[Federal Register Volume 63, Number 86 (Tuesday, May 5, 1998)]
[Rules and Regulations]
[Pages 24740-24742]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11563]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-300-AD; Amendment 39-10511; AD 98-09-30]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-301 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), 
applicable to certain Airbus Model A330-301 series airplanes. This 
action requires a one-time visual inspection to measure clearances 
between the engine forward feed pipe and shroud sleeve in the engine 
pylon; and repetitive operational tests for fuel leakage, and 
replacement of the shroud sleeve with a new improved part, if 
necessary. This amendment is prompted by the issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified in this AD are intended to prevent 
fuel from leaking into the pylon primary structure and into the engine

[[Page 24741]]

nacelle core zone, which could result in a fire in the engine.

DATES: Effective May 20, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 20, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before June 4, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 97-NM-300-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, notified the 
FAA that an unsafe condition may exist on certain Airbus Model A330-301 
series airplanes. The DGAC advises that it has received reports of 
insufficient overlap between the fuel feed pipe and the shroud sleeve. 
The insufficient overlap has been attributed to an error during 
manufacturing of the shroud sleeve. Such insufficient overlap could 
cause an improper O-ring seal between the fuel feed pipe and the shroud 
sleeve. In the event of a leak in the fuel feed pipe, such insufficient 
overlap could permit fuel to leak into the pylon primary structure and 
into the engine nacelle core zone. This condition, if not corrected, 
could result in a fire in the engine.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A330-28-3046, Revision 01, dated 
November 12, 1996, which describes procedures for a one-time visual 
inspection to measure clearances of the overlap between the engine 
forward feed pipe and shroud sleeve in the engine pylon, and repetitive 
operational tests for fuel leakage. The DGAC classified this service 
bulletin as mandatory, and issued French airworthiness directive 96-
174-034(B)R1, dated January 2, 1997, in order to assure the continued 
airworthiness of these airplanes in France.
    Airbus also has issued Service Bulletin A330-28-3045, dated August 
9, 1996, which describes procedures for replacing the shroud sleeve 
with a newly designed shroud sleeve. The DGAC approved this service 
bulletin.

FAA's Conclusions

    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.19) 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 the 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 bulletins described previously.

Cost Impact

    None of the Airbus Model A330-301 series airplanes affected by this 
action are on the U.S. Register. All airplanes included in the 
applicability of this rule currently are operated by non-U.S. operators 
under foreign registry; therefore, they are not directly affected by 
this AD action. However, the FAA considers that this rule is necessary 
to ensure that the unsafe condition is addressed in the event that any 
of these subject airplanes are imported and placed on the U.S. Register 
in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 4 work hours to 
accomplish the required actions, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of this AD would be 
$240 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and 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.
    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 97-NM-300-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.

[[Page 24742]]

    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

    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:

98-09-30  Airbus: Amendment 39-10511. Docket 97-NM-300-AD.

    Applicability: Airbus Model A330-301 series airplanes equipped 
with Pratt & Whitney or General Electric engines on which Airbus 
Modification 44649 has not been accomplished, certificated in any 
category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (d) 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 fuel from leaking into the pylon primary structure 
and into the engine nacelle core zone, which could result in a fire 
in the engine; accomplish the following:
    (a) Within 500 flight hours after the effective date of this AD, 
perform a one-time visual inspection to measure the clearances 
between the engine forward feed pipe and the shroud sleeve of the 
left- and right-hand engine pylons, in accordance with Airbus 
Service Bulletin A330-28-3046, Revision 01, dated November 12, 1996. 
If the measured clearance is greater than 6 millimeters (mm), no 
further action is required by this AD.
    (b) If the measured clearance is less than or equal to 6 mm, 
prior to further flight, perform an operational test to check for 
fuel leaks in accordance with Airbus Service Bulletin A330-28-3046, 
Revision 01, dated November 12, 1996.
    (1) If no leaking is found, repeat the operational test 
thereafter at intervals not to exceed 500 flight hours until the 
requirements of paragraph (c) of this AD are accomplished.
    (2) If any leaking is found, prior to further flight, replace 
the shroud sleeve with a new improved part in accordance with Airbus 
Service Bulletin A330-28-3045, dated August 9, 1996. Accomplishment 
of this replacement constitutes terminating action for the 
repetitive operational testing requirements of this AD.
    (c) For any airplane on which the measured clearance is less 
than or equal to 6 mm and no leaking is found during any operational 
test required by paragraph (b) of this AD: Within 1 year after the 
effective date of this AD, replace the shroud sleeve with a new 
improved part in accordance with Airbus Service Bulletin A330-28-
3045, dated August 9, 1996. Accomplishment of this modification 
constitutes terminating action for the repetitive operational 
testing requirements of paragraph (b) of this AD.
    (d) 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, FAA, 
Transport Airplane directorate. 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

    (e) Special flight permits may be issued in accordance with 
Secs. 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.
    (f) The replacement shall be done in accordance with Airbus 
Service Bulletin A330-28-3045, dated August 9, 1996. The inspection 
and operational test (if accomplished) shall be done in accordance 
with Airbus Service Bulletin A330-28-3046, Revision 01, dated 
November 12, 1996. 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 3: The subject of this AD is addressed in French 
airworthiness directive 96-174-034(B)R1, dated January 2, 1997.

    (g) This amendment becomes effective on May 20, 1998.

    Issued in Renton, Washington, on April 24, 1998.
Gary L. Killion,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-11563 Filed 5-4-98; 8:45 am]
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