[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]
BILLING CODE 4910-13-U
