AD 2001-09-14

[Federal Register Volume 66, Number 91 (Thursday, May 10, 2001)]
[Rules and Regulations]
[Pages 23838-23840]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-11223]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-389-AD; Amendment 39-12221; AD 2001-09-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-243, -341, -342, and 
-343 Series Airplanes Equipped With Rolls Royce Trent 700 Series 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Airbus Model A330-243, -341, -342, and -343 series 
airplanes equipped with Rolls Royce Trent 700 series engines. This 
action requires repetitive inspections of certain components, and 
corrective action, if necessary. This action is necessary to detect and 
correct fatigue cracking of the hinge assemblies and the 12 o'clock 
beam structure of the thrust reverser C-duct, which could cause failure 
of the thrust reverser hinge, resulting in separation of the thrust 
reverser from the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Effective May 25, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 25, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before June 11, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-389-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: 
<a href="/cdn-cgi/l/email-protection#1821357976753571796a7b7775757d766c587e7979367f776e"><span class="__cf_email__" data-cfemail="7e47531f101353171f0c1d1113131b100a3e181f1f50191108">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-389-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 for Windows or 
ASCII text.
    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: 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: 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 Airbus Model A330-243, -341, 
-342, and -343 series airplanes equipped with Rolls Royce Trent 700 
series engines. The DGAC advises that, during flight tests, 
unexpectedly high fatigue loads were measured on the hinges integrated 
on the 12 o'clock beam which forms the upper edge of the thrust 
reverser C-duct. The hinges are unable to withstand these high fatigue 
loads for the design life of the airplane. Resulting fatigue cracks, if 
not detected and corrected, could cause failure of the thrust reverser 
hinge, which could result in separation of the thrust reverser from the 
airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A330-78-3006, Revision 05, dated 
March 6, 2001, which describes procedures for a general visual 
inspection of the hinge assemblies and the beam structure of the upper 
extreme edge of the thrust reverser unit C-duct for cracks, and 
corrective action, if necessary; a detailed visual inspection, if 
applicable, of hinges 2, 3, 4, and 5 in the same area for cracks, and 
corrective action, if necessary; and repetitions of these inspections, 
as applicable, at applicable intervals. 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 1997-118-047(B) 
R2, dated September 20, 2000, in order to assure the continued 
airworthiness of these airplanes in France.
    Airbus Service Bulletin A330-78-3006, Revision 05, dated March 6, 
2001, references Rolls Royce Service Bulletin RB.211-78-B115, Revision 
2, dated October 29, 1999, as an additional source of service 
information for

[[Page 23839]]

accomplishment of the inspections and corrective actions.

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 21.19) 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 that may be 
registered in the United States at some time in the future, this AD is 
being issued to detect and correct fatigue cracking of the hinge 
assemblies and the 12 o'clock beam structure of the thrust reverser C-
duct, which could cause failure of the thrust reverser hinge, resulting 
in separation of the thrust reverser from the airplane. This AD 
requires accomplishment of the actions specified in the Airbus service 
bulletin described previously.

Cost Impact

    None of the 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 5 work hours to 
accomplish the required inspections, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of this AD would 
be $300 per airplane, per inspection cycle.

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.
    Submit comments using the following format:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the proposed 
AD is being requested.
    <bullet> 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 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 2000-NM-389-AD.'' The postcard will be date stamped 
and returned to the commenter.

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

    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:

2001-09-14  Airbus Industrie: Amendment 39-12221. Docket 2000-NM-
389-AD.

    Applicability: Model A330-243, -341, -342 and -343 series 
airplanes; certificated in any category; that are equipped with 
Rolls Royce Trent 700 series engines.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (b) 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.


[[Page 23840]]


    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracking of the hinge assemblies 
and the 12 o'clock beam structure of the thrust reverser C-duct, 
which could cause failure of the thrust reverser hinge, resulting in 
separation of the thrust reverser from the airplane, accomplish the 
following:

Initial and Repetitive Inspections

    (a) Perform a general visual inspection of the hinge assemblies 
and the 12 o'clock beam structure of the right and left thrust 
reversers for cracks, in accordance with Airbus Service Bulletin 
A330-78-3006, Revision 05, dated March 6, 2001, according to the 
criteria in Table 1 of this AD, below:

                       Table 1--Initial Inspection
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                   If--                            Then inspect--
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Neither Airbus Modification 46879 nor       Before the accumulation of
 47358 has been embodied on the airplane.    1,200 total flight cycles,
                                             or within 6 months after
                                             the effective date of this
                                             AD, whichever occurs first.
Either Airbus Modification 46879 or 47358   Before the accumulation of
 have been embodied on the airplane.         2,000 total flight cycles,
                                             or 6 months after the
                                             effective date of this AD,
                                             whichever occurs first.
------------------------------------------------------------------------

    (1) If no crack is found during the general visual inspection 
required by paragraph (a) of this AD, before further flight, perform 
a detailed visual inspection of the lugs of hinges 2, 3, 4, and 5 of 
the right and left thrust reversers for cracks in accordance with 
Airbus Service Bulletin A330-78-3006, Revision 05, dated March 6, 
2001.
    (i) If no crack is found as a result of the detailed visual 
inspection mandated by paragraph (a)(1) of this AD, repeat the 
general visual inspection mandated by paragraph (a) of this AD 
according to the schedule in Table 2 of this AD.
    (ii) If a crack is found as a result of the detailed visual 
inspection mandated by paragraph (a)(1) of this AD:
    (A) Before further flight, replace the affected thrust reverser 
with a new or serviceable thrust reverser in accordance with Airbus 
Service Bulletin A330-78-3006, Revision 05, dated March 6, 2001.
    (B) Repeat the general visual inspection mandated in paragraph 
(a) of this AD according to the schedule in Table 2 of this AD.
    (2) If a crack is found during the general visual inspection 
required by paragraph (a) of this AD, accomplish the actions 
required by paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.
    (i) Before further flight, replace the affected thrust reverser 
with a new or serviceable thrust reverser in accordance with Airbus 
Service Bulletin A330-78-3006, Revision 05, dated March 6, 2001.
    (ii) Repeat the general visual inspection mandated in paragraph 
(a) of this AD according to the schedule in Table 2 of this AD, 
below:

                    Table 2.--Repetitive Inspections
------------------------------------------------------------------------
                                             Then repeat the inspection
                   If--                     at intervals not to exceed--
------------------------------------------------------------------------
Neither Airbus Modification 46879 nor       1,200 flight cycles.
 47358 has been embodied on the airplane.
Either Airbus Modification 46879 or 47358   2,000 flight cycles.
 has been embodied on the airplane.
------------------------------------------------------------------------


    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''


    Note 3: For the purposes of this AD, a detailed visual 
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 a mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

Alternative Methods of Compliance

    (b) 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, 
Transport Airplane Directorate, FAA. 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
sections 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.

Incorporation by Reference

    (d) The actions shall be done in accordance with Airbus Service 
Bulletin A330-78-3006, Revision 05, dated March 6, 2001. 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 5: The subject of this AD is addressed in French 
airworthiness directive 1997-118-047(B) R2, dated September 20, 
2000.

Effective Date

    (e) This amendment becomes effective on May 25, 2001.


    Issued in Renton, Washington, on April 30, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-11223 Filed 5-9-01; 8:45 am]
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