[Federal Register Volume 63, Number 56 (Tuesday, March 24, 1998)]
[Proposed Rules]
[Pages 14044-14047]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-7525]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-341-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, and A300-600
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 A300, A310, and
A300-600 series airplanes. This proposal would require repetitive
inspections to detect corrosion and cracks on the bottom area of the
wing skin, and corrective action, 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 corrosion and cracks
on the bottom area of the wing skin, which could result in reduced
structural integrity of the airplane.
[[Page 14045]]
DATES: Comments must be received by April 23, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-341-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 97-NM-341-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. 97-NM-341-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 A300, A310, and A300-600 series
airplanes. The DGAC advises that it has received reports of corrosion
on the lower wing root joint, on the bottom wing skin, inboard and
outboard of the external lower surface splice. Most of the corrosion
was found in the area aft of frame 43, and around fasteners, starting
from the edges of the countersinks. Such corrosion could lead to
cracking in this area. This condition, if not detected and corrected in
a timely manner, could result in reduced structural integrity of the
airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-57-0204, dated December 4,
1995 (for Model A300 series airplanes); A310-57-2061, dated December 4,
1995 (for Model A310 series airplanes); and A300-57-6047, Revision 01,
dated October 16, 1996, as revised by Change Notice 1.A., dated
February 24, 1997 (for Model A300-600 series airplanes). These service
bulletins describe procedures for repetitive detailed visual
inspections to detect corrosion and cracks of the bottom wing skin
area, inboard and outboard of the rib 1 external lower surface splice,
between frame 40 and frame 47. The service bulletins also describe
procedures for removal of any corrosion found, application of
protective treatment, and non-destructive inspection for cracks, if
necessary.
The DGAC classified these service bulletins as mandatory and issued
French airworthiness directive 97-006-210(B), dated January 2, 1997, 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 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
the actions specified in the service bulletins described previously,
except as discussed below.
Differences Between the Proposal and the Related Service Bulletins
The proposed rule would differ from the Airbus service bulletins
described previously in that, unlike the compliance time threshold and
intervals provided in the service bulletins, this proposed AD would
reference tables that provide compliance time thresholds and intervals
in flight cycles and corresponding flight hours for each airplane
model. The thresholds and intervals defined in the service bulletins
are based on an Average Flight Time (AFT) for each airplane model. For
those airplanes that are operated with a flight duration different from
the AFT, an adjustment must be made to the thresholds and intervals. To
provide clarification of the appropriate thresholds and intervals,
Tables 1, 2, 3, 4, and 5 have been included in the proposed AD to
provide specific thresholds and intervals, and to eliminate the need
for operators to calculate differing adjustments for various AFT's.
Operators also should note that the service bulletins specify that
the manufacturer may be contacted for disposition of certain repair
conditions. However, this proposal would require the repair of those
conditions to be accomplished in accordance with a method approved by
the FAA.
Cost Impact
The FAA estimates that 49 Model A300 and A310 series airplanes, and
51 Model A300-600 series airplanes, of U.S. registry would be affected
by this proposed AD, that it would take approximately 8 work hours per
inspection cycle to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Based on these figures, the
cost impact of the proposed AD on U.S. operators is estimated to be
$48,000, or $480 per airplane, per inspection cycle.
[[Page 14046]]
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: Docket 97-NM-341-AD.
Applicability: All Model A300, A310, and A300-600 series
airplanes, 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 (d) 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 corrosion and cracks on the bottom wing
skin area, which could result in reduced structural integrity of the
airplane, accomplish the following:
(a) At the time specified in paragraph (a)(1), (a)(2), (a)(3),
or (a)(4) of this AD, as applicable: Except as required by
paragraphs (b) and (c) of this AD, perform an inspection for
corrosion and cracks on the bottom wing skin area, and accomplish
follow-on corrective actions, in accordance with Airbus Service
Bulletin A300-57-0204, dated December 4, 1995 (for Model A300 series
airplanes); A310-57-2061, dated December 4, 1995 (for Model A310
series airplanes); or A300-57-6047, Revision 01, dated October 16,
1996, as revised by Change Notice 1.A., dated February 24, 1997 (for
Model A300-600 series airplanes); as applicable; subsequently
referred to in this AD as the ``applicable'' service bulletins.
Thereafter, repeat the inspection at intervals not to exceed 5
years.
(1) For airplanes with 5 years or less since date of
manufacture: Prior to the accumulation of 5 years since date of
manufacture or within 18 months after the effective date of this AD,
whichever occurs later.
(2) For airplanes with more than 5 years, but less than 15 years
since date of manufacture: Within 18 months after the effective date
of this AD.
(3) For airplanes with more than 15 years, but less than 20
years since date of manufacture: Within 12 months after the
effective date of this AD.
(4) For airplanes with more than 20 years since date of
manufacture: Within 6 months after the effective date of this AD.
(b) If any corrosion or crack is found during an inspection
required by paragraph (a) of this AD, and the applicable service
bulletin specifies to contact Airbus for an appropriate action:
Prior to further flight, repair in accordance with a method approved
by the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate.
(c) If any crack is found during an inspection required by
paragraph (a) of this AD, and the applicable service bulletin
specifies to refer to Table B, Figure 4, of the service bulletin to
determine the fatigue inspection threshold and interval: Use Table
1, 2, 3, 4, or 5, of this AD, as applicable, to determine the
fatigue inspection threshold and interval in flight cycles (FC) or
flight hours (FH).
Table 1.--Airbus Service Bulletin A300-57-204 (Model A300 B2) Fatigue Inspection
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Detailed visual
Threshold (FC or FH, interval (FC or FH, NDT (HFEC) interval (FC or FH,
Area whichever occurs whichever occurs whichever occurs first)
first) first)
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1, 2, 3a \1\.................. 10,400 FC or 15,800 10,400 FC or 15,800 10,400 FC or 15,800 FH.
FH. FH.
3b, 4a \2\.................... 7,200 FC or 11,000 FH 2,500 FC or 3,800 FH. 6,300 FC or 9,600 FH.
4b............................ 10,400 FC or 15,800 10,400 FC or 15,800 10,400 FC or 15,800 FH.
FH. FH.
5, 6.......................... 9,900 FC or 15,100 FH 8,700 FC or 13,200 FH 9,900 FC or 15,100 FH.
7, 8.......................... 6,600 FC or 10,000 FH 5,000 FC or 7,700 FH. 6,400 FC or 9,700 FH.
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\1\ Area 3, as defined by Table B, Table 4, of SB A300-57-0204, has been split into areas 3a and 3b with a
borderline between stiffener 43.2 and lattice flange 44 for Tables 1, 2, and 3 of this AD.
\2\ Area 4, as defined by Table B, Table 4, of SB A300-57-0204, has been split into areas 4a and 4b with a
borderline between lattice flange 44 and stiffener 44.1 for Tables 1, 2, and 3 of this AD.
Table 2.--Airbus Service Bulletin A300-57-204 (Model A300 B4-100) Fatigue Inspection
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Detailed visual
Threshold (FC or FH, interval (FC or FH, NDT (HFEC) interval (FC or FH,
Area whichever occurs whichever occurs whichever occurs first)
first) first)
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1, 2, 3a...................... 9,500 FC or 15,600 FH 8,600 FC or 14,200 FH 9,500 FC or 15,600 FH.
[[Page 14047]]
3b, 4a....................... 6,700 FC or 12,000 FH 2,000 FC or 3,300 FH. 5,000 FC or 8,200 FH.
4b............................ 9,500 FC or 15,600 FH 8,600 FC or 14,200 FH 9,500 FC or 15,600 FH.
5, 6......................... 8,200 FC or 13,400 FH 7,200 FC or 11,900 FH 8,200 FC or 13,400 FH.
7, 8.......................... 4,600 FC or 7,600 FH. 3,600 FC or 5,900 FH. 4,500 FC or 7,400 FH
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Table 3.--Airbus Service Bulletin A300-57-204 (Model A300B4-200) Fatigue Inspection
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Detailed visual
Threshold (FC or FH, interval (FC or FH, NDT (HFEC) interval (FC or FH,
Area whichever occurs whichever occurs whichever occurs first)
first) first)
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1, 2, 3a...................... 9,900 FC or 21,100 FH 9,000 FC or 19,200 FH 9,900 FC or 12,100 FH.
3b, 4a........................ 7,000 FC or 14,900 FH 2,100 FC or 4,500 FH. 5,200 FC or 11,100 FH.
4b............................ 9,900 FC or 21,100 FH 9,000 FC or 19,200 FH 9,900 FC or 21,100 FH.
5, 6.......................... 8,500 FC or 18,100 FH 7,500 FC or 16,000 FH 8,500 FC or 18,100 FH.
7, 8.......................... 4,800 FC or 10,200 FH 3,700 FC or 7,900 FH. 4,700 FC or 10,000 FH.
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Table 4.--Airbus Service Bulletin A310-57-2061 (Model A310-200 and A310-300) Fatigue Inspection
----------------------------------------------------------------------------------------------------------------
Detailed visual
Threshold (FC or FH, interval (FC or FH, NDT (HFEC) interval (FC or FH,
Area whichever occurs whichever occurs whichever occurs first)
first) first)
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1............................. 12,800 FC or 36,600 10,500 FC or 29,900 12,800 FC or 36,600 FH.
FH. FH.
2............................. 5,700 FC or 16,300 FH 4,600 FC or 13,100 FH 5,700 FC or 16,300 FH.
3, 5.......................... 5,100 FC or 14,700 FH 4,100 FC or 11,800 FH 5,100 FC or 14,700 FH.
4............................. 4,500 FC or 12,800 FH 1,800 FC or 5,100 FH. 4,500 FC or 12,800 FH.
6............................. 19,400 FC or 55,300 16,500 FC or 47,000 19,400 FC or 55,300 FH.
FH. FH.
7............................. 16,300 FC or 46,500 13,800 FC or 39,500 16,300 FC or 46,500 FH.
FH. FH.
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Table 5.--Airbus Service Bulletin A300-57-6047 (Model A300-600) Fatigue Inspection
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Detailed visual
Threshold (FC or FH, interval (FC or FH, NDT (HFEC) interval (FC or FH,
Area whichever occurs whichever occurs whichever occurs first)
first) first)
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1, 2.......................... 13,600 FC or 42,900 11,800 FC or 37,000 15,500 FC or 48,800 FH.
FH. FH.
3............................ 6,500 FC or 20,400 FH 5,800 FC or 18,400 FH 6,900 FC or 21,600 FH.
4, 6.......................... 4,800 FC or 15,100 FH 4,500 FC or 14,200 FH 5,000 FC or 15,700 FH.
5............................. 2,100 FC or 6,500 FH. 900 FC or 3,000 FH... 2,100 FC or 6,500 FH.
7............................. 5,700 FC or 18,100 FH 5,500 FC or 17,200 FH 6,300 FC or 19,800 FH.
8............................. 2,400 FC or 7,400 FH. 2,100 FC or 6,500 FH. 2,400 FC or 7,400 FH.
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(d) 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.
(e) 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 97-006-210(B), dated January 2, 1997.
Issued in Renton, Washington, on March 17, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-7525 Filed 3-23-98; 8:45 am]
BILLING CODE 4910-13-U
