[Federal Register Volume 65, Number 103 (Friday, May 26, 2000)]
[Rules and Regulations]
[Pages 34055-34059]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-12814]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-251-AD; Amendment 39-11742; AD 2000-10-18]
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 Industrie Model A300, A300-600, and 
A310 series airplanes, that currently requires inspections to detect 
cracks in the lower spar axis of the pylons between ribs 6 and 7, and 
repair, if necessary. For certain Model A310 series airplanes, this 
amendment reduces the currently required inspection thresholds and 
intervals, and removes an option for a terminating modification. 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 such fatigue cracking, 
which could result in reduced structural integrity of the engine 
pylon's lower spar, and possible separation of the engine from the 
airplane.

DATES: Effective June 30, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 30, 2000.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of June 28, 1996 (61 FR 26091, May 24, 1996).

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 96-11-05, 
amendment 39-9630 (61 FR 26091, May 24, 1996), which is applicable to 
certain Airbus Industrie Model A300, A300-600, and A310 series 
airplanes, was published in the Federal Register on February 14, 2000 
(65 FR 7316). The action proposed to continue to require inspections to 
detect cracks in the lower spar axis of the engine pylons for Airbus 
Model A300 and A300-600 series airplanes, and to require accomplishment 
of the actions specified in Airbus Service Bulletin A310-54-2017, 
Revision 03, for Model A310 series airplanes.

Comments Received

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

No Objection to the Proposal

    One commenter, an operator, states that it is not affected by the 
proposed AD, and therefore has no objection or additional comments.

[[Page 34056]]

Reference to French Airworthiness Directive

    One commenter, the manufacturer, requests that the proposed AD be 
revised to include a reference to a related French airworthiness 
directive. The commenter states that the proposed AD refers to French 
airworthiness directive 1999-239-287(B), which addresses Airbus Model 
A310 series airplanes, but does not mention 1993-228-154(B)R3, which 
addresses Airbus Model A300 and A300-600 series airplanes (actions for 
those airplanes are required in existing FAA AD 96-11-05).
    The FAA acknowledges that the actions required by existing FAA AD 
96-11-05 are related to French airworthiness directive 1993-228-154(B). 
The FAA has no objection to including the reference in this AD, which 
continues to require those actions for Model A300 and A300-600 series 
airplanes. ``NOTE 3'' of the AD has been revised accordingly. However, 
although the FAA generally references the latest pertinent 
airworthiness directive issued by another airworthiness authority as an 
informational Note in the AD, this information is not intended to be an 
exhaustive list of all related mandatory continuing airworthiness 
information, and should not be considered as such.

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 change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 146 airplanes of U.S. registry that will be 
affected by this AD.
    The requirements of this AD will not add any new additional 
economic burden on affected operators, other than the costs that are 
associated with accomplishing inspections for certain airplanes at an 
earlier time than would have been required by AD 96-11-05. The current 
costs associated with this AD are reiterated (as follows) for the 
convenience of affected operators.
    The inspections that are currently required by AD 96-11-05, and 
retained in this AD, take approximately 8 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $480 per airplane, per inspection 
cycle.

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 39-9630 (61 FR 
26091, May 24, 1996), and by adding a new airworthiness directive (AD), 
amendment 39-11742, to read as follows:

2000-10-18  Airbus Industrie: Amendment 39-11742. Docket 99-NM-251-AD. 
Supersedes AD 96-11-05, Amendment 39-9630.

    Applicability: The following models, certificated in any 
category: Model A300 and A300-600 series airplanes, as listed in 
Airbus Service Bulletins A300-54-0073 and A300-54-6014, both 
Revision 1, dated March 28, 1994; and Model A310 series airplanes, 
except those on which Airbus Modification 10149 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 (m)(1) 
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 engine pylon's lower spar and 
possible separation of the engine from the airplane, accomplish the 
following:

Restatement of Certain Requirements of AD 96-11-05

Eddy Current Inspections

    (a) For Model A300 series airplanes equipped with General 
Electric CF6-50C engines, and having pylons that have not been 
modified in accordance with Airbus Industrie Service Bulletin A300-
54-0080, Revision 1, dated January 16, 1995: Prior to the 
accumulation of 10,900 total landings, or within 500 landings after 
June 28, 1996 (the effective date of AD 96-11-05, amendment 39-
9630), whichever occurs later, perform an internal eddy current 
inspection to detect cracks in the lower spar axis of the pylons 
between ribs 6 and 7, in accordance with Airbus Industrie Service 
Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 6,700 landings.
    (2) If any crack is found that is less than 35 millimeters ( 
1.38 inches), prior to further flight, stop-drill the crack in 
accordance with the procedures specified in Section 51-41-10 of the 
Structural Repair Manual (SRM). Thereafter, prior to the 
accumulation of 250 landings after crack discovery, repair in 
accordance with the service bulletin. Prior to the accumulation of 
17,900 landings after accomplishing the repair, perform an eddy 
current inspection to detect cracks at the stiffener ends, ribs 6 
and 7, at the edge of the holes made during the repair and on the 
fasteners located at the edge of the doubler, in accordance with the 
service bulletin.
    (i) If no crack is found, repeat the inspection required by 
paragraph (a)(2) of this AD thereafter at intervals not to exceed 
15,000 landings.

[[Page 34057]]

    (ii) If any crack is found, prior to further flight, 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).
    (3) If any crack is found that is greater than or equal to 35 mm 
(1.38 in.), 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).
    (b) For Model A300 series airplanes equipped with General 
Electric CF6-50C engines, and having pylons that have been modified 
in accordance with Airbus Industrie Service Bulletin A300-54-0080, 
Revision 1, dated January 16, 1995: Prior to the accumulation of 
30,300 landings since installation of the modification, or within 
500 landings after June 28, 1996, whichever occurs later, perform an 
eddy current inspection to detect cracks in the lower spar axis of 
the pylons between ribs 6 and 7, in accordance with Airbus Industrie 
Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the eddy current inspection 
thereafter at intervals not to exceed 21,300 landings.
    (2) If any crack is found, 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).
    (c) For Model A300 series airplanes equipped with Pratt & 
Whitney JT9D-59A engines, and having pylons that have not been 
modified in accordance with Airbus Industrie Service Bulletin A300-
54-0080, Revision 1, dated January 16, 1995: Prior to the 
accumulation of 8,600 total landings, or within 500 landings after 
June 28, 1996, whichever occurs later, perform an internal eddy 
current inspection to detect cracks in the lower spar axis of the 
pylons between ribs 6 and 7, in accordance with Airbus Industrie 
Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 5,700 landings.
    (2) If any crack is found that is less than 35 mm (1.38 in.), 
prior to further flight, stop-drill the crack in accordance with the 
procedures specified in Section 51-41-10 of the SRM. Thereafter, 
prior to the accumulation of 250 landings after crack discovery, 
repair in accordance with the service bulletin. Prior to the 
accumulation of 14,200 landings after accomplishing the repair, 
perform an eddy current inspection to detect cracks at the stiffener 
ends, ribs 6 and 7, at the edge of the holes made during the repair 
and on the fasteners located at the edge of the doubler, in 
accordance with the service bulletin.
    (i) If no crack is found, repeat the inspection required by 
paragraph (c)(2) of this AD thereafter at intervals not to exceed 
12,800 landings.
    (ii) If any crack is found, prior to further flight, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116; or by the DGAC (or its delegated agent).
    (3) If any crack is found that is greater than or equal to 35 mm 
(1.38 in.), 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).
    (d) For Model A300 series airplanes equipped with Pratt & 
Whitney JT9D-59A engines, and having pylons that have been modified 
in accordance with Airbus Industrie Service Bulletin A300-54-0080, 
Revision 1, dated January 16, 1995: Prior to the accumulation of 
24,000 landings since installation of the modification, or within 
500 landings after June 28, 1996, whichever occurs later, perform an 
eddy current inspection to detect cracks in the lower spar axis of 
the pylons between ribs 6 and 7, in accordance with Airbus Industrie 
Service Bulletin A300-54-0073, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the eddy current inspection 
thereafter at intervals not to exceed 18,200 landings.
    (2) If any crack is found, 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).
    (e) For Model A300-600 series airplanes equipped with General 
Electric CF6-80C2 engines, and having pylons that have not been 
modified in accordance with Airbus Industrie Service Bulletin A300-
54-6020, dated February 22, 1994: Prior to the accumulation of 9,400 
total landings, or within 500 landings after June 28, 1996, 
whichever occurs later, perform an internal eddy current inspection 
to detect cracks in the lower spar axis of the pylons between ribs 6 
and 7, in accordance with Airbus Industrie Service Bulletin A300-54-
6014, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 6,100 landings.
    (2) If any crack is found that is less than or equal to 35 mm 
(1.38 in.), prior to further flight, stop-drill the crack in 
accordance with the procedures specified in Section 51-41-10 of the 
SRM. Thereafter, prior to the accumulation of 250 landings after 
crack discovery, repair in accordance with the service bulletin. 
Prior to the accumulation of 15,600 landings after accomplishing the 
repair, perform an eddy current inspection to detect cracks at the 
stiffener ends, ribs 6 and 7, at the edge of the holes made during 
the repair and on the fasteners located at the edge of the doubler, 
in accordance with the service bulletin.
    (i) If no crack is found, repeat the inspection required by 
paragraph (e)(2) of this AD thereafter at intervals not to exceed 
13,600 landings.
    (ii) If any crack is found, 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).
    (3) If any crack is found that is greater than or equal to 35 mm 
(1.38 in.), 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).
    (f) For Model A300-600 series airplanes equipped with General 
Electric CF6-80C2 engines, and having pylons that have been modified 
in accordance with Airbus Industrie Service Bulletin A300-54-6020, 
dated February 22, 1994: Prior to the accumulation of 26,400 
landings since installation of the modification, or within 500 
landings after June 28, 1996, whichever occurs later, perform an 
eddy current inspection to detect cracks in the lower spar axis of 
the pylons between ribs 6 and 7, in accordance with Airbus Industrie 
Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the eddy current inspection 
thereafter at intervals not to exceed 19,400 landings.
    (2) If any crack is found, 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).
    (g) For Model A300-600 series airplanes equipped with Pratt & 
Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have not 
been modified in accordance with Airbus Industrie Service Bulletin 
A300-54-6020, dated February 22, 1994: Prior to the accumulation of 
5,700 total landings, or within 500 landings after June 28, 1996, 
whichever occurs later, perform an internal eddy current inspection 
to detect cracks in the lower spar axis of the pylons between ribs 6 
and 7, in accordance with Airbus Industrie Service Bulletin A300-54-
6014, Revision 1, dated March 28, 1994.

[[Page 34058]]

    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 4,400 landings.
    (2) If any crack is found that is less than 35 mm (1.38 in.), 
prior to further flight, stop-drill the crack in accordance with the 
procedures specified in Section 51-41-10 of the SRM. Thereafter, 
prior to the accumulation of 250 landings after crack discovery, 
repair in accordance with the service bulletin. Prior to the 
accumulation of 10,100 landings after accomplishing the repair, 
perform an eddy current inspection to detect cracks at the stiffener 
ends, ribs 6 and 7, at the edge of the holes made during the repair 
and on the fasteners located at the edge of the doubler, in 
accordance with the service bulletin.
    (i) If no crack is found, repeat the inspection required by 
paragraph (g)(2) of this AD thereafter at intervals not to exceed 
10,000 landings.
    (ii) If any crack is found, 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).
    (3) If any crack is found that is greater than or equal to 35 mm 
(1.38 in.), 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).
    (h) For Model A300-600 series airplanes equipped with Pratt & 
Whitney JT9D-7R4 or PW 4000 engines, and having pylons that have 
been modified in accordance with Airbus Industrie Service Bulletin 
A300-54-6020, dated February 22, 1994: Prior to the accumulation of 
17,000 landings since installation of the modification, or within 
500 landings after June 28, 1996, whichever occurs later, perform an 
eddy current inspection to detect cracks in the lower spar axis of 
the pylons between ribs 6 and 7, in accordance with Airbus Industrie 
Service Bulletin A300-54-6014, Revision 1, dated March 28, 1994.
    (1) If no crack is found, repeat the eddy current inspection 
thereafter at intervals not to exceed 14,500 landings.
    (2) If any crack is found, 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).

New Requirements of This AD

New and Repetitive Inspections for Model A310 Series Airplanes

    (i) For Model A310 series airplanes on which the modification 
specified in Airbus Service Bulletin A310-54-2023, dated October 15, 
1993, has not been accomplished: Perform an eddy current inspection 
to detect cracks in the lower spar axis of the pylons between ribs 6 
and 7, in accordance with Airbus Industrie Service Bulletin A310-54-
2017, Revision 03, dated June 11, 1999, at the applicable time 
specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD.
    (1) For airplanes that have accumulated fewer than 10,000 total 
landings as of the effective date of this AD: Inspect prior to the 
accumulation of 7,000 total landings, or within 1,500 landings after 
the effective date of this AD, whichever occurs later.
    (2) For airplanes that have accumulated 10,000 total landings or 
more and fewer than 20,000 total landings as of the effective date 
of this AD: Inspect within 1,000 landings after the effective date 
of this AD.
    (3) For airplanes that have accumulated 20,000 total landings or 
more as of the effective date of this AD: Inspect within 500 
landings after the effective date of this AD.
    (j) If no crack is found during the inspection required by 
paragraph (i) of this AD, accomplish the actions specified by either 
paragraph (j)(1) or (j)(2) of this AD.
    (1) Repeat the inspection thereafter at intervals not to exceed 
6,400 landings. Or
    (2) Prior to further flight, modify the lower spar between ribs 
6 and 7 in accordance with Airbus Industrie Service Bulletin A310-
54-2023, dated October 15, 1993, and thereafter accomplish the 
actions required by paragraph (l) of this AD.
    (k) If any crack is found during any inspection required by 
paragraph (i) or (j) of this AD, accomplish the actions required by 
paragraph (k)(1) or (k)(2) of this AD, as applicable.
    (1) If the crack is less than 35 mm (1.38 in.), prior to further 
flight, repair in accordance with Airbus Industrie Service Bulletin 
A310-54-2017, Revision 03, dated June 11, 1999. Thereafter, within 
13,600 landings after accomplishing the repair, perform an eddy 
current inspection to detect cracks at the stiffener ends, ribs 6 
and 7, at the edge of the holes made during the repair, and on the 
fasteners located at the end of the doubler, in accordance with the 
service bulletin.
    (i) If no crack is found during the inspection required by 
paragraph (k)(1) of this AD, repeat the inspection required by 
paragraph (i) of this AD thereafter at intervals not to exceed 
11,600 landings.
    (ii) If any crack is found during the inspection required by 
paragraph (k)(1) of this AD, 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).
    (2) If the crack is equal to or greater than 35 mm (1.38 in.), 
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).
    (l) For Model A310 series airplanes on which the modification 
specified in Airbus Industrie Service Bulletin A310-54-2023, dated 
October 15, 1993, has been accomplished: Within 23,000 landings 
after accomplishment of the modification, or within 90 days after 
the effective date of this AD, whichever occurs later, perform an 
eddy current inspection to detect cracks in the lower spar axis of 
the pylons between ribs 6 and 7, in accordance with Airbus Industrie 
Service Bulletin A310-54-2017, Revision 03, dated June 11, 1999.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 15,500 landings.
    (2) If any crack is found during any inspection required by 
paragraph (l) or (l)(1) of this AD, 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).

Alternative Methods of Compliance

    (m)(1) 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.
    (2) Alternate methods of compliance approved previously in 
accordance with AD 96-11-05, Amendment 39-9630, for paragraphs (a) 
through (h) of that AD, are approved as alternative methods of 
compliance with paragraphs (a) through (h) of this AD.

    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

    (n) 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.

[[Page 34059]]

Incorporation by Reference

    (o) Except as required by paragraphs (a)(2), (a)(2)(ii), (a)(3), 
(b)(2), (c)(2), (c)(2)(ii), (c)(3), (d)(2), (e)(2), (e)(2)(ii), 
(e)(3), (f)(2), (g)(2), (g)(2)(ii), (g)(3), (h)(2), (k)(1)(ii), 
(k)(2), and (l)(2), the actions shall be done in accordance with the 
following Airbus service bulletins:

----------------------------------------------------------------------------------------------------------------
      Airbus service bulletin No.                   Revision level                   Service bulletin date
----------------------------------------------------------------------------------------------------------------
A300-54-0073,..........................  1..................................  March 28, 1994.
A300-54-6014,..........................  1..................................  March 28, 1994.
A310-54-2017,..........................  03.................................  June 11, 1999.
A310-54-2023,..........................  Original...........................  October 15, 1993.
----------------------------------------------------------------------------------------------------------------

    (1) The incorporation by reference of Airbus Service Bulletin 
A310-54-2017,
    Revision 03, dated June 11, 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 service 
bulletins was approved previously by the Director of the Federal 
Register as of June 28, 1996 (61 FR 26091, May 24, 1996).
    (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 directives 1999-239-287(B) and 1993-228-154(B)R3, both 
dated June 2, 1999.

    (p) This amendment becomes effective on June 30, 2000.

    Issued in Renton, Washington, on May 16, 2000.
Donald L. Riggin,
Acting Manager,Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-12814 Filed 5-25-00; 8:45 am]
BILLING CODE 4910-13-U