[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]


-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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]
BILLING CODE 4910-13-U