[Federal Register Volume 64, Number 175 (Friday, September 10, 1999)]
[Proposed Rules]
[Pages 49110-49112]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-23477]
[[Page 49110]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-184-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 and A340 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 certain Airbus Model A330 and A340
series airplanes. This proposal would require repetitive detailed
visual inspections to detect cracking of the vertical flange of the
inboard Z-stiffeners of the centerline panel of the fuselage belly
fairing; and corrective actions, if necessary. This proposed AD also
provides for optional terminating action for the repetitive
inspections. 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 cracking of the vertical flange of the
inboard Z-stiffeners of the centerline panel of the fuselage belly
fairing, which could result in reduced structural integrity of the
belly fairing.
DATES: Comments must be received by October 12, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-184-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: 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:
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.
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 99-NM-184-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-114, Attention: Rules
Docket No. 99-NM-184-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 certain Airbus Model A330 and A340 series
airplanes. The DGAC advises that during full-scale fatigue testing,
fatigue cracking occurred in one of the inboard Z-stiffeners at the
fitting retaining the centerline panel between the main landing gear
doors. The cracking initiated in the cut-out radius of the vertical
flange and propagated downward. Such fatigue cracking, if not detected
and corrected, could result in reduced structural integrity of the
belly fairing.
Explanation of Relevant Service Information
The manufacturer has issued Airbus Service Bulletins A330-53-3020
(for Model A330 series airplanes) and A340-53-4029 (for Model A340
series airplanes); each dated November 30, 1995. These service
bulletins describe procedures for repetitive detailed visual
inspections to detect cracking of the vertical flange of the inboard Z-
stiffeners of the centerline panel of the fuselage belly fairing; and
corrective actions, if necessary. The detailed visual inspection
includes the left- and right-hand sides of the centerline panel between
the main landing gear doors. The corrective actions reference the
accomplishment of Airbus Service Bulletin A330-53-3019 (for Model A330
series airplanes) or A340-53-4028 (for Model A340 series airplanes);
each dated November 30, 1995. These service bulletins describe
procedures for modification of the vertical flange of the inboard Z-
stiffeners of the centerline panel of the fuselage belly fairing. The
modification involves the installation of a new cut-out of the vertical
flange of the inboard Z-stiffeners; and installation of an external
reinforcement plate (strap), and modification of the assembly (length
of fasteners) between the Z-stiffeners and the belly fairing panel.
Accomplishment of the modification of the vertical flange of the
inboard Z-stiffeners of the centerline panel of the fuselage belly
fairing eliminates the need for the repetitive inspections, provided
that all cracking is eliminated. Accomplishment of the actions
specified in the applicable service bulletins is intended to adequately
address the identified unsafe condition. The DGAC classified Airbus
Service Bulletins A330-53-3020 and A340-53-4029 as mandatory and issued
French airworthiness directives 96-056-029 (B) (for Model A330 series
airplanes), and 96-057-042 (B) (for Model A340 series airplanes); each
dated March 13, 1996; 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
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
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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, this
proposed AD would require accomplishment of the actions specified in
the service bulletins described previously, except as discussed below.
This proposed AD also would provide for optional terminating action for
the repetitive inspections.
Operators should note that, in consonance with the findings of the
DGAC, the FAA has determined that the repetitive inspections proposed
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 to
detect cracking before it represents a hazard to the airplane.
Differences Between Proposed Rule and Service Bulletin
Unlike the procedures described in Airbus Service Bulletins A330-
53-3020 (for Model A330 series airplanes) and A340-53-4029 (for Model
A340 series airplanes), this proposed AD would not permit further
flight if cracks are detected of the vertical flange of the inboard Z-
stiffeners of the centerline panel of the fuselage belly fairing. The
FAA has determined that, because of the safety implications and
consequences associated with such cracking, any vertical flange of the
inboard Z-stiffener that is found to be cracked must be repaired or
modified to eliminate any cracking, or repaired (for any cracking that
cannot be eliminated), prior to further flight.
Operators also should note that, although the service bulletins
specify that the manufacturer may be contacted for disposition of
certain cracking conditions, this proposal would require the repair of
those conditions to be accomplished in accordance with a method
approved by the FAA.
Cost Impact
None of the airplanes affected by this action are on the U.S.
Register. All airplanes included in the applicability of this proposed
rule currently are operated by non-U.S. operators under foreign
registry; therefore, they are not directly affected by this proposed AD
action. However, the FAA considers that this proposed 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 1 work hour to
accomplish the proposed inspection, at an average labor rate of $60 per
work hour. Based on these figures, the cost impact of this AD would be
$60 per airplane, per inspection cycle.
Should an operator elect to accomplish the optional terminating
action proposed by this AD, it would require approximately 7 work hours
to accomplish the proposed optional terminating action, at an average
labor rate of $60 per work hour. Required parts would cost
approximately $2,350 per airplane. Based on these figures, the cost
impact of the optional terminating action is estimated to $2,770 per
airplane.
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 99-NM-184-AD.
Applicability: Model A330 and A340 series airplanes; except
those airplanes on which Airbus Modification 42605, or Airbus
Service Bulletin A330-53-3019 (for Model A330 series airplanes) or
A340-53-4028 (for Model A340 series airplanes) 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 of the vertical flange of
the inboard Z-stiffeners of the centerline panel of the fuselage
belly fairing, which could result in reduced structural integrity of
the belly fairing, accomplish the following:
Repetitive Detailed Visual Inspections
(a) Prior to the accumulation of 5,500 total flight cycles, or
within 500 flight hours after the effective date of this AD,
whichever occurs later, perform a detailed visual inspection to
detect cracking of the vertical flange of the inboard Z-stiffeners
of the centerline panel of the fuselage belly fairing, in accordance
with Airbus Service Bulletin A330-53-3020 (for Model A330 series
airplanes) or A340-53-4029 (for Model A340 series airplanes); each
dated November 30, 1995; as applicable.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc. may be used. Surface cleaning and
elaborate access procedures may be required.''
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(1) If no cracking is detected, repeat the inspection thereafter
at intervals not to exceed 5,500 flight cycles, until the
requirements of paragraph (b) of this AD are accomplished.
Corrective Actions
(2) If any cracking is detected during any inspection required
by this AD, prior to further flight, modify the vertical flange of
both inboard Z-stiffeners of the centerline panel of the fuselage
belly fairing and re-inspect the modified area to determine if
cracking has been eliminated, in accordance with Airbus Service
Bulletin A330-53-3019 (for Model A330 series airplanes) or A340-53-
4028 (for Model A340 series airplanes); each dated November 30,
1995; as applicable.
(i) If all cracking is not eliminated after accomplishment of
the modification, 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). For a repair
method to be approved by the Manager, International Branch, ANM-116,
as required by this paragraph, the Manager's approval letter must
specifically reference this AD.
(ii) If all cracking is eliminated after the accomplishment of
the modification, no further action is required by this AD.
Optional Terminating Action
(b) Modification of the vertical flange of both inboard Z-
stiffeners of the centerline panel of the fuselage belly fairing in
accordance with Airbus Service Bulletin A330-53-3019 (for Model A330
series airplanes) or A340-53-4028 (for Model A340 series airplanes);
each dated November 30, 1995; as applicable constitutes terminating
action for the requirements 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.
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
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 4: The subject of this AD is addressed French airworthiness
directives 96-056-029 (B) and 96-057-042 (B); each dated March 13,
1996; in order to assure the continued airworthiness of these
airplanes in France.
Issued in Renton, Washington, on September 2, 1999.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-23477 Filed 9-9-99; 8:45 am]
BILLING CODE 4910-13-U
