AD Amdt-39-10649

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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