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

[Federal Register Volume 63, Number 180 (Thursday, September 17, 1998)]
[Rules and Regulations]
[Pages 49656-49657]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-24871]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-17-AD; Amendment 39-10763; AD 98-19-22]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 and A300-600 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 Model A310 and A300-600 series airplanes, 
that requires repetitive visual inspections to detect corrosion on the 
lower rim area of the fuselage rear pressure bulkhead; and follow-on 
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 corrosion at the lower rim area of the fuselage 
rear pressure bulkhead, which could result in reduced structural 
integrity of the bulkhead, and consequent decompression of the cabin.

DATES: Effective October 22, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 22, 1998.

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 Model A310 and 
A300-600 series airplanes was published in the Federal Register on 
March 20, 1998 (63 FR 13572). That action proposed to require 
repetitive visual inspections to detect corrosion on the lower rim area 
of the fuselage rear pressure bulkhead; and follow-on actions, if 
necessary.
    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.
    The commenter, Airbus, requests that the applicability of the 
proposed rule be clarified. The commenter states that the words ``in 
production'' were omitted from the translation of the relevant French 
airworthiness directive. The commenter indicates that the proposed AD 
should not apply to airplanes on which Airbus Modification 6788 was 
installed in production of the airplane. The commenter explains that 
those airplanes have skin panel corrosion protection that airplanes on 
which the modification described in Airbus Service Bulletin A310-53-
2036 or A300-53-6017 do not have. Consequently, the latter airplanes 
must be inspected repetitively (every five years) for corrosion of the 
panels.
    The FAA concurs with this request for the reasons provided by the 
commenter. The applicability of this final rule has been revised 
accordingly.
    The manufacturer also notes that Revision 01 of the service 
bulletins cited in the proposed AD has been issued, and requests that 
the proposal be revised to reference this latest revision.
    The FAA concurs. Since the issuance of the proposal, Airbus issued 
Service Bulletins A310-53-2092 (for Model A310 series airplanes) and 
A300-53-6066 (for Model A300-600 series airplanes), both Revision 01, 
both dated March 11, 1998. Revision 01 of the service bulletins is 
essentially identical to the original issue; however, Revision 01 
includes minor editorial changes. This final rule has been revised to 
include Revision 01 of these service bulletins as an additional source 
of service information.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 90 Model A310 and A300-600 series airplanes 
of U.S. registry will be affected by this AD,

[[Page 49657]]

that it will take approximately 62 work hours per airplane to 
accomplish the required actions, 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 $334,800, or $3,720 per airplane.
    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 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 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:

98-19-22  Airbus: Amendment 39-10763. Docket 98-NM-17-AD.

    Applicability: Model A310 and A300-600 series airplanes on which 
Airbus Modification 6788 has not been accomplished during 
production; 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 corrosion at the lower rim area of the 
fuselage rear pressure bulkhead, which could result in reduced 
structural integrity of the bulkhead, and consequent decompression 
of the cabin, accomplish the following:
    (a) Within 18 months after the effective date of this AD: Except 
as provided by paragraph (b) of this AD, perform a visual inspection 
to detect corrosion of the lower rim area of the aft pressure 
bulkhead, in accordance with Airbus Service Bulletin A310-53-2092 
(for Model A310 series airplanes), dated October 16, 1996, or 
Revision 01, dated March 11, 1998; or Airbus Service Bulletin A300-
53-6066 (for Model A300-600 series airplanes), dated October 16, 
1996, or Revision 01, dated March 11, 1998; as applicable. If any 
discrepancy is found, prior to further flight, repair in accordance 
with the applicable service bulletin. Thereafter, repeat the 
inspection at the interval specified in paragraph (a)(1) or (a)(2), 
as applicable.
    (1) For airplanes on which Airbus Service Bulletin A310-53-2036 
or A300-53-6017 has not been accomplished: Repeat the inspection at 
intervals not to exceed 3 years.
    (2) For airplanes on which Airbus Service Bulletin A310-53-2036 
or A300-53-6017 has been accomplished: Repeat the inspection at 
intervals not to exceed 5 years.
    (b) If any discrepancy is found during an inspection required by 
paragraph (a) of this AD, and the applicable service bulletin 
specifies to contact Airbus for 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) 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.

    (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.
    (e) Except as provided by paragraph (b) of this AD, the actions 
shall be done in accordance with Airbus Service Bulletin A310-53-
2092, dated October 16, 1996; Airbus Service Bulletin A310-53-2092, 
Revision 01, dated March 11, 1998; Airbus Service Bulletin A300-53-
6066, dated October 16, 1996; or Airbus Service Bulletin A300-53-
6066, Revision 01, dated March 11, 1998; 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 97-061-212(B), dated February 26, 1997.

    (f) This amendment becomes effective on October 22, 1998.

    Issued in Renton, Washington, on September 10, 1998.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-24871 Filed 9-16-98; 8:45 am]
BILLING CODE 4910-13-U

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