[Federal Register Volume 63, Number 232 (Thursday, December 3, 1998)]
[Rules and Regulations]
[Pages 66753-66755]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-32099]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-264-AD; Amendment 39-10928; AD 98-25-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A321-111, -112, and -131
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 A321-111, -112, and -131 series
airplanes. This action requires repetitive inspections to detect
fatigue cracking in the area surrounding certain attachment holes of
the forward pintle fittings of the main landing gear (MLG) and the
actuating cylinder anchorage fittings on the inner rear spar; and
repair, if necessary. This amendment also provides for optional
terminating action for the repetitive inspections. This amendment is
prompted by issuance of mandatory continuing airworthiness information
by a foreign civil airworthiness authority. The actions specified in
this AD are intended to detect and correct fatigue cracking on the
inner rear spar of the wings, which could result in reduced structural
integrity of the airplane.
DATES: Effective December 18, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 18, 1998.
Comments for inclusion in the Rules Docket must be received on or
before January 4, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-264-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 A321-
111, -112, and -131 series airplanes. The DGAC advises that, during
full-scale testing of a Model A320 test article, fatigue cracking was
detected between 64,120 and 82,607 total simulated flight cycles.
Investigation revealed that the fatigue cracks originated at the
attachment holes of the forward pintle fittings and the actuating
cylinder anchorage fittings. Such fatigue cracking on the inner rear
spar of the wings, if not detected and corrected, could result in
reduced structural integrity of the airplane.
Similar Airplane Models
The inner rear spar construction of the wings of Model A321 series
airplanes is similar in design to that of Model A320 series airplanes.
Therefore, Model A321 series airplanes may be subject to the same
unsafe condition revealed on the Model A320 series airplanes.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A320-57-1101, dated July 24,
1997, which describes procedures for repetitive ultrasonic inspections
to detect fatigue cracking in the area surrounding certain attachment
holes of the forward pintle fittings of the main landing gear (MLG) and
the actuating cylinder anchorage fittings on the inner rear spar.
Airbus also has issued Service Bulletin A320-57-1100, including
Appendix 1, both dated July 28, 1997. This service bulletin describes
procedures for visual and eddy current inspections to detect cracking
in the area surrounding certain attachment holes of the forward pintle
fittings of the MLG and the actuating cylinder anchorage fittings on
the inner rear spar; follow-on corrective actions, if necessary; and
rework of the attachment holes, which eliminates the need for the
repetitive ultrasonic inspections described in Airbus Service Bulletin
A320-57-1101.
Accomplishment of the actions specified in Airbus Service Bulletin
A320-57-1101 or A320-57-1100 is intended to adequately address the
identified unsafe condition. The DGAC classified Airbus Service
Bulletin A320-57-1101 as mandatory and issued French airworthiness
directive 98-212-116(B), dated June 3, 1998, in order to assure the
continued airworthiness of these airplanes in France.
FAA's Conclusions
This airplane model is manufactured in France and is 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 registered
in the United States, this AD is being issued to detect and correct
fatigue cracking on the inner rear spar of the wings, which could
result in reduced structural integrity of the airplane. This AD
requires accomplishment of the actions specified in Airbus Service
Bulletin A320-57-1101 described previously, except as discussed below.
This AD also provides for optional terminating action for the
repetitive inspections required by this AD.
Operators should note that, in consonance with the findings of the
DGAC, the FAA has determined that the repetitive inspections required
by this AD can be allowed to continue in lieu of accomplishment of a
terminating action. In making this determination, the FAA considers
that, in this case, long-term continued operational safety will be
adequately assured by accomplishing the repetitive inspections
[[Page 66754]]
to detect cracking before it represents a hazard to the airplane.
Differences Between Rule and Service Bulletin
Operators also should note that, although the service bulletin
specifies that the manufacturer may be contacted for disposition of
cracking conditions in the area surrounding certain attachment holes of
the forward pintle fittings of the MLG, this AD requires the repair of
the fatigue cracking 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 is acceptable for
compliance with this AD.
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 20 work hours to
accomplish the required inspection, at an average labor rate of $60 per
work hour. Based on these figures, the cost impact of the inspection
proposed by this AD would be $1,200 per airplane, per inspection cycle.
Should an operator elect to accomplish the optional terminating
action that is provided by this AD action, it would take approximately
520 work hours to accomplish, at an average labor rate of $60 per work
hour. The cost of required parts would be approximately $17,540 per
airplane. Based on these figures, the cost impact of the optional
terminating action would be $48,740 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 98-NM-264-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.
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:
98-25-05 Airbus Industrie: Amendment 39-10928. Docket 98-NM-264-AD.
Applicability: Model A321-111, -112, and -131 series airplanes;
except those on which Airbus Modification 24977 has been
accomplished during production, or on which the action described in
Airbus Service Bulletin A320-57-1100, dated July 28, 1997 (Airbus
Modification 26010) has 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 (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 fatigue cracking on the inner rear spar of
the wings, which could result in reduced structural integrity of the
airplane, accomplish the following:
(a) Prior to the accumulation of 20,000 total flight cycles, or
within 120 days after the effective date of this AD, whichever
occurs later, perform an ultrasonic inspection to detect fatigue
cracking in the area
[[Page 66755]]
surrounding certain attachment holes of the forward pintle fittings
of the main landing gear (MLG) and the actuating cylinder anchorage
fittings on the inner rear spar, in accordance with Airbus Service
Bulletin A320-57-1101, dated July 24, 1997.
(1) If no cracking is detected, prior to further flight, repair
the sealant in the inspected areas and repeat the ultrasonic
inspections thereafter at intervals not to exceed 7,700 flight
cycles.
(2) If any cracking is detected, 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).
(b) Accomplishment of visual and eddy current inspections to
detect cracking in the area surrounding certain attachment holes of
the forward pintle fittings of the MLG and the actuating cylinder
anchorage fittings on the inner rear spar; follow-on corrective
actions, as applicable; and rework of the attachment holes; in
accordance with Airbus Service Bulletin A320-57-1100, dated July 28,
1997, constitutes terminating action for the repetitive inspection
requirements of this AD. If any cracking is detected during
accomplishment of any inspection described in the service bulletin,
and the service bulletin specifies to contact Airbus for appropriate
action: Prior to further flight, repair in accordance with a method
approved by either the Manager, International Branch, ANM-116, or
the DGAC (or its delegated agent).
(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.
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.
(d) 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.
(e) Except as provided by paragraphs (a)(2) and (b) of this AD,
the actions shall be done in accordance with Airbus Service Bulletin
A320-57-1101, dated July 24, 1997. 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 98-212-116(B), dated June 3, 1998.
(f) This amendment becomes effective on December 18, 1998.
Issued in Renton, Washington, on November 25, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-32099 Filed 12-2-98; 8:45 am]
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