[Federal Register Volume 69, Number 89 (Friday, May 7, 2004)]
[Proposed Rules]
[Pages 25511-25514]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-10381]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-13-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and A300 B4; Model 
A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R (Collectively 
Called A300-600); 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 all Airbus Model A300 B2 and A300 
B4; Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R 
(collectively called A300-600); and Model A310 series airplanes. This 
proposal would require a detailed inspection of certain pulleys and 
control cables in the rear fuselage for corrosion and damage; and 
corrective action, if necessary. This action is necessary to detect and 
correct frayed or corroded control cables for the elevator and rudder, 
which could result in a ruptured control cable, and possible reduced 
controllability of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Comments must be received by June 7, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-13-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. 2003-NM-13-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, 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:
     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 proposed 
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 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

[[Page 25512]]

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 2003-NM-13-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. 2003-NM-13-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 A300 B2 and A300 B4; 
Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R 
(collectively called A300-600); and Model A310 series airplanes. The 
DGAC advises that, during a scheduled maintenance visit on an A310 
series airplane, an operator found two frayed and corroded elevator 
control cables, and one frayed and corroded rudder control cable in the 
unpressurized stabilizer compartment at the rear of the fuselage. This 
condition, if not corrected, could result in a ruptured control cable, 
and possible reduced controllability of the airplane.
    The subject area on certain Model A300 B2 and A300 B4; and Model 
A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R (collectively 
called A300-600) series airplanes is almost identical to that on the 
affected Model A310 series airplane. Therefore, those Model A300 B2 and 
A300 B4; and Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R 
(collectively called A300-600) series airplanes may be subject to the 
same unsafe condition revealed on the Model A310 series airplanes.

Explanation of Relevant Service Information

    Airbus has issued the following service bulletins.
     For Model A300 B2 and A300 B4 series airplanes: Airbus 
Service Bulletin A300-27A0197, Revision 01, including Appendix 01, 
dated February 26, 2003;
     For Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-
600R (collectively called A300-600) series airplanes: Airbus Service 
Bulletin A300-27A6051, including Appendix 01, dated August 8, 2002; and
     For Model A310 series airplanes: Airbus Service Bulletin 
A310-27A2098, including Appendix 01, dated August 8, 2002.
    These service bulletins describe procedures for a one-time visual 
inspection for corrosion and damage (e.g., frayed or broken wires) of 
the pulleys and cables of the rudder, elevator, trimmable horizontal 
stabilizer, and rudder trim control located at the rear fuselage. These 
service bulletins also contain an Inspection Record Sheet in Appendix 
01 for reporting inspection findings to the manufacturer.
    For airplanes on which no damage is found, the service bulletins 
describe procedures for lubricating and testing the cables following 
the inspection. For airplanes on which any damage is found that is 
within certain limits defined by the applicable aircraft maintenance 
manual (AMM), the service bulletins allow further flight. For airplanes 
on which any damage is found that is outside the AMM limits, the 
service bulletins describe procedures for corrective actions. The 
corrective actions include replacing the cables prior to further 
flight, and lubricating and testing the cables.
    The DGAC classified these service bulletins as mandatory and issued 
French airworthiness directive 2002-608(B) R1, dated January 8, 2003, 
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 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 service bulletin described previously, 
except as discussed below.

Differences Among the French Airworthiness Directive, the Service 
Bulletins, and the Proposed AD

    The French airworthiness directive does not define the type of 
inspection, and the service bulletins state that operators should 
``visually inspect'' the affected cables. This proposed AD defines the 
inspection as a ``detailed inspection.'' A definition of this 
inspection is included in Note 1 of this proposed AD.
    The service bulletins do not specify a compliance time for sending 
the inspection report to the manufacturer, and the French airworthiness 
directive specifies compliance within the month following the 
inspection. This proposed AD would require reporting the inspection 
findings to the manufacturer within 60 days after the proposed 
inspection. We find that this information is necessary for the 
manufacturer to gather based upon the importance of the safety issue. 
We also find that reporting within 60 days ensures an appropriate 
interval of time for operators to comply with this proposed requirement 
without compromising safety.

Clarification of Inspection Thresholds

    The service bulletins and the French airworthiness directive give 
inspection thresholds in terms of flight hours accumulated (20,000, 25, 
000, and 30,000 total flight hours) on the affected airplanes, well as 
the number of years since new (10, 13, and 16 years). We have expressed 
these thresholds in paragraph (c) of this proposed AD in a manner that 
captures the intent of the service bulletins and French airworthiness 
directive, and ensures that all affected airplanes are covered.
    Additionally, in lieu of expressing thresholds as a number years 
``since new,'' the proposed AD specifies those thresholds as the 
earlier of the date of issuance of the original Airworthiness 
Certificate, or the original Export Certificate of Airworthiness. This 
decision is based on our determination that operators may interpret 
``since new'' differently. We find that our proposed terminology is 
generally understood within the industry, and records will always exist 
that establish these dates with certainty.

Interim Action

    We consider this proposed AD interim action. If final action is 
later identified, we may consider further rulemaking then.

Cost Impact

    The FAA estimates that 174 airplanes of U.S. registry would be 
affected by this

[[Page 25513]]

proposed AD, that it would take approximately 1 work hour per airplane 
to accomplish the proposed inspection. The average labor rate is $65 
per work hour. Based on these figures, the cost impact of the proposed 
AD on U.S. operators is estimated to be $11,310, or $65 per airplane.
    The cost impact figure discussed above is 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.

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 2003-NM-13-AD.

    Applicability: All Model A300 B2 and A300 B4; Model A300 B4-600, 
B4-600R, C4-605R Variant F, and F4-600R (collectively called A300-
600); and Model A310 series airplanes; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct frayed or corroded control cables for the 
elevator and rudder, which could result in a ruptured control cable, 
and possible reduced controllability of the airplane, accomplish the 
following:

Definitions

    (a) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of the following service bulletins, as 
applicable:
    (1) For Model A300 B2 and A300 B4 series airplanes: Airbus 
Service Bulletin A300-27A0197, Revision 01, including Appendix 01, 
dated February 26, 2003;
    (2) For Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-
600R (collectively called A300-600) series airplanes: Airbus Service 
Bulletin A300-27A6051, including Appendix 01, dated August 8, 2002; 
and
    (3) For Model A310 series airplanes: Airbus Service Bulletin 
A310-27A2098, including Appendix 01, dated August 8, 2002.
    (b) In this AD, the phrase ``date of airworthiness 
certification'' means the date of issuance of the original 
Airworthiness Certificate or the original Export Certificate of 
Airworthiness, whichever occurs first.

Inspection and Corrective Action

    (c) At the applicable time in paragraph (c)(1), (c)(2), (c)(3), 
or (c)(4) of this AD, do a detailed inspection for corrosion and 
damage (e.g., frayed or broken wires) of the pulleys and cables of 
the rudder, elevator, trimmable horizontal stabilizer, and rudder 
trim control located at the rear of the fuselage; including any 
applicable testing and lubrication following the inspection. If any 
corrosion or damage is found that is outside the limits specified in 
the service bulletin, prior to further flight, replace the affected 
cable with a new cable; including any applicable testing and 
lubrication following the replacement. Accomplish all the actions in 
accordance with the applicable service bulletin.
    (1) For airplanes that have accumulated, as of the effective 
date of this AD, less than 20,000 total flight hours and less than 
10 years since the date of airworthiness certification: Inspect at 
the later of the times specified in paragraphs (c)(1)(i) and 
(c)(1)(ii) of this AD.
    (i) Prior to the accumulation of 20,000 total flight hours, or 
within 10 years since the date of airworthiness certification, 
whichever occurs earliest.
    (ii) Within 1,800 flight hours after the effective date of this 
AD.
    (2) For airplanes that have accumulated, as of the effective 
date of this AD, either 20,000 or more total flight hours or more 
than 10 years since the date of airworthiness certification, but 
less than 25,000 total flight hours and 13 years since the date of 
airworthiness certification: Inspect at the later of the times 
specified in paragraphs (c)(2)(i) and (c)(2)(ii) of this AD.
    (i) Prior to the accumulation of 25,000 total flight hours, or 
within 13 years since the date of airworthiness certification, 
whichever occurs earliest.
    (ii) Within 1,800 flight hours after the effective date of this 
AD.
    (3) For airplanes that have accumulated, as of the effective 
date of this AD, either 25,000 or more total flight hours or more 
than 13 years since the date of airworthiness certification, but 
less than 30,000 total flight hours and 16 years since the date of 
airworthiness certification: Inspect at the later of the times 
specified in paragraphs (c)(3)(i) and (c)(3)(ii) of this AD.
    (i) Prior to the accumulation of 30,000 total flight hours, or 
within 16 years since the date of airworthiness certification, 
whichever occurs earliest.
    (ii) Within 1,200 flight hours after the effective date of this 
AD.
    (4) For airplanes that have accumulated, as of the effective 
date of this AD, either 30,000 or more total flight hours or more 
than 16 years since the date of airworthiness certification: Inspect 
within 600 flight hours after the effective date of this AD.

    Note 1:
    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.''

Reporting

    (d) Submit a report of the findings (both positive and negative) 
of the inspection required by paragraph (c) of this AD to Airbus 
Industrie, Customer Services Directorate, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; Attn: AI/SE-D32 Technical 
Data and Documentation Services, or fax: (+33) 5 61 93 28 06. Send 
the report at the applicable time specified in paragraph (c)(1) or 
(c)(2) of this AD. The Inspection Record Sheet in Appendix 01 of the 
applicable service bulletin may be used. Include the inspection 
results, a description of any discrepancy found, the airplane serial 
number, the number of landings and flight hours on the airplane, the 
service bulletin number, and the date of inspection. 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.

[[Page 25514]]

    (1) If the inspection is done after the effective date of this 
AD: Submit the report within 60 days after the inspection.
    (2) If the inspection was done prior to the effective date of 
this AD: Submit the report within 60 days after the effective date 
of this AD.

Alternative Methods of Compliance

    (e) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized 
to approve alternative methods of compliance for this AD.

    Note 2:
    The subject of this AD is addressed in French airworthiness 
directive 2002-608(B) R1, dated January 8, 2003.


    Issued in Renton, Washington, on April 27, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-10381 Filed 5-6-04; 8:45 am]
BILLING CODE 4910-13-P