[Federal Register Volume 65, Number 30 (Monday, February 14, 2000)]
[Proposed Rules]
[Pages 7316-7320]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-3397]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-251-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of 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 action would reduce the currently 
required inspection thresholds and intervals, and would remove an 
option for a terminating modification. This proposal is prompted by 
issuance of mandatory continuing airworthiness information by a foreign 
civil airworthiness authority. The actions specified by the proposed 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: Comments must be received by March 15, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-251-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

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.

[[Page 7317]]


SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-251-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 99-NM-251-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On May 15, 1996, the FAA issued AD 96-11-05, amendment 39-9630 (61 
FR 26091, May 24, 1996), applicable to certain Airbus Industrie Model 
A300, A300-600, and A310 series airplanes, to require inspections to 
detect cracks in the lower spar axis of the pylons between ribs 6 and 
7, and repair, if necessary. That action was prompted by a report that 
fatigue cracks were found in the lower spar of the pylon between ribs 6 
and 7 on airplanes equipped with General Electric and Pratt and Whitney 
engines. These cracks initiated at the pylon center stiffener beyond 
the flat area. The requirements of that AD are intended to prevent such 
fatigue cracking, which could result in reduced structural integrity of 
the lower spar of the pylon.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 96-11-05, the Direction Generale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, has advised the FAA that certain in-service events have 
necessitated a revised inspection program for Airbus Model A310 series 
airplanes. The DGAC informed the FAA that, as a result of these in-
service events, accomplishment of Airbus Service Bulletin A310-54-2023, 
dated October 15, 1993, is no longer appropriate terminating action for 
the inspection requirements of AD 96-11-05 for affected Model A310 
series airplanes. (That service bulletin is cited in AD 96-11-05 as the 
appropriate source of service information for accomplishment of the 
modification that terminates the requirement for the internal eddy 
current inspections for those Model A310 series airplanes.) However, 
compliance with that service bulletin would extend the inspection 
thresholds and repetitive intervals for Model A310 series airplanes.

Explanation of Relevant Service Information

    Airbus Industrie has issued Service Bulletin A310-54-2017, Revision 
03, dated June 11, 1999, which describes procedures for repetitive eddy 
current inspections of the engine pylon lower spar for cracks, and 
repair of any crack. For Model A310 series airplanes, Revision 03 
reduces the recommended compliance times and repetitive inspection 
intervals. Revision 03 also specifies additional inspection thresholds 
and intervals for Model A310 series airplanes on which modification of 
the lower ribs and spar between ribs 6 and 7 has been accomplished as 
specified in Airbus Service Bulletin A310-54-2023, dated October 15, 
1993. The DGAC classified Service Bulletin A310-54-2017, Revision 03, 
as mandatory and issued French airworthiness directive 1999-239-287(B), 
dated June 2, 1999, in order to assure the continued airworthiness of 
these airplanes in France.

FAA's Conclusions

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would supersede AD 96-11-05 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.

Cost Impact

    There are approximately 146 airplanes of U.S. registry that would 
be affected by this proposed AD.
    The requirements of this proposed AD would 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 proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative,

[[Page 7318]]

on a substantial number of small entities under the criteria of the 
Regulatory Flexibility Act. A copy of the draft regulatory evaluation 
prepared for this action is contained in the Rules Docket. A copy of it 
may be obtained by contacting the Rules Docket at the location provided 
under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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), 
to read as follows:

Airbus Industrie: 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.
    (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

[[Page 7319]]

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.
    (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 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 the 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 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 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 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 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

[[Page 7320]]

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 
Secs. 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 1999-239-287(B), dated June 2, 1999.


    Issued in Renton, Washington, on February 8, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-3397 Filed 2-11-00; 8:45 am]
BILLING CODE 4910-13-P