[Federal Register Volume 62, Number 230 (Monday, December 1, 1997)]
[Proposed Rules]
[Pages 63476-63478]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-31333]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-152-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111, -211, -212, -
214, -231, -232, and -233 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Airbus Model A320-111, -211, -
212, -214, -231, -232, and -233 series airplanes. This proposal would
require repetitive ultrasonic inspections to detect fatigue cracking in
the wing/fuselage joint cruciform fittings, and corrective actions, if
necessary. This proposal is prompted by issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. The actions specified by the proposed AD are intended to
detect and correct fatigue cracks on the wing/fuselage joint cruciform
fittings, which could result in reduced structural integrity of the
wing/fuselage.
DATES: Comments must be received by December 31, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-152-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.
The service information referenced in the proposed rule 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.
FOR FURTHER INFORMATION CONTACT: 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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
[[Page 63477]]
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-NM-152-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 97-NM-152-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
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 all Airbus Model A320-111, -211, -212, -214, -
231, -232, and -233 series airplanes. The DGAC advises that it received
a report indicating that, during full-scale fatigue testing on a Model
A320 test article, fatigue cracks were found in the structure at the
wing/fuselage joint area cruciform fitting. The cracking occurred after
104,720 and 116,536 simulated flights. This condition, if not detected
and corrected in a timely manner, could result in reduced structural
integrity of the wing/fuselage.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A320-57-1051, Revision 01, dated
March 21, 1996, which describes procedures for repetitive ultrasonic
inspections to detect fatigue cracking in the wing/fuselage joint
cruciform fittings, and corrective action, if necessary. The DGAC
classified this service bulletin as mandatory and issued French
airworthiness directive 96-299-094(B), dated December 18, 1996, in
order to assure the 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 21.29) 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 Proposed 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, the proposed AD would require accomplishment of
actions specified in the service bulletin described previously.
Differences Between the Proposal and Relevant Service Information
Operators should note that, unlike the procedures described in the
referenced service bulletin, this proposed AD would not permit further
flight with cracking detected in the wing/fuselage joint cruciform
fittings. The FAA has determined that, due to the safety implications
and consequences associated with such cracking, all fittings that are
found to be cracked must be repaired prior to further flight.
Cost Impact
The FAA estimates that 132 of U.S. registry would be affected by
this proposed AD. It would take approximately 8 work hours per airplane
to accomplish the proposed 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 on U.S. operators is estimated to be
$63,360, or $480 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this AD were not adopted.
Regulatory Impact
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Airbus Industrie: Docket 97-NM-152-AD.
Applicability: Model A320-111, -211, -212, -214, -231, -232, and
-233 series airplanes, all serial numbers, certificated in any
category.
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 (b) 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.
[[Page 63478]]
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct fatigue cracks on the wing/fuselage joint
cruciform fittings, which could result in reduced structural
integrity of the wing/fuselage, accomplish the following:
(a) Prior to the accumulation of 28,000 total landings, or
within 60 days after the effective date of this AD, whichever occurs
later, perform an ultrasonic inspection to detect fatigue cracking
in the wing/fuselage joint cruciform fittings, in accordance with
Airbus Service Bulletin A320-57-1051, Revision 01, dated March 21,
1996.
(1) If no cracking is detected, repeat the inspection thereafter
at intervals not to exceed 20,000 landings.
(2) If any crack is detected, prior to further flight, repair it
in accordance with the service bulletin. Thereafter, repeat the
inspection at the times specified in paragraph (a)(2)(i) or
(a)(2)(ii) of this AD, as applicable.
(i) If the crack that was detected and repaired was greater than
2.5 mm: Repeat the inspection prior to the accumulation of 32,000
landings since accomplishment of the repair; and thereafter at
intervals not to exceed 32,000 landings.
(ii) If the crack that was detected and repaired was less than
or equal to 2.5 mm: Repeat the inspection prior to the accumulation
of 28,000 landings since accomplishment of the repair; and
thereafter at intervals not to exceed 20,000 landings.
(b) 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 request
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.
(c) 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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 96-299-094(B), dated December 18, 1996.
Issued in Renton, Washington, on November 21, 1997.
Stewart R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-31333 Filed 11-28-97; 8:45 am]
BILLING CODE 4910-13-U
