[Federal Register Volume 63, Number 131 (Thursday, July 9, 1998)]
[Rules and Regulations]
[Pages 37061-37063]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-17954]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-31-AD; Amendment 39-10649; AD 98-14-16]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 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 A300 series airplanes. This action
requires repetitive inspections to detect cracks in the forward canted
frames between fuselage frames 47a and 48 from stringer (STGR) 41 to
STGR 43; and temporary repair, or replacement of the forward canted
frame with a new frame, if necessary. 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 cracking in the forward canted frames,
which could result in failure of the forward canted frame, and
consequent reduced structural integrity of the airplane.
DATES: Effective July 24, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 24, 1998.
Comments for inclusion in the Rules Docket must be received on or
before August 10, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-31-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
[[Page 37062]]
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 A300
series airplanes. The DGAC advises that it has been informed of several
reported cases of fatigue cracking between frame 47a to 48 on the
forward canted frame from stringer (STGR) 41 to STGR 43. These cracks
were found on airplanes that had accumulated between 20,900 and 24,000
flight cycles. This condition, if not corrected, could result in
failure of the forward canted frame, and consequent reduced structural
integrity of the airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-53-0314, dated January 14,
1997, which describes procedures for repetitive eddy current
inspections to detect cracking in the forward canted frames between
fuselage frames 47a and 48 from STGR 41 to STGR 43; and temporary
repair, or replacement of the forward canted frame with a new forward
canted frame, if necessary. Following accomplishment of the
replacement, the service bulletin recommends accomplishment of the eddy
current inspections at an extended threshold and interval.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition.
The DGAC classified this service bulletin as mandatory and issued
French airworthiness directive 97-063-214(B), dated February 26, 1997,
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
cracking in the forward canted frames, which could result in failure of
the forward canted frame, and consequent reduced structural integrity
of the airplane. This AD requires accomplishment of the actions
specified in the service bulletin described previously, except as
discussed below.
Difference Between This AD and Related Service Information
Operators should note that, although the service bulletin specifies
that the manufacturer may be contacted for disposition of certain
repair conditions, this AD would require the repair of those conditions
to be accomplished in accordance with a method approved by the FAA or
the DGAC (or its delegated agent). In light of the type of repair that
would 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 would be 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 3 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 this AD would be
$180 per airplane, per inspection cycle.
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-31-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
[[Page 37063]]
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:
98-14-16 Airbus: Amendment 39-10649. Docket 98-NM-31-AD.
Applicability: Model A300 series airplanes, certificated in any
category, as listed below:
B2-1C, all serial numbers;
B2K-3C, all serial numbers;
B2-203, all serial numbers;
B4-203 having manufacturer's serial number 255; and
B4-2C having manufacturer's serial number 256.
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 (e) 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 cracking in the forward canted frames,
which could result in failure of the forward canted frame, and
consequent reduced structural integrity of the airplane, accomplish
the following:
(a) Perform an eddy current inspection to detect cracking in the
forward canted frame between fuselage frames 47a and 48 from
stringer 41 to stringer 43, in accordance with Airbus Service
Bulletin A300-53-0314, dated January 14, 1997; at the time specified
in paragraph (a)(1), (a)(2), (a)(3), or (a)(4) of this AD, as
applicable. If no crack is detected, repeat the inspection
thereafter at intervals not to exceed 2,100 flight cycles.
(1) For airplanes that have accumulated less than 11,000 flight
cycles as of the effective date of this AD: Perform the inspection
prior to the accumulation of 11,000 total flight cycles, or within
2,000 flight cycles after the effective date of this AD, whichever
occurs later.
(2) For airplanes that have accumulated 11,000 or more total
flight cycles, but less than 14,000 total flight cycles, as of the
effective date of this AD: Perform the inspection within 2,000
flight cycles after the effective date of this AD.
(3) For airplanes that have accumulated 14,000 or more total
flight cycles as of the effective date of this AD: Perform the
inspection within 1,000 flight cycles after the effective date of
this AD.
(4) For airplanes on which the forward canted frame has been
replaced with a basic frame (A53833393-200, -201, -202, -203, -206,
or -207): Perform the inspection prior to the accumulation of 11,000
total flight cycles since the frame replacement date, or within
2,100 flight cycles after the effective date of this AD, whichever
occurs later.
(b) Except as provided by paragraph (d) of this AD, if any crack
is detected during any inspection required by paragraph (a) of this
AD, prior to further flight, accomplish the requirements of either
paragraph (b)(1) or (b)(2) of this AD, in accordance with Airbus
Service Bulletin A300-53-0314, dated January 14, 1997. Thereafter,
inspect in accordance with the requirements of paragraph (c) of this
AD.
(1) Replace the forward canted frame with a new forward canted
frame. Or
(2) Perform the temporary repair and, within 1,600 flight cycles
after accomplishment of the temporary repair, replace the forward
canted frame with a new forward canted frame.
(c) Prior to accumulation of 24,600 flight cycles after
replacement of the forward canted frame with a new forward canted
frame, and thereafter at intervals not to exceed 3,200 flight
cycles: Perform an eddy current inspection to detect cracking of the
new forward canted frame in accordance with the requirements of
paragraph (a) of this AD.
(d) For airplane having manufacturer's serial number 32: If any
crack is detected during any inspection required by paragraph (a) of
this AD, prior to further flight, repair the crack in accordance
with a method approved by either the Manager, International Branch,
ANM-116, Transport Airplane Directorate, FAA, or the Direction
Generale de l'Aviation Civile (DGAC) (or its delegated agent).
(e) 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.
(f) 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.
(g) The actions shall be done in accordance with Airbus Service
Bulletin A300-53-0314, dated January 14, 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 97-063-214(B), dated February 26, 1997.
(h) This amendment becomes effective on July 24, 1998.
Issued in Renton, Washington, on June 30, 1998.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-17954 Filed 7-8-98; 8:45 am]
BILLING CODE 4910-13-U
