AD Amdt-39-10614

[Federal Register Volume 63, Number 122 (Thursday, June 25, 1998)]
[Rules and Regulations]
[Pages 34576-34578]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-16472]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-78-AD; Amendment 39-10614; AD 98-13-23]
RIN 2120-AA64


Airworthiness Directives; Airbus Model 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 A300-600 series airplanes, that 
requires inspections to detect corrosion and cracking of the lower 
horizontal stabilizer cutout longeron, the corner fitting, the skin 
strap, and the outer skin; and repair, if necessary. This amendment is 
prompted by cracking found at the lower corner of the horizontal 
stabilizer cutout longeron during a full scale fatigue test. The 
actions specified by this AD are intended to prevent such cracking, 
which could result in reduced structural integrity of the horizontal-
stabilizer cutout longeron.

DATES: Effective July 30, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 30, 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 A300-600 
series airplanes was published in the Federal Register on December 12, 
1995 (60 FR 63665). That action proposed to require repetitive visual 
and eddy current inspections to detect corrosion and fatigue cracking 
of the lower horizontal stabilizer cutout longeron, the corner fitting, 
the skin strap, and the skin between FR87 and FR89 and between STGR24 
and STGR27, left-hand and right-hand. That action also proposed to 
require repetitive rotating probe inspections to detect cracks in the 
fastener holes at the same locations; and repair or certain 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 comments received.

Support for the Proposal

    One commenter has no objection to the proposed rule.

Request to Revise Compliance Time to Permit ``Adjustment of Range''

    One commenter, the manufacturer, requests that the compliance times 
for the inspection threshold and the repetitive intervals proposed be 
revised to follow the recommendations of the Airbus service bulletin 
specified in the proposed rule. That service bulletin specifies that 
inspection thresholds and intervals may be adjusted based on certain 
average flight operations of the airplane. The commenter states that 
this approach was approved by the Direction Generale de l'Aviation 
Civile (DGAC), which is the airworthiness authority for France, in its 
approval of the service bulletin.
    The FAA does not concur that the compliance times should be 
revised. As explained in the proposal, the FAA has determined that such 
adjustments may not address the unsafe condition in a timely manner. In 
developing appropriate compliance times for the proposed rule, the FAA 
considered not only the manufacturer's recommendation, but the safety 
implications involved with cracking of the horizontal stabilizer cutout 
longeron and the number of landings that had been accumulated when 
cracking was detected. Therefore, this AD does not permit such 
adjustments, and no change to the compliance times of the final rule 
has been made. However, operators may request approval of an adjustment 
of the compliance time under the provisions of paragraph (f) of this 
AD, provided that such adjustment provides an acceptable level of 
safety.

Remove Touch-and-Go Landings From the Total Number of Landings

    This same commenter requests that touch-and-go landings not be 
included in calculating the total number of

[[Page 34577]]

airplane landings. The commenter points out that most of the relevant 
fatigue parameters for touch-and-go flights are less significant than 
for conditions of normal flight. Further, the commenter states that 
including touch-and-go's in the total landing count for an individual 
airplane is too conservative, considering the high penalty of counting 
each touch-and-go.
    The FAA does not concur. Fatigue cracking has been found at the 
lower corner of the horizontal stabilizer cutout longeron. Since 
fatigue cracking in that area is aggravated by landing, the FAA finds 
that all touch-and-go landings must be counted in determining the total 
number of landings between consecutive inspections.

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 2 Airbus Model A300-600 series airplanes of 
U.S. registry will be affected by this AD, that it will take 
approximately 268 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 $32,160, or $16,080 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the proposed 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:

98-13-23  Airbus Industrie: Amendment 39-10614. Docket 95-NM-78-AD.

    Applicability: Model A300-600 series airplanes on which Airbus 
Modification No. 6146 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 
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 use the authority 
provided in paragraph (f) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced structural integrity of the horizontal 
stabilizer cutout longeron due to fatigue cracking, accomplish the 
following:
    (a) Prior to the accumulation of 18,000 total landings, or 
within 2,000 landings after the effective date of this AD, whichever 
occurs later: Perform a visual and an eddy current inspection to 
detect cracks and/or corrosion of Areas 1 and 2 of the lower 
horizontal stabilizer cutout longeron, as defined in Airbus Service 
Bulletin A300-53-6042, Revision 1, dated February 20, 1995. Perform 
the inspections in accordance with the service bulletin.
    (b) Perform a visual and an eddy current inspection to detect 
cracks and/or corrosion of Area 3 of the lower horizontal stabilizer 
cutout longeron, as defined in Airbus Service Bulletin A300-53-6042, 
Revision 1, dated February 20, 1995. Perform these inspections in 
accordance with the service bulletin, at the later of the times 
specified in paragraphs (b)(1) and (b)(2) of this AD.
    (1) Prior to the accumulation of 24,000 total landings, but not 
before the accumulation of 18,000 total landings; or
    (2) Prior to the accumulation of 2,000 landings after the 
effective date of this AD.
    (c) If no cracking is detected during any inspection required by 
this AD: Prior to further flight, cold work and ream the vacated 
fastener holes, in accordance with Airbus Service Bulletin A300-53-
6042, Revision 1, dated February 20, 1995; and perform the 
requirements of paragraph (c)(1) or (c)(2) of this AD, as 
applicable.
    (1) For airplanes on which no cracking is found in Area 1 or 2: 
Repeat the inspections required by paragraph (a) of this AD 
thereafter at intervals not to exceed 6,000 flight cycles.
    (2) For airplanes on which no cracking is found in Area 3: 
Perform the various follow-on actions in accordance with the service 
bulletin. (The follow-on actions include installing a new corner 
fitting, installing a new longeron, and performing a cold working 
procedure.) After accomplishment of these follow-on actions, no 
further action is required by this AD.
    (d) If any cracking is detected during any inspection required 
by this AD, perform the requirements of paragraph (d)(1) or (d)(2) 
of this AD, as applicable.
    (1) If any cracking is found in Area 1 or 3 that is within the 
limits specified in Airbus Service Bulletin A300-53-6042, Revision 
1, dated February 20, 1995: Prior to further flight, repair in 
accordance with the service bulletin.
    (2) If any cracking is found in Area 2, or if any cracking is 
found in any area and that cracking is beyond the limits described 
in Airbus Service Bulletin A300-53-6042, Revision 1, dated February 
20, 1995: Prior to further flight, repair in accordance with a 
method approved by the Manager, International Branch, ANM-116, FAA, 
Transport Airplane Directorate.
    (e) If any corrosion is detected during any inspection required 
by this AD, prior to further flight, repair the corrosion in 
accordance with Airbus Service Bulletin A300-53-6042, Revision 1, 
dated February 20, 1995.
    (f) 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

[[Page 34578]]

compliance with this AD, if any, may be obtained from the Manager, 
International Branch, ANM-116.

    (g) 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.
    (h) Except as provided by paragraph (d)(2) of this AD, the 
actions shall be done in accordance with Airbus Service Bulletin 
A300-53-6042, Revision 1, dated February 20, 1995. 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 94-269-171(B)R1, dated March 29, 1995.

    (i) This amendment becomes effective on July 30, 1998.

    Issued in Renton, Washington, on June 15, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-16472 Filed 6-24-98; 8:45 am]
BILLING CODE 4910-13-U