AD 2003-18-08

[Federal Register Volume 68, Number 176 (Thursday, September 11, 2003)]
[Rules and Regulations]
[Pages 53498-53499]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-22708]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-179-AD; Amendment 39-13299; AD 2003-18-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Airbus Model A310 series airplanes, that requires 
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: Effective October 16, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 16, 2003.

ADDRESSES: 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 Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Airbus Model A310 series 
airplanes was published in the Federal Register on June 18, 2003 (68 FR 
36504). That action proposed to 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).

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule as proposed.

Change to Labor Rate Estimate

    Since issuing the proposal, we have reviewed the figures we have 
used over the past several years to calculate AD costs to operators. To 
account for various inflationary costs in the airline industry, we find 
it necessary to increase the labor rate used in these calculations from 
$60 per work hour to $65 per work hour. The cost impact information, 
below, reflects this increase in the specified hourly labor rate.

Cost Impact

    The FAA estimates that 48 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the required actions, 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 $3,120, or $65 per 
airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the 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 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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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

0
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:

[[Page 53499]]

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-18-08 Airbus: Amendment 39-13299. 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, 
excluding 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.

Incorporation by Reference

    (f) The actions shall be done in accordance with Airbus Service 
Bulletin A310-57A2084, excluding Appendix 01, dated May 3, 2002. 
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 2: The subject of this AD is addressed in French 
airworthiness directive 2002-263(B), dated May 15, 2002.

Effective Date

    (g) This amendment becomes effective on October 16, 2003.

    Issued in Renton, Washington, on August 29, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-22708 Filed 9-10-03; 8:45 am]
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