[Federal Register Volume 68, Number 117 (Wednesday, June 18, 2003)]
[Proposed Rules]
[Pages 36504-36506]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-15335]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-179-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus 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 A310 series 
airplanes. This proposal would require electrical conductivity testing 
to verify the correct heat treatment of the two half fittings holding 
the ejection jack for the ram air turbine (RAT). This action is 
necessary to prevent decreased structural integrity of the two half 
fittings and loss of the RAT during extension, which could lead to 
reduced controllability of the airplane in the event of a dual engine 
failure, or in the event of loss of two or all hydraulic systems. This 
action is intended to address the identified unsafe condition.

DATES: Comments must be received by July 18, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-179-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. 2002-NM-179-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.

[[Page 36505]]

    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: Tom Groves, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1503; 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 2002-NM-179-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. 2002-NM-179-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 A310 series 
airplanes. The DGAC advises that an operator reported that the two half 
fittings holding the ejection jack for the ram air turbine (RAT) were 
found cracked. Investigation showed that the cracks were due to stress 
corrosion. Conductivity testing revealed that the heat treatment of the 
half fittings aluminum alloy was incorrect. Incorrect heat treatment of 
the half fittings decreased the material behavior against stress 
corrosion, and was identified as the cause of the cracking. This 
condition, if not corrected, could result in decreased structural 
integrity of the half fittings and loss of the RAT during extension, 
which could lead to reduced controllability of the airplane in the 
event of a dual engine failure, or in the event of loss of two or all 
hydraulic systems.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A310-57A2084, including Appendix 
01, dated May 3, 2002, which describes procedures for a one-time 
electrical conductivity test of the half fittings, to check for the 
heat treatment status. The service bulletin also describes procedures 
for a detailed inspection of the half fittings for cracks or corrosion, 
if necessary. The service bulletin also describes procedures for 
replacement of the half fittings. Accomplishment of the actions 
specified in the service bulletin is intended to adequately address the 
identified unsafe condition. The DGAC classified this service bulletin 
as mandatory and issued French airworthiness directive 2002-263(B), 
dated May 15, 2002, in order to ensure the continued airworthiness of 
these airplanes in France.

FAA's Conclusions

    This airplane model is manufactured in France and is 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 Between Proposed Rule, the Foreign Airworthiness Directive, 
and the Service Bulletin

    The proposed AD would differ from the parallel French airworthiness 
directive in that it would require all replacement half fittings to 
have successfully passed the electrical conductivity test per Airbus 
Service Bulletin A310-57A2084, including Appendix 01, dated May 3, 
2002. Operators should note that the parallel French airworthiness 
directive requires that replacement half fittings have a certain part 
number and should either have been ordered after November 2001, or have 
successfully passed the electrical conductivity test. The FAA does not 
consider the ``order date'' as sufficient assurance that the 
replacement half fittings have the correct heat treatment.
    Operators should also note that, although the service bulletin 
specifies reporting to Airbus the result of the inspections and any 
corrective actions, the proposed AD does not include such a 
requirement.

Cost Impact

    The FAA estimates that 48 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 actions, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the proposed AD on U.S. operators is estimated to be 
$2,880, or $60 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 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

[[Page 36506]]

incidental costs, such as the time required to gain access and close 
up, planning time, or time necessitated by other administrative 
actions.

Changes to 14 CFR Part 39/Effect on the Proposed AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance. Because we have now included this material in part 39, only 
the office authorized to approve AMOCs is identified in each individual 
AD.

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 2002-NM-179-AD.

    Applicability: All Model A310 series airplanes, certificated in 
any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent decreased structural integrity of the two half 
fittings and loss of the ram air turbine (RAT) during extension, 
which could lead to reduced controllability of the airplane in the 
event of a dual engine failure, or in the event of loss of two or 
all hydraulic systems, accomplish the following:

Service Bulletin References

    (a) The following information pertains to the service bulletin 
referenced in this AD:
    (1) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Airbus Service Bulletin A310-57A2084, 
including Appendix 01, dated May 3, 2002.
    (2) Although the service bulletin referenced in this AD 
specifies to submit information to the manufacturer, this AD does 
not include such a requirement.

Conductivity Test

    (b) Within 600 flight hours after the effective date of this AD, 
perform a one-time electrical conductivity test of the two half 
fittings holding the RAT ejection jack, to verify correct heat 
treatment of the half fittings, per the service bulletin.
    (1) If correct heat treatment of the two half fittings is 
verified, no further action is required by this paragraph.
    (2) If incorrect heat treatment of any half fitting is found by 
the test performed in paragraph (b) of this AD, perform a detailed 
inspection of the two half fittings for any cracking or corrosion, 
per the service bulletin.

    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.''

Corrective Action

    (c) For any half fittings that require a detailed inspection per 
paragraph (b)(2) of this AD: Do the actions specified in paragraph 
(c)(1) or (c)(2) of this AD, as applicable, per the service 
bulletin.
    (1) If no cracking or corrosion is found: Within one year after 
the effective date of this AD, replace the two half fittings with 
half fittings having part number A5721023800000 that have 
successfully passed the electrical conductivity test, per the 
service bulletin.
    (2) If any cracking or corrosion is found: Before further 
flight, replace the two half fittings with half fittings having part 
number A5721023800000 that have successfully passed the electrical 
conductivity test, per the service bulletin.

Parts Installation

    (d) As of the effective date of this AD, no person shall install 
a half fitting having part number A5721023800000 that has not 
successfully passed the electrical conductivity test per the service 
bulletin, on any airplane.

Alternative Methods of Compliance

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

    Note 2: The subject of this AD is addressed in French 
airworthiness directive 2002-263(B), dated May 15, 2002.


    Issued in Renton, Washington, on June 12, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-15335 Filed 6-17-03; 8:45 am]
BILLING CODE 4910-13-P