[Federal Register: March 20, 1998 (Volume 63, Number 54)]
[Rules and Regulations]               
[Page 13493-13495]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20mr98-7]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-230-AD; Amendment 39-10409; AD 98-06-31]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A300, 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 A300, A310, and A300-600 series 
airplanes, that requires inspections to detect cracking of the aft door 
frame area, and repair, 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 cracks in the aft door frame area, which 
could result in reduced structural integrity and rapid decompression of 
the airplane.

DATES: Effective April 24, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 24, 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

[[Page 13494]]

Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A300, A310, 
and A300-600 series airplanes was published in the Federal Register on 
November 26, 1997 (62 FR 63039). That action proposed to require 
inspections to detect cracking of the aft door frame area, and repair, 
if necessary.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter supports the proposed rule.

Request To Cite Latest Service Bulletins

    One commenter requests that the proposed AD be revised to cite the 
latest revision of Airbus Service Bulletins A300-53-303, A310-53-2079, 
and A300-53-6056. The commenter states that the related French 
airworthiness directive (CN) 96-135-199(B) would be revised to include 
the wording, ``SB . . . or any later approved revision.'' The commenter 
points out that the latest revisions of the service bulletins include a 
higher value for the acceptable cumulative crack length.
    The FAA does not concur with the commenter's request to cite the 
latest service bulletin. As stated in the proposal, although the 
service bulletins, in certain circumstances, provide for continued 
flight without immediate repair of the damage area, this AD does not 
permit further flight with cracks detected in the aft door frame area. 
The FAA has determined that, due to safety implications and 
consequences associated with cracking in the aft door frame area, all 
locations in the aft door frame area that are found to be cracked must 
be repaired prior to further flight. In light of this, the FAA finds it 
unnecessary to revise this final rule to cite the latest revisions of 
the service bulletins to reference a higher value for crack length.
    In addition, where a specific document is referenced in an AD, the 
use of the phrase, ``or later FAA-approved revision,'' violates Office 
of the Federal Register regulations regarding approval of material that 
is incorporated by reference. However, affected operators may request 
to use a later revision of the referenced service bulletins as an 
alternative method of compliance, under the provisions of paragraph (d) 
of the final rule.

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 as proposed.

Cost Impact

    The FAA estimates that 49 Airbus Model A300 and A310 series 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 25 work hours per airplane to accomplish the 
required inspections, and that the average labor rate is $60 per work 
hour. Based on these figures, the cost impact of the required 
inspections on U.S. operators is estimated to be $73,500, or $1,500 per 
airplane.
    The FAA estimates that 51 Airbus Model A300-600 series airplanes of 
U.S. registry will be affected by this AD, that it will take 
approximately 18 work hours per airplane to accomplish the required 
inspections, and that the average labor rate is $60 per work hour. 
Based on these figures, the cost impact of the required inspections on 
U.S. operators of Model A300-600 series airplanes is estimated to be 
$55,080, or $1,080 per airplane.
    The cost impact figures discussed above are 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:

98-06-31  Airbus Industrie: Amendment 39-10409. Docket 97-NM-230-AD.

    Applicability: Model A300, A310, and A300-600 airplanes on which 
Airbus Modification 6924 has not been installed; 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 (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 cracks in the aft door frame area, which 
could result in reduced structural integrity and possible rapid 
decompression of the aircraft, accomplish the following:
    (a) Prior to the accumulation of 10 years since date of 
manufacture, or within 12 months after the effective date of this 
AD, whichever occurs later: Except as provided by paragraphs (b) and 
(c) of this AD, accomplish a high frequency eddy current inspection 
to detect stress corrosion cracks in the aft door frame area, and 
perform the applicable corrective actions, in accordance with Airbus 
Service Bulletin A300-53-303, dated February 23, 1996 (for Model 
A300 series airplanes); A310-53-2079, dated February 23, 1996 (for 
Model A310 series airplanes); or A300-53-6056, dated February 23, 
1996 (for Model A300-600 series airplanes); subsequently referred to 
as the applicable service bulletin. Thereafter, repeat the 
inspection at intervals not to exceed 5 years, in all areas not 
repaired permanently

[[Page 13495]]

in accordance with the applicable service bulletin.
    (b) If any 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 a compliance time other than ``prior to further flight'' 
for accomplishment of the repair: Accomplish the repair prior to 
further flight in accordance with the procedures specified in the 
applicable service bulletin.
    (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, FAA, 
Transport Airplane Directorate. 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.
    (f) The actions shall be done in accordance with Airbus Service 
Bulletin A300-53-303; Airbus Service Bulletin A310-53-2079; or 
Airbus Service Bulletin A300-53-6056, all dated February 23, 1996; 
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 (CN) 96-135-199(B), dated July 17, 1996.

    (g) This amendment becomes effective on April 24, 1998.

    Issued in Renton, Washington, on March 11, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-6953 Filed 3-19-98; 8:45 am]
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