[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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