[Federal Register Volume 69, Number 63 (Thursday, April 1, 2004)]
[Proposed Rules]
[Pages 17115-17117]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-7304]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-123-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to all Airbus Model A300 B2 and A300 
B4; A300 B4-600, A300 B4-600R, A300 C4-605R Variant F A300 F4-600R 
(collectively called A300-600); and A310 series airplanes. This 
proposal would require an inspection to detect breaks in the bottom 
flange fitting of the ram air turbine (RAT); and corrective actions, if 
necessary. This proposal would also require submission of an inspection 
report to the airplane manufacturer. This action is necessary to 
prevent failure of the RAT yoke fitting, which could result in the loss 
of RAT function and possible loss of critical flight control in the 
event of certain emergency situations. This action is intended to 
address the identified unsafe condition.

DATES: Comments must be received by May 3, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-123-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-123-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: 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

    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 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-123-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.

[[Page 17116]]

2003-NM-123-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; 
A300 B4-600, A300 B4-600R, A300 C4-605R Variant F, A300 F4-600R 
(collectively called A300-600); and A310 series airplanes. The DGAC 
advises that, during scheduled maintenance on a Model A310 series 
airplane, an operator reported that the swivel coupling of the ram air 
turbine (RAT) yoke fitting was found broken. Investigation along the 
corner radius of the bottom flange fitting of the part showed that the 
failure was associated with abnormal static loads. The RAT drives a 
pump that allows one hydraulic system to be pressurized in order to 
maintain critical flight control in the event of certain emergency 
situations. Failure of the RAT yoke fitting, if not corrected, could 
result in the loss of RAT function and possible loss of critical flight 
control.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A300-57A0241, dated 
March 6, 2003; AOT A300-57A6096, dated March 6, 2003; and AOT A310-
57A2085, dated March 6, 2003. These AOTs describe procedures for 
inspecting the bottom flange fitting of the RAT for damage, and 
replacing it with a new part, if necessary. The DGAC classified these 
AOTs as mandatory and issued French airworthiness directive 2003-
149(B), dated April 16, 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 AOTs described previously, except as 
discussed below.

Differences Among the Proposed Rule, the AOTs, and the French 
Airworthiness Directive

    The French airworthiness directive mandates, and the AOTs describe, 
a one-time inspection of the yoke fitting for the RAT swivel coupling. 
However, because the root cause has not been identified, this proposed 
AD would require repetitive inspections. We find it necessary to 
require these repetitive inspections to ensure the safety of the fleet 
until a terminating action can be developed.
    Although the AOTs and the French AD do not give a compliance time 
for submitting inspection reports to the manufacturer, this proposed AD 
would require submission of such reports within 60 days following any 
inspection.

Interim Action

    This proposed AD is considered to be interim action. The inspection 
reports that would be required by this proposed AD will enable the 
manufacturer to obtain better insight into the nature, cause, and 
extent of the damage, and eventually to develop final action to address 
the unsafe condition. Once final action has been identified, we may 
consider further rulemaking.

Cost Impact

    The FAA estimates that 165 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 1 work 
hour per airplane to accomplish the proposed inspection, and that 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 
$10,725, or $65 per airplane, per inspection cycle.
    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 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-123-AD.

    Applicability: Model A300 B2 and A300 B4; A300 B4-600, A300 B4-
600R, A300 C4-605R Variant F, A300 F4-600R (collectively called 
A300-600); and A310 series airplanes; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the ram air turbine (RAT) yoke fitting, 
which could result in the loss of RAT function and possible loss of 
critical flight control in the event of certain emergency 
situations, accomplish the following:

[[Page 17117]]

All Operators Telex (AOT) References

    (a) The term ``All Operators Telex,'' or ``AOT'' as used in this 
AD, means the following AOTs, as applicable:
    (1) For Model A300 B2 and A300 B4 series airplanes: Airbus All 
Operators Telex A300-57A0241, dated March 6, 2003;
    (2) For Model A300 B4-600, A300 B4-600R, A300 C4-605R Variant F, 
and A300 F4-600R (collectively called A300-600) series airplanes: 
Airbus All Operators Telex A300-57A6096, dated March 6, 2003; and
    (3) For Model A310 series airplanes: Airbus All Operators Telex 
A310-57A2085, dated March 6, 2003.

Detailed Inspection and Replacement, If Necessary

    (b) Within 600 flight hours or 3 months after the effective date 
of this AD, whichever occurs first: Perform a detailed inspection of 
the bottom flange fitting of the yoke fitting for the RAT swivel 
coupling in accordance with the applicable AOT.

    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.''

    (1) If the flange fitting is not broken, repeat the inspection 
required by paragraph (b) of this AD at intervals not to exceed 600 
flight hours.
    (2) If the flange fitting is broken, before further flight, 
replace the flange fitting with a new flange fitting in accordance 
with the applicable AOT. Repeat the inspection required by paragraph 
(b) of this AD at intervals not to exceed 600 flight hours.

Inspection Report

    (c) Submit a report of the findings, both positive (broken or 
cracked fittings) and negative (no findings) of the initial 
inspection required by paragraph (b) of this AD; thereafter report 
only positive findings of the repetitive inspections required by 
paragraphs (b)(1) and (b)(2) of this AD. Send the reports to Airbus, 
Customer Service Engineering, Attention: Mr. Xavier Jolivet, SEA22, 
1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax 
number (33) 561933614, at the applicable time specified in paragraph 
(c)(1) or (c)(2) of this AD. The report must include the inspection 
results, a description of any discrepancies found, the airplane 
serial number, and the number of landings and flight hours on the 
airplane. 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) For inspections done on or after the effective date of this 
AD: Submit the report within 60 days after the inspection.
    (2) For inspections 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

    (d) 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 2003-149(B), dated April 16, 2003.



    Issued in Renton, Washington, on March 24, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-7304 Filed 3-31-04; 8:45 am]
BILLING CODE 4910-13-P