[Federal Register Volume 65, Number 122 (Friday, June 23, 2000)]
[Rules and Regulations]
[Pages 39072-39074]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-15185]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-240-AD; Amendment 39-11790; AD 2000-12-12]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A300, A300-600, and A310 
series airplanes, that currently requires inspections to detect cracks 
in the lower spar axis of the nacelle pylon between ribs 9 and 10, and 
repair, if necessary. The existing AD also provides for optional 
modification of the pylon, which terminates the inspections for Model 
A300 and A310 series airplanes and increases the threshold and 
repetitive interval of the inspections for Model A300-600 series 
airplanes. This amendment reduces the inspection threshold and requires 
repetitive inspections following accomplishment of the optional 
modification for Model A310 series airplanes. 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 prevent fatigue cracking, which could result in 
reduced structural integrity of the lower spar of the pylon.

DATES: Effective July 28, 2000.
    The incorporation by reference of Airbus Industrie Service 
Bulletins A310-54-2016, Revision 02, dated June 11, 1999, and A310-54-
2022, Revision 1, dated March 16, 1999 is approved by the Director of 
the Federal Register as of July 28, 2000.
    The incorporation by reference of the remaining Airbus Industrie 
publications was approved previously by the Director of the Federal 
Register as of June 12, 1995 (60 FR 25604, May 12, 1995).

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) by superseding AD 95-10-03, 
amendment 39-9220 (60 FR 25604, May 12, 1995), which is applicable to 
certain Airbus Model A300, A300-600, and A310 series airplanes, was 
published in the Federal Register on April 20, 2000 (65 FR 21154). The 
action proposed to continue to require inspections to detect cracks in 
the lower spar axis of the nacelle pylon between ribs 9 and 10, and 
repair, if necessary. The action also proposed to continue to provide 
for optional modification of the pylon, which terminates the 
inspections for Model A300 and A310 series airplanes and increases the 
threshold and repetitive interval of the inspections for Model A300-600 
series airplanes. The action also proposed to reduce the inspection 
threshold and require repetitive inspections following accomplishment 
of the optional modification for Model A310 series airplanes.

[[Page 39073]]

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    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 140 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 4 work hours per airplane to accomplish 
the inspection that was previously required by AD 95-10-03, and 
retained in this AD, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the inspection on U.S. 
operators is estimated to be $240 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 removing amendment 39-9220 (60 FR 
25604, May 12, 1995), and by adding a new airworthiness directive (AD), 
amendment 39-11790, to read as follows:

2000-12-12  Airbus Industrie: Amendment 39-11790. Docket 99-NM-240-
AD. Supersedes AD 95-10-03, Amendment 39-9220.
    Applicability: The following airplanes, certificated in any 
category:

--Model A300 series airplanes, as listed in Airbus Service Bulletin 
A300-54-071, Revision 1, dated October 15, 1993.
--Model A300-600 series airplanes, as listed in Airbus Service 
Bulletin A300-54-6011, Revision 1, dated October 15, 1993.
--Model A310 series airplanes, as listed in Airbus Service Bulletin 
A310-54-2016, Revision 02, dated June 11, 1999.

    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 prevent fatigue cracking, which could result in reduced 
structural integrity of the lower spar of the pylon, accomplish the 
following:

Restatement of Certain Requirements of AD 95-10-03

Model A300 Series Airplanes

    (a) For Model A300 B4-2C, B2K-3C, B2-203, B4-103, and B4-203 
series airplanes: Prior to the accumulation of 9,000 total landings, 
or within 500 landings after June 12, 1995 (the effective date of AD 
95-10-03, amendment 39-9220), whichever occurs later, perform an 
internal eddy current inspection to detect cracks in the lower spar 
axis of the pylon between ribs 9 and 10, in accordance with Airbus 
Industrie Service Bulletin A300-54-071, dated November 12, 1991; or 
Revision 1, dated October 15, 1993.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 2,500 landings.
    (2) If any crack is found that is less than or equal to 30 mm: 
Perform subsequent inspections and repair in accordance with the 
methods and times specified in the service bulletin.
    (3) If any crack is found that is greater than 30 mm, but less 
than 100 mm: Prior to the accumulation of 250 landings after crack 
discovery, 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).
    (4) If any crack is found that is greater than or equal to 100 
mm: Prior to further flight, repair in accordance with a method 
approved by the Manager, International Branch, ANM-116; or the DGAC 
(or its delegated agent).
    (5) Accomplishment of the modification specified in Airbus 
Industrie Service Bulletin A300-54-0079, dated October 15, 1993, 
constitutes terminating action for the inspections required by 
paragraph (a) of this AD.

Model A300-600 Series Airplanes

    (b) For Model A300-600 B4-620, C4-620, B4-622R, and B4-622 
series airplanes: Except as provided by paragraph (b)(5) of this AD, 
prior to the accumulation of 4,000 total landings, or within 500 
landings after June 12, 1995 (the effective date of AD 95-10-03), 
whichever occurs later, perform an internal eddy current inspection 
to detect cracks in the lower spar axis of the pylon between ribs 9 
and 10, in accordance with Airbus Industrie Service Bulletin A300-
54-6011, dated November 12, 1991, as amended by Service Bulletin 
Change Notice O.A., dated July 10, 1992; or Revision 1, dated 
October 15, 1993.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 2,500 landings.
    (2) If any crack is found that is less than or equal to 30 mm: 
Perform subsequent inspections and repair in accordance with the 
methods and times specified in the service bulletin.
    (3) If any crack is found that is greater than 30 mm, but less 
than 100 mm: Prior to the accumulation of 250 landings after crack 
discovery, repair in accordance with a method approved by the 
Manager, International Branch, ANM-116; or the Direction Generale de 
l'Aviation Civile (DGAC) (or its delegated agent).
    (4) If any crack is found that is greater than or equal to 100 
mm: Prior to further flight, repair in accordance with a method 
approved by the Manager, International Branch, ANM-116; or the DGAC 
(or its delegated agent).
    (5) Accomplishment of the modification specified in Airbus 
Industrie Service Bulletin A300-54-6019, dated October 15, 1993, 
increases the threshold and repetitive interval of the inspections 
required by paragraph (b) of this AD to the threshold and

[[Page 39074]]

interval specified in paragraph 2.D. of the Accomplishment 
Instructions of Airbus Industrie Service Bulletin A300-54-6011, 
Revision 1, dated October 15, 1993.

New Requirements of This AD

Model A310 Series Airplanes

    (c) For Model A310-221, -222, -322, -324, and -325 series 
airplanes: Perform an internal eddy current inspection to detect 
cracks in the lower spar axis of the pylon between ribs 9 and 10, in 
accordance with Airbus Industrie Service Bulletin A310-54-2016, 
dated November 12, 1991; or Revision 1, dated October 15, 1993; or 
Revision 02, dated June 11, 1999; at the time specified in paragraph 
(d) of this AD.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 2,500 landings.
    (2) If any crack is found that is less than or equal to 30 mm: 
Perform subsequent inspections and repair in accordance with the 
methods and times specified in the service bulletin.
    (3) If any crack is found that is greater than 30 mm, but less 
than 100 mm: Prior to the accumulation of 250 landings after crack 
discovery, repair in accordance with a method approved by the 
Manager, International Branch, ANM-116; or the DGAC (or its 
delegated agent).
    (4) If any crack is found that is greater than or equal to 100 
mm: Prior to further flight, repair in accordance with a method 
approved by the Manager, International Branch, ANM-116; or the DGAC 
(or its delegated agent).
    (5) Accomplishment of the modification specified in Airbus 
Industrie Service Bulletin A310-54-2022, dated October 15, 1993; or 
Revision 01, dated March 16, 1999; increases the threshold and 
repetitive interval of the inspections required by paragraph (c) of 
this AD to the threshold and interval specified in paragraph 2.D. of 
the Accomplishment Instructions of Airbus Industrie Service Bulletin 
A310-54-2016, Revision 02, dated June 11, 1999.
    (d) Perform the initial inspection required by paragraph (c) of 
this AD at the earlier of the times specified by paragraphs (d)(1) 
and (d)(2) of this AD.
    (1) Prior to the accumulation of 25,000 total landings, or 
within 500 landings after June 12, 1995, whichever occurs later.
    (2) At the applicable time specified by paragraph (d)(2)(i), 
(d)(2)(ii), or (d)(2)(iii) of this AD.
    (i) For airplanes that have accumulated fewer than 10,000 
landings as of the effective date of this AD: Perform the inspection 
prior to the accumulation of 3,800 total landings, or within 1,500 
landings after the effective date of this AD, whichever occurs 
later.
    (ii) For airplanes that have accumulated 10,000 total landings 
or more, but fewer than 20,000 total landings, as of the effective 
date of this AD: Perform the inspection within 1,000 landings after 
the effective date of this AD.
    (iii) For airplanes that have accumulated 20,000 total landings 
or more as of the effective date of this AD: Perform the inspection 
within 500 landings after the effective date of this AD.

Alternative Methods of Compliance

    (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.

Special Flight Permits

    (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.

Incorporation by Reference

    (g) Except as provided by paragraphs (a)(3), (a)(4), (b)(3), 
(b)(4), (c)(3), and (c)(4) of this AD, the actions shall be done in 
accordance with the following Airbus Industrie service bulletins, as 
applicable.

------------------------------------------------------------------------
  Airbus Industrie Service
        Bulletin No.          Revision  Level    Service Bulletin  Date
------------------------------------------------------------------------
A300-54-071.................  Original.......  November 12, 1991.
A300-54-071.................  1..............  October 15, 1993.
A300-54-0079................  Original.......  October 15, 1993.
A300-54-6011................  Original.......  November 12, 1991.
Change Notice O.A. A300-54-   Original.......  July 10, 1992.
 6011.
A300-54-6011................  1..............  October 15, 1993.
A300-54-6019................  Original.......  October 15, 1993.
A310-54-2016................  Original.......  November 12, 1991.
A310-54-2016................  1..............  October 15, 1993.
A310-54-2022................  Original.......  October 15, 1993.
A310-54-2022................  01.............  March 16, 1999.
A310-54-2016................  02.............  June 11, 1999.
------------------------------------------------------------------------

    (1) The incorporation by reference of Airbus Industrie Service 
Bulletin
    A310-54-2016, Revision 02, dated June 11, 1999; and A310-54-
2022, Revision 1, dated March 16, 1999, is approved by the Director 
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51.
    (2) The incorporation by reference of the remaining Airbus 
Industrie publications was approved previously by the Director of 
the Federal Register as of June 12, 1995 (60 FR 25604, May 12, 
1995).
    (3) 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 1999-237-285(B), dated June 2, 1999.

    (h) This amendment becomes effective on July 28, 2000.

    Issued in Renton, Washington, on June 9, 2000.
Donald L. Riggin,
 Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-15185 Filed 6-22-00; 8:45 am]
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