[Federal Register Volume 65, Number 73 (Friday, April 14, 2000)]
[Rules and Regulations]
[Pages 20076-20078]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-8988]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-82-AD; Amendment 39-11612; AD 2000-05-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-600 and A310 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus A300-600 and A310 series airplanes, that 
requires repetitive high frequency eddy current (HFEC) inspections to 
detect cracking of the inner flange of fuselage frame FR73A, between 
beams 5 and 7, and corrective actions, if necessary. This amendment is 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The actions specified by 
this AD are intended to detect and correct fatigue cracking of the 
inner flange of fuselage frame FR73A, which could result in reduced 
structural integrity of the fuselage.

DATES: Effective May 19, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 19, 2000.

ADDRESSES: 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 Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Airbus A300-600 and A31 
series airplanes was published in the Federal Register on January 5, 
2000 (65 FR 397). That action

[[Page 20077]]

proposed to require repetitive high frequency eddy current (HFEC) 
inspections to detect cracking of the inner flange of fuselage frame 
FR73A, between beams 5 and 7, and corrective actions, if necessary.

Comment Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.

Request To Revise Applicability

    The commenter, the manufacturer, requests that the applicability of 
the proposed AD be revised. The commenter states that the applicability 
should reflect the fact that inspections required by the proposed AD 
are necessary only on airplanes on which Airbus Modification 06925 has 
been installed during production. Because the retrofit solution has 
better stress margins compared to those of the production solution, 
airplanes with the retrofit solution are not subject to the unsafe 
condition. The commenter also states that Model A300F4-600 (freighter) 
series airplanes should not be included in the applicability of the AD 
because no aft passenger/crew doors and no frames FR73A (which are the 
subject areas of the inspections) exist on these airplanes. The 
commenter suggests that such an exclusion in the AD can best be 
addressed by excluding airplanes on which Airbus Modification 08907 has 
been accomplished, since Modification 08907 removes the reinforcements 
installed by Modification 06925.
    The FAA concurs with the request to limit the applicability of the 
AD by including only those airplanes on which Airbus Modification 06925 
has been installed in production, and by excluding airplanes on which 
Airbus Modification 08907 has been accomplished. The FAA has determined 
that the revised applicability will more accurately reflect those 
airplanes subject to the unsafe condition that is identified and 
addressed by the AD. The applicability of the final rule has been 
revised accordingly.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule with the change described previously. 
The FAA has determined that this change will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Interim Action

    This is considered to be interim action. The inspection reports 
that are required by this AD will enable the manufacturer to obtain 
better insight into the nature, cause, and extent of the cracking, and 
eventually to develop final action to fully address the unsafe 
condition. Once final action has been identified, the FAA may consider 
further rulemaking.

Cost Impact

    The FAA estimates that 198 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour per 
airplane to accomplish the required inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $11,880, or $60 
per airplane, per inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the 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 adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 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:

2000-05-03  Airbus Industrie: Amendment 39-11612. Docket 99-NM-82-
AD.

    Applicability: Model A300-600 and A310 series airplanes, 
certificated in any category, on which Airbus Modification 06925 has 
been accomplished in production; except airplanes on which Airbus 
Modification 08907 has been accomplished.

    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 (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 fatigue cracking of the inner flange of 
fuselage frame FR73A, which could result in reduced structural 
integrity of the fuselage, accomplish the following:

HFEC Inspection

    (a) Prior to the accumulation of 18,000 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later: Perform a high frequency eddy current (HFEC) 
inspection to detect cracking of the inner flange (left and right 
sides) of the rear fuselage frame FR73A, between beams 5 and 7, in 
accordance with Airbus Service Bulletin A310-53-2107, Revision 01 
(for Model A310 series airplanes), or A300-53-6116, Revision 01 (for 
Model A300-600 series airplanes); both dated July 2, 1999; as 
applicable.
    (1) If no crack is detected, repeat the HFEC inspection 
thereafter at intervals not to exceed 5,000 flight cycles.
    (2) For any crack that is less than or equal to 0.20 inch (5.0 
millimeters) in length: Prior to further flight, accomplish either 
paragraph (a)(2)(i) or (a)(2)(ii) of this AD.
    (i) Rework the frame in accordance with the applicable service 
bulletin. Within 3,000 flight cycles after accomplishing the rework, 
replace the fuselage frame FR73A between

[[Page 20078]]

beams 5 and 7 with a new frame section in accordance with the 
applicable service bulletin. Or
    (ii) Replace the fuselage frame FR73A between beams 5 and 7 with 
a new frame section, in accordance with the applicable service 
bulletin.
    (3) For any crack greater than 0.20 inch (5.0 millimeters) in 
length: Prior to further flight, accomplish either paragraph 
(a)(3)(i) or (a)(3)(ii) of this AD.
    (i) Repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate; 
or the Direction Generale de l'Aviation Civile (DGAC) (or its 
delegated agent). Or
    (ii) Replace the fuselage frame FR73A between beams 5 and 7 with 
a new section, in accordance with the applicable service bulletin.
    (b) Within 18,000 flight cycles after any replacement 
accomplished in accordance with paragraph (a)(2)(i), (a)(2)(ii), or 
(a)(3)(ii) of this AD: Repeat the inspection specified by paragraph 
(a) of this AD. Thereafter, repeat the inspection at intervals not 
to exceed 5,000 flight cycles.
    (c) Submit a report of inspection findings (both positive and 
negative) of any inspection required by this AD to Airbus Industrie, 
Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; at the applicable time specified in paragraph 
(c)(1) or (c)(2) of this AD. The report must include the inspection 
results, a description of any discrepancies found, the airplane 
serial number, the age of the airplane since entry into service, and 
the number of landings and flight hours on the airplane. Information 
collection requirements contained in this regulation have been 
approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.) and have been assigned OMB Control Number 2120-0056.
    (1) For airplanes on which the inspection required by paragraph 
(a) of this AD is accomplished after the effective date of this AD: 
Submit the report within 10 days after performing the inspection.
    (2) For airplanes on which the inspection required by paragraph 
(a) of this AD has been accomplished prior to the effective date of 
this AD: Submit the report within 10 days after the effective date 
of this AD.

Alternative Methods of Compliance

    (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.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
Secs. 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.

Incorporation by Reference

    (f) Except as provided by paragraph (a)(3)(i) of this AD, the 
actions shall be done in accordance with Airbus Service Bulletin 
A310-53-2107, Revision 01, dated July 2, 1999, or Airbus Service 
Bulletin A300-53-6116, Revision 01, dated July 2, 1999; as 
applicable. 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 1999-013-276(B), dated January 13, 1999.

    (g) This amendment becomes effective on May 19, 2000.

    Issued in Renton, Washington, on April 5, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-8988 Filed 4-13-00; 8:45 am]
BILLING CODE 4910-13-U