[Federal Register Volume 65, Number 114 (Tuesday, June 13, 2000)]
[Rules and Regulations]
[Pages 37029-37031]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-14432]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-139-AD; Amendment 39-11776; AD 2000-11-27]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
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 A319, A320, and A321 series 
airplanes. This action requires a one-time ultrasonic inspection to 
detect disbonding of the skin attachments at the stringers and spars of 
the vertical stabilizer, and repair, if necessary. This action is 
necessary to detect and correct disbonding of the vertical stabilizer 
structure, which could result in reduced structural integrity of the 
spar boxes of the vertical stabilizer.

DATES: Effective June 28, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 28, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before July 13, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-139-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this

[[Page 37030]]

location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may also be sent via the Internet using the 
following address: [email protected]. Comments sent via the 
Internet must contain ``Docket No. 2000-NM-139-AD'' in the subject line 
and need not be submitted in triplicate.
    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 Geuneurale 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 A319, A320, and A321 series airplanes. The DGAC advises that 
localized disbonding has been detected on the skin attachments at the 
stringers and spars of the spar boxes of the vertical stabilizer. 
During the manufacturing process, pre-cured parts (attachments of the 
stringers, spars, and ribs) are installed on the skin panel before the 
final curing process. A peel ply is used to protect the contact 
surfaces of the attachment angles of the skin panels of the vertical 
stabilizer until the pre-cured parts are ready for installation. 
Investigation revealed that, after the peel ply was removed from the 
attachment angles, a residue of polymer finish contaminated the contact 
surfaces of some pre-cured parts. This contamination reduced the 
adhesive strength of the bond and, in some cases, caused debonding 
(disbonding) of the skin attachments. This condition, if not detected 
and corrected, could result in reduced structural integrity of the spar 
boxes of the vertical stabilizer.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus Service Bulletin A320-55A1027, 
dated May 12, 2000, which describes procedures for a one-time 
ultrasonic inspection to detect disbonding of the skin attachments at 
the stringers and spars of the vertical stabilizer, left-and right-hand 
sides, and repair, if necessary. If any disbonding (damage) is detected 
and the area of damage is greater than 300 square millimeters (mm2), or 
if multiple damage is detected on one specific component (stringer-spar 
attachment), the repair involves installing additional fasteners in the 
affected areas. The amount of damage determines the number of 
additional fasteners to be installed in the affected area.
    Additionally, Airbus Service Bulletin A320-55A1027 references 
Airbus Service Bulletin A320-55-1026, Revision 01, dated May 20, 1999, 
which, for certain airplanes, describes procedures for prior or 
concurrent modification of the vertical stabilizer to ensure proper 
reinforcement of the structure-skin attachments.
    The DGAC classified Airbus Service Bulletin A320-55-A1027 as 
mandatory and issued French airworthiness directive T2000-208-148(B) 
R1, dated May 17, 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 
Sec. 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 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, this AD is being issued to detect and correct 
disbonding of the vertical stabilizer structure, which could result in 
reduced structural integrity of the spar boxes of the vertical 
stabilizer. This AD requires a one-time ultrasonic inspection to detect 
disbonding of the skin attachments at the stringers and spars of the 
vertical stabilizer, and repair, if necessary. The actions are required 
to be accomplished in accordance with the service bulletin described 
previously.

Interim Action

    This is considered interim action. The manufacturer has advised 
that it is currently developing a repetitive inspection program to 
positively address the unsafe condition addressed by this AD. Once this 
repetitive inspection program is developed, approved, and available, 
the FAA may consider additional rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an 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:
     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.
     For each issue, state what specific change to the AD is 
being requested.
     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

[[Page 37031]]

postcard on which the following statement is made: ``Comments to Docket 
Number 2000-NM-139-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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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:

2000-11-27  Airbus Industrie: Amendment 39-11776. Docket 2000-NM-
139-AD.

    Applicability: Model A319, A320, and A321 series airplanes; 
certificated in any category; as listed in Airbus Service Bulletin 
A320-55A1027, dated May 12, 2000.

    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 (c) 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 detect and correct disbonding of the vertical stabilizer 
structure, which could result in reduced structural integrity of the 
spar boxes of the vertical stabilizer, accomplish the following:

Ultrasonic Inspection

    (a) Within 60 days after the effective date of this AD, perform 
a one-time ultrasonic inspection to detect disbonding (damage) of 
the skin attachments at the stringers and spars of the vertical 
stabilizer, left-and right-hand sides, in accordance with Airbus 
Service Bulletin A320-55A1027, dated May 12, 2000.
    (1) If no damage is detected or if a single area of damage is 
less than or equal to an area of 300 square millimeters (mm2), no 
further action is required by this AD.
    (2) If any damage is detected and the area of damage is greater 
than 300 mm2, or if multiple damage is detected on one specific 
component (stringer/spar attachment), prior to further flight, 
accomplish applicable repairs in accordance with the service 
bulletin.

Modification (for Certain Airplanes)

    (b) For airplanes with manufacturer's serial numbers listed in 
paragraph B of the Planning Information of Airbus Service Bulletin 
A320-55A1027, dated May 12, 2000: Prior to or concurrent with the 
ultrasonic inspection required by paragraph (a) of this AD, modify 
the vertical stabilizer to ensure proper reinforcement of the 
structure/skin attachments, in accordance with Airbus Service 
Bulletin A320-55-1026, Revision 01, dated May 20, 1999.

    Note 2: Accomplishment of the modification required by paragraph 
(b) of this AD, prior to the effective date of this AD, in 
accordance with Airbus Service Bulletin A320-55-1026 dated March 29, 
1999, is considered acceptable for compliance with the applicable 
requirement of this AD.

Alternative Methods of Compliance

    (c) 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 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

    (d) Special flight permits may be issued in accordance with 
Sec. 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

    (e) The actions shall be done in accordance with Airbus Service 
Bulletin
    A320-55A1027, dated May 12, 2000, and Airbus Service Bulletin 
A320-55-1026, Revision 01, dated May 20, 1999. 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 directive T2000-208-148(B) R1, dated May 17, 2000.

    (f) This amendment becomes effective on June 28, 2000.

    Issued in Renton, Washington, on June 2, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-14432 Filed 6-12-00; 8:45 am]
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