 all Airbus Model A330 and A340 
series airplanes. This proposal would require, among other actions, a 
detailed inspection of the rudder travel limitation unit for proper 
adjustment, measurement of the desynchronization of rudder servo-
controls, installation of rigging placards for rudder servo-controls, 
and follow-on and corrective actions, if necessary. This action is 
necessary to prevent desynchronization of the rudder servo-controls, 
which could result in high load factors on the rudder servo-controls, 
and consequent reduced structural integrity of the attachment fittings 
for the rudder servo-controls. This action is intended to address the 
identified unsafe condition.

DATES: Comments must be received by June 30, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-187-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: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-187-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: 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 Docket Number 2001-NM-187-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-187-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 all Airbus Model A330 and A340 series 
airplanes. The DGAC advises that it has received several reports of 
abnormal stiff application of the rudder pedal in flight and during 
ground tests. Investigation revealed cracks on the attachment fittings 
for the blue rudder servo-controls and on the spherical bearing of the 
tail lock for the blue rudder servo-controls. Also, the actuating 
spring rod of the blue rudder servo-controls was found to be shorter 
than the actuating spring rods of the yellow and green rudder servo-
controls, which resulted in desynchronization of the rudder servo-
controls. The high load factors induced by the desynchronization caused 
the cracks on the attachment fittings for the servo-controls and 
spherical bearing. The desynchronization was caused by deviation from 
the procedures for adjusting actuating spring rods of the rudder servo-
controls. This condition, if not corrected, could result in high load 
factors on the rudder servo-controls, and consequent reduced structural 
integrity of the attachment fittings for the rudder servo-controls.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A330-27-3084 (for Model A330 
series airplanes); and Service Bulletin A340-27-4088 (for Model A340 
series airplanes); both dated March 28, 2001. These service bulletins 
describe

[[Page 31992]]

procedures for performing a detailed inspection of the rudder travel 
limitation unit (RTLU) for proper adjustment, and measuring 
desynchronization of the rudder servo-controls. The inspection of the 
RTLU includes installing rigging pins on the bellcrank and right and 
left input levers and, if necessary, adjusting the length of the 
applicable adjustable rod. Measurement of the rudder servo-controls for 
desynchronization includes disconnecting the control rod from the 
bellcrank; installing a rigging pin on the bellcrank assembly of the 
lower servo-controls; pressurizing and depressurizing the blue, yellow, 
and green hydraulic systems at the appropriate times; recording the 
results; if desynchronization is found, determining if the value is 
within the acceptable limits specified in the service bulletins; 
replacing or adjusting the actuating spring rods and affected rudder 
servo-controls; and returning replaced rudder servo-controls with the 
highest load factors to the manufacturer; as applicable.
    For airplanes on which any rudder servo-control has been replaced 
per Service Bulletin A330-27-3084 or Service Bulletin A340-27-4088, 
Airbus has also issued Service Bulletin A330-55-3028 (for Model A330 
series airplanes); and Service Bulletin A340-55-4026 (for Model A340 
series airplanes); including Appendix 01; dated May 28, 2001. These 
service bulletins describe procedures for a detailed or high frequency 
eddy current inspection of the attachment fittings of desynchronized 
rudder servo-controls for cracks. The service bulletins describe 
procedures for follow-on actions (including additional detailed 
inspections in the area of the fasteners and attachment fittings; 
additional high frequency eddy current inspections; cold expansion of 
specific fastener holes; drilling/reaming and cleaning of specific 
fastener holes; rotating probe inspections; and wet installation of 
pins, collars, and oversize fasteners) depending on airplane 
configuration; as applicable; and repetitive inspections. The service 
bulletins also state that if any crack is found, operators should 
contact Airbus for repair instructions.
    For certain Model A330 series airplanes, Airbus Service Bulletin 
A330-27-3084 recommends concurrent accomplishment of Airbus Service 
Bulletin A330-27-3082, dated March 28, 2001. Service Bulletin A330-27-
3082 describes procedures for installing rigging placards for the 
rudder servo-controls (including bonding placards to the appropriate 
areas and coating them with lacquer).
    For certain Model A340 series airplanes, Airbus Service Bulletin 
A340-27-4088 recommends concurrent accomplishment of Airbus Service 
Bulletin A340-27-4086, dated March 28, 2001. Service Bulletin A340-27-
4086 describes procedures for installing rigging placards for the 
rudder servo-controls (including bonding placards to the appropriate 
areas and coating them with lacquer).
    Accomplishment of the actions specified in these service bulletins 
is intended to adequately address the identified unsafe condition. The 
DGAC classified these service bulletins as mandatory and issued French 
airworthiness directives 2001-156(B) and 2001-157(B), both dated May 2, 
2001, in order to assure 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 the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
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 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 applicable service bulletins described 
previously, except as discussed below.

Differences Between Foreign Airworthiness Directives, Service 
Bulletins, and Proposed AD

    Operators should note that although French airworthiness directives 
2001-156(B) and 2001-157(B); and Airbus Service Bulletins A330-55-3028 
(for Model A330 series airplanes) and A340-55-4026 (for Model A340 
series airplanes); include instructions for reporting inspection 
results and returning desynchronized rudder servo-controls with the 
highest load factors to Airbus, this proposed AD would not require 
those actions.
    Operators should also note that, although Airbus Service Bulletins 
A330-55-3028 and A340-55-4026 specify that the manufacturer may be 
contacted for certain repair instructions, this proposal would require 
the repair be accomplished in accordance with a method approved by 
either the FAA, or the DGAC (or its delegated agent). In light of the 
type of repair that would be required to address the identified unsafe 
condition, and in consonance with existing bilateral airworthiness 
agreements, the FAA has determined that, for this proposed AD, a repair 
approved by either the FAA or the DGAC (or its delegated agent) would 
be acceptable for compliance with this proposed AD.

Cost Impact

    The FAA estimates that 9 Model A330 series airplanes of U.S. 
registry would be affected by this proposed AD, that it would take 6 
work hours per airplane to accomplish the proposed inspection and 
measurement, and 1 work hour per airplane to accomplish the proposed 
installation of the rigging placards, and that the average labor rate 
is $60 per work hour. Required rigging placards would be provided to 
the operators at no cost. Based on these figures, the cost impact of 
the proposed AD on U.S. operators is estimated to be $3,780, or $420 
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 proposed 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.
    Currently, there are no Airbus Model A340 series airplanes on the 
U.S. Register. However, should an affected airplane be imported and 
placed on the U.S. Register in the future, it would require 6 work 
hours per airplane to accomplish the proposed inspection and 
measurement, and 1 work hour per airplane to accomplish the proposed 
installation of the rigging placards, at an average labor rate of $60 
per work hour. Required placards would be provided to the operators at 
no cost. Based on these figures, the cost impact of the proposed AD for 
Model A340 operators would be $420 per airplane.

[[Page 31993]]

Regulatory Impact

    The regulations proposed herein would not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the 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-187-AD.

    Applicability: Model A330 and A340 series airplanes, 
certificated in any category; except those airplanes modified in 
production in accordance with Airbus Modification 48110.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (e) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent desynchronization of the rudder servo-controls, which 
could result in high load factors on the rudder servo-controls, and 
consequent reduced structural integrity of the attachment fittings 
for the rudder servo-controls, accomplish the following:

Inspection of Rudder Travel Limitation Unit

    (a) Within 16 months after the effective date of this AD: 
Perform a one-time detailed inspection of the rudder travel 
limitation unit (RTLU) (including installing rigging pins on the 
bellcrank and the right and left input levers) for proper 
adjustment, per the Accomplishment Instructions specified in Airbus 
Service Bulletin A330-27-3084 (for Model A330 series airplanes); or 
Airbus Service Bulletin A340-27-4088 (for Model A340 series 
airplanes); both dated March 28, 2001; as applicable. Although the 
service bulletins reference a reporting requirement, such reporting 
is not required by this AD.
    (1) If it is possible to install rigging pins on both input 
levers, the RTLU is properly adjusted and no further action is 
required by this paragraph.
    (2) If it is not possible to install the rigging pins on either 
input lever, before further flight, adjust the length of the 
appropriate adjustable rod, per the Accomplishment Instructions 
specified in the applicable service bulletin.

    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.''

Measurement of Rudder Servo-Controls Desynchronization and Corrective 
Action if Necessary

    (b) Within 16 months after the effective date of this AD: 
Measure the desynchronization value (value D) of the rudder servo-
controls and, depending on the measurement, before further flight, 
perform the applicable corrective actions (e.g., replacement and/or 
adjustment of the spring rod and/or the rudder servo-controls); per 
the Accomplishment Instructions specified in Airbus Service Bulletin 
A330-27-3084 (for Model A330 series airplanes); or Airbus Service 
Bulletin A340-27-4088 (for Model A340 series airplanes); both dated 
March 28, 2001; as applicable. Operators should note that although 
these service bulletins request that desynchronized rudder servo-
controls with the highest load factors be returned to the 
manufacturer, that action is not required by this AD.
    (c) If any rudder servo-control was replaced per the 
requirements of paragraph (b) of this AD, do paragraphs (c)(1) and 
(c)(2) of this AD.
    (1) Before further flight, perform either a detailed inspection 
or a high frequency eddy current (HFEC) inspection for cracks in the 
attachment fittings of the desynchronized rudder servo-controls, and 
perform the applicable follow-on and corrective actions (e.g., cold 
expansion of affected fastener holes, drilling/reaming of affected 
holes, and rotating probe inspections), per the Accomplishment 
Instructions specified in Airbus Service Bulletin A330-55-3028 (for 
Model A330 series airplanes); or Airbus Service Bulletin A340-55-
4026 (for Model A340 series airplanes); excluding Appendix 01; dated 
May 28, 2001; as applicable; except where the service bulletin 
specifies to contact the manufacturer for repair instructions, 
repair per a method approved by the Manager, International Branch, 
ANM-116, FAA.
    (2) Repeat the inspection required by paragraph (c)(1) of this 
AD at the following intervals:
    (i) If the immediately preceding inspection was conducted using 
detailed inspection techniques, conduct the next inspection within 
300 flight cycles; or
    (ii) If the immediately preceding inspection was conducted using 
HFEC techniques, conduct the next inspection within 6,000 flight 
cycles.

Concurrent Requirements

    (d) Concurrently with the requirements of paragraphs (a) and (b) 
of this AD, install appropriate rigging placards for the rudder 
servo-controls, per Airbus Service Bulletin A330-27-3082 (for Model 
A330 series airplanes); or Airbus Service Bulletin A340-27-4086 (for 
Model A340 series airplanes); both dated March 28, 2001; as 
applicable.

Alternative Methods of Compliance

    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, International 
Branch, ANM-116.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (f) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

    Note 4: The subject of this AD is addressed in French 
airworthiness directives 2001-156(B) and 2001-157(B), both dated May 
2, 2001.



[[Page 31994]]


    Issued in Renton, Washington, on May 21, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-13389 Filed 5-28-03; 8:45 am]
BILLING CODE 4910-13-P