[Federal Register Volume 66, Number 209 (Monday, October 29, 2001)]
[Rules and Regulations]
[Pages 54416-54418]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-26860]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-300-AD; Amendment 39-12481; AD 2001-22-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Airbus Model A300 B2 and B4 series airplanes. 
This action requires determining the part and amendment numbers of the 
variable lever arm (VLA) of the rudder control system to verify the 
parts were installed using the correct standard, and corrective 
actions, if necessary. This action is necessary to prevent failure of 
both spring boxes of the VLA due to corrosion damage, which could 
result in loss of rudder control and consequent reduced controllability 
of the airplane. This action is intended to address the identified 
unsafe condition.

DATES: Effective November 13, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 13, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before November 28, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-300-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 the Internet must contain 
``Docket No. 2001-NM-300-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via fax or the Internet as 
attached electronic files must be formatted in Microsoft Word 97 for 
Windows or ASCII text.
    The service information referenced in this AD 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; 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: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, recently 
notified the FAA that an unsafe condition may exist on certain Airbus 
Model A300 B2 and B4 series airplanes. The DGAC advises that two 
reports were received which indicated that, during regularly scheduled 
maintenance, damage to the variable lever arm (VLA) of the rudder 
control system was found. Further investigation revealed that the VLA 
spring box mountings, the mounting trunnion, and a tie rod also were 
damaged. Such damage was attributed to corrosion of the spring boxes. 
Both affected spring boxes were installed per the pre-vendor service 
bulletin (VSB) 27-21-1H standard, causing stiff operation of the 
springs and subsequent damage. Failure of one spring box of the VLA 
does not affect safety of flight, but failure of both spring boxes 
could result in loss of rudder control and consequent reduced 
controllability of the airplane.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A300-27A0196, dated 
September 20, 2001, which describes procedures for determining the part 
and amendment numbers of the variable lever arm (VLA) of the rudder 
control system to verify the spring boxes were installed using the 
post-VSB 27-21-1H standard, and corrective actions, if necessary. The 
corrective actions include a detailed visual inspection of the VLA tie 
rod for damage (bent or ruptured rod) if the part and amendment numbers 
of the VLA are incorrect, and replacement of any damaged tie rod with a 
new tie rod.
    The DGAC classified this AOT as mandatory and issued French 
telegraphic airworthiness directive T 2001-447(B), dated September 24, 
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 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, this AD is being issued to

[[Page 54417]]

prevent failure of both spring boxes of the variable lever arm (VLA) 
due to corrosion damage, which could result in jammed rudder pedals, 
loss of rudder control, and consequent reduced controllability of the 
airplane. This AD requires a one-time inspection to determine the part 
number of the VLA of the rudder control system, and follow-on actions, 
if necessary. The actions are required to be accomplished in accordance 
with the AOT described previously.

Interim Action

    This is considered to be interim action. The manufacturer is 
gathering data that will enable it to obtain better insight into the 
nature, cause, and extent of the corrosion damage, and eventually to 
develop final action to address the unsafe condition. Once final action 
has been identified, the FAA may consider further rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
     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.
     For each issue, state what specific change to the AD is 
being requested.
     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 rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-300-AD.'' The postcard will be date stamped 
and returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    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

    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:

2001-22-02  Airbus Industrie: Amendment 39-12481. Docket 2001-NM-
300-AD.

    Applicability: Model A300 B2 and B4 series airplanes, 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (b) 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 failure of both spring boxes of the variable lever 
arm (VLA) due to corrosion damage, which could result in loss of 
rudder control and consequent reduced controllability of the 
airplane, accomplish the following:

Inspection/Corrective Actions

    (a) Within 10 days after the effective date of this AD: 
Determine the part and amendment numbers of the VLA of the rudder 
control system to verify the parts were installed using the correct 
standard, per Airbus All Operators Telex (AOT) A300-27A0196, dated 
September 20, 2001.
    (1) If the part and amendment numbers shown are not correct, as 
specified in the AOT, before further flight, do a detailed visual 
inspection of the VLA tie rod for damage (bent or ruptured rod) per 
the AOT.
    (i) If the tie rod is damaged, replace the VLA with a new VLA 
per the AOT. Such replacement ends the requirements of this AD.
    (ii) If the tie rod is not damaged, no further action is 
required by this AD.
    (2) If the part and amendment numbers shown are correct, no 
further action is required by this AD.

    Note 2: For the purposes of this AD, a detailed visual 
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.''


[[Page 54418]]



Alternative Methods of Compliance

    (b) 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

    (c) 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.

Incorporation by Reference

    (d) The actions shall be done in accordance with Airbus All 
Operators Telex A300-27A0196, dated September 20, 2001. 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 Industrie, 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 4: The subject of this AD is addressed in French 
telegraphic airworthiness directive T 2001-447(B), dated September 
24, 2001.

Effective Date

    (e) This amendment becomes effective on November 13, 2001.

    Issued in Renton, Washington, on October 18, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-26860 Filed 10-26-01; 8:45 am]
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