AD 2001-07-02

[Federal Register Volume 66, Number 66 (Thursday, April 5, 2001)]
[Rules and Regulations]
[Pages 18045-18047]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-7960]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-117-AD; Amendment 39-12167; AD 2001-07-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-301, -321, -322, -
341, and -342 Series Airplanes; and Model A340-211, -212, -213, -311, -
312, and -313 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) that 
is applicable to certain Airbus Model A330 and A340 series airplanes. 
This action requires a one-time inspection for cracks on the attachment 
holes of the doorstop fitting on the aft passenger/crew doors; repair, 
if necessary; and modification of the attachment holes. This action is 
necessary to detect and prevent fatigue cracking of the attachment 
holes for doorstop fitting number 5, which could result in reduced 
structural integrity of the door frames. This action is intended to 
address the identified unsafe condition.

DATES: Effective April 20, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 20, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before May 7, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-117-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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#8db4a0ece3e0a0e4ecffeee2e0e0e8e3f9cdebececa3eae2fb"><span class="__cf_email__" data-cfemail="dfe6f2beb1b2f2b6beadbcb0b2b2bab1ab9fb9bebef1b8b0a9">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-117-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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; 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 and 
A340 series airplanes. The DGAC advises that, during fatigue tests, 
cracks were found, starting at the attachment holes for doorstop 
fitting No. 5 at frame 73A on the aft passenger/crew doors. This 
condition, if not corrected, could result in reduced structural 
integrity of the door frames.
    Although the fatigue tests were performed on the Model A340 series 
airplane, the subject area on affected Model A330 series airplanes is 
almost identical to that on the affected Model A340 series airplanes. 
Therefore, those Model A330 series airplanes may be subject to the same 
unsafe condition revealed on the Model A340 series airplanes.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A330-53-3074, Revision 01 (for 
Model A330 series airplanes), and A340-53-4085, Revision 01 (for Model 
A340 series airplanes), both dated May 19, 1998, which describe, among 
other things, procedures for inspection of the two inboard attachment 
holes and the support fitting in frame 73A of the aft passenger/crew 
doors for cracks, and cold expansion of the holes and the addition of 
bushings to improve the fatigue behavior of the doorstop fittings. 
Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition.
    The DGAC classified the inspections as mandatory and the cold 
expansion modifications as optional and issued French airworthiness 
directives 2000-126-114(B) (for Model A330 series airplanes) and 2000-
125-139(B) (for Model A340 series airplanes), both dated March 8, 2000, 
in order to assure the continued airworthiness of these airplanes in 
France.

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 21.29) 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 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,

[[Page 18046]]

this AD is being issued to detect and prevent fatigue cracking of the 
of the attachment holes for doorstop fitting number 5, which could 
result in reduced structural integrity of the door frames. This AD 
requires inspection of the two inboard attachment holes and the support 
fitting in frame 73A of the aft passenger/crew doors for cracks; 
repair, if necessary; and cold expansion of the holes and the addition 
of bushings to improve the fatigue behavior of the doorstop fittings, 
the accomplishment of which constitutes terminating action for certain 
inspections. The actions are required to be accomplished in accordance 
with the service bulletins described previously, except as discussed 
below.

Differences Between This AD and the Service Bulletins and Foreign 
Airworthiness Directives

    This AD differs from the parallel French airworthiness directives 
in that they mandate the accomplishment of the cold expansion of the 
holes and the addition of bushings. The French airworthiness directives 
provide for those actions as optional, in lieu of repetitive 
inspections. Mandating the modification is based on the FAA's 
determination that long-term continued operational safety will be 
better ensured by modifications or design changes to remove the source 
of the problem, rather than by repetitive inspections. Long-term 
inspections may not be providing the degree of safety assurance 
necessary for the transport airplane fleet. This, coupled with a better 
understanding of the human factors associated with numerous continual 
inspections, has led the FAA to consider placing less emphasis on 
inspections and more emphasis on design improvements. This modification 
requirement is consistent with these conditions.
    Operators should note that, although the service bulletins specify 
that the manufacturer may be contacted for disposition of certain 
repair conditions, this AD requires the repair of those conditions to 
be accomplished in accordance with a method approved by either the FAA 
or the DGAC (or its delegated agent). In light of the type of repair 
that will be required to address the identified unsafe condition, and 
in consonance with existing bilateral airworthiness agreements, the FAA 
has determined that, for this AD, a repair approved by either the FAA 
or the DGAC will be acceptable for compliance with this AD.
    In addition, although the service bulletins refer to inspection 
service bulletins that must be followed prior to or concurrent with the 
modifications, this AD does not require accomplishment of those 
inspection service bulletins because the accomplishment of the 
modification cancels their inspection requirements.

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 4 work hours to 
accomplish the required actions, at an average labor rate of $60 per 
work hour. The cost of required parts would be minimal. Based on these 
figures, the cost impact of this AD is estimated to 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.
    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-117-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

[[Page 18047]]

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:

2001-07-02  Airbus Industrie: Amendment 39-12167. Docket 2000-NM-
117-AD.

    Applicability: Model A330-301, -321, -322, -341, and -342 series 
airplanes, and Model A340-211, -212, -213, -311, -312, and -313 
series airplanes, certificated in any category, except those on 
which Airbus Modification 41849 or 44932 (reference Service Bulletin 
A330-53-3074, Revision 01, for Model A330 series airplanes; or A340-
53-4085 Revision 01, for Model A340 series airplanes; both dated May 
19, 1998) has been accomplished.

    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 propagation of fatigue cracking, which could result 
in reduced structural integrity of the door frames, accomplish the 
following:

Inspection

    (a) Conduct an eddy current rotating probe test procedure on the 
holes for doorstop fitting number 5 (left and right) on frame 73A, 
as specified in paragraph (a)(1) or (a)(2), as applicable, of this 
AD.
    (1) For Model A330 series airplanes: Prior to the accumulation 
of 13,000 total flight cycles, conduct the test in accordance with 
Airbus Service Bulletin A330-53-3074, Revision 01, dated May 19, 
1998.
    (2) For Model A340 series airplanes: Prior to the accumulation 
of 8,000 total flight cycles, conduct the test in accordance with 
Airbus Service Bulletin A340-53-4085, Revision 01, dated May 19, 
1998.

Repairs

    (b) If any crack is detected during the inspection required by 
paragraph (a) of this AD, prior to further flight, repair in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Direction Generale de l'Aviation Civile (DGAC) (or its 
delegated agent).

Terminating Action

    (c) Before further flight following the inspection required in 
paragraph (a) of this AD, cold expand the holes for (left and right) 
doorstop fitting number 5 and install bushings, in accordance with 
Airbus Service Bulletin A330-53-3074, Revision 01 (for Model A330 
series airplanes), or Airbus Service Bulletin A340-53-4085, Revision 
01 (for Model A340 series airplanes), both dated May 19, 1998, as 
applicable. Accomplishment of this action constitutes terminating 
action for the requirements of this AD.

    Note 2: Inspection and modification accomplished prior to the 
effective date of this AD, in accordance with Airbus Service 
Bulletin A330-53-3074, dated November 17, 1997 (for Model A330 
series airplanes), or Airbus Service Bulletin A340-53-4085, dated 
November 17, 1997 (for Model A340 series airplanes), as applicable, 
are considered acceptable for compliance with the applicable action 
specified in this AD.

Alternative Methods of Compliance

    (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. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then 
forward the requests and added comments to the Manager, 
International Branch, ANM-116.

    Note 3: 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

    (e) 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

    (f) Except as required by paragraph (b) of this AD, the actions 
shall be done in accordance with Airbus Service Bulletin A330-53-
3074, Revision 01, dated May 19, 1998; or Airbus Service Bulletin 
A340-53-4085, Revision 01, dated May 19, 1998; as applicable. 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 4: The subject of this AD is addressed in French 
airworthiness directives 2000-126-114(B), dated March 8, 2000, and 
2000-125-139(B), dated March 8, 2000.

Effective Date

    (g) This amendment becomes effective on April 20, 2001.

    Issued in Renton, Washington, on March 26, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-7960 Filed 4-4-01; 8:45 am]
BILLING CODE 4910-13-U