AD 2000-04-13

[Federal Register Volume 65, Number 39 (Monday, February 28, 2000)]
[Rules and Regulations]
[Pages 10381-10385]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-4338]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-240-AD; Amendment 39-11596; AD 2000-04-13]
RIN 2120-AA64


Airworthiness Directives; Aerospatiale Model ATR72 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 Aerospatiale Model ATR72 series airplanes, that 
requires initial and repetitive inspections to detect fatigue cracking 
in certain areas of the fuselage, and corrective actions, 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 prevent fatigue 
cracking of the fuselage and the passenger and service doors, which 
could result in reduced structural integrity of the airplane.

DATES: Effective April 3, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 3, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 
03, 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 Aerospatiale Model ATR72 
series airplanes was published as a supplemental notice of proposed 
rulemaking (NPRM) in the Federal Register on October 26, 1999 (64 FR 
57602). That action proposed to require initial and repetitive 
inspections to detect fatigue cracking in certain areas of the 
fuselage, and corrective actions, if necessary.

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.

Approved Repairs

    One commenter, an operator, expresses concern that paragraphs (c) 
and (d)(2)(ii) of the proposed AD mandate that any repairs, previously 
conducted through Aerospatiale, now must be approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; or 
the Direction Generale de l'Aviation Civile (DGAC) (or its delegated 
agent). The commenter is concerned that, if the only resources for 
repair approvals are those mentioned here, any repair approval process 
will not be responsive on a timely basis. The commenter states that 
notification to the Manager, ANM-116, of damage found and the repair

[[Page 10382]]

method used, following embodiment, would be more appropriate.
    The FAA infers that the commenter is requesting that the AD be 
revised to allow repair approvals through Aerospatiale, with subsequent 
notification to the Manager, ANM-116. The FAA does not concur. To 
specify within an AD that repairs are to be accomplished in accordance 
with the manufacturer would be delegating the FAA's rulemaking 
authority to the manufacturer. Since the referenced service information 
does not provide appropriate repair procedures, the FAA must require 
that operators accomplish necessary repairs in accordance with a method 
approved by the FAA or the DGAC (or its delegated agent). The FAA notes 
that, if Aerospatiale has been designated by the DGAC as a delegated 
agent for repair approvals, such approvals by Aerospatiale would be 
acceptable for compliance with this AD. No change to the AD is 
necessary.

Prior Repairs

    The same commenter notes that there should be some consideration 
for airplanes on which the modification has already been accomplished 
with some form of repair (prior to the effective date of the AD). As 
written, the AD would require that any such repair be ``reapproved'' by 
the FAA or DGAC.
    The FAA does not concur. As noted in the FAA's response to the 
previous comment, repairs approved by Aerospatiale may be acceptable 
for compliance with this AD, if Aerospatiale is a delegated agent of 
the DGAC for such repairs. If this is the case, no ``reapproval'' is 
necessary, since such approved repairs would be acceptable for 
compliance with the requirements of this AD. Further, sufficient time 
is provided prior to the compliance thresholds of this AD to allow 
operators to determine if approvals must be obtained for previously 
accomplished repairs, and to obtain such approvals, if necessary. No 
change to the AD is necessary.

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 39 airplanes of U.S. registry will be 
affected by this AD.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-53-1018 (14 U.S.-registered airplanes), it will take 
approximately 250 work hours per airplane to accomplish the required 
actions, at an average labor rate of $60 per work hour. Required parts 
will cost approximately $9,880 per airplane. Based on these figures, 
the cost impact of these actions required by this AD on U.S. operators 
is estimated to be $348,320, or $24,880 per airplane.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-52-1013, Revision 2 (2 U.S.-registered airplanes), it 
will take approximately 3 work hours per airplane to accomplish the 
required actions, at an average labor rate of $60 per work hour. Based 
on these figures, the cost impact of these actions required by this AD 
on U.S. operators is estimated to be $360, or $180 per airplane.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-52-1019, Revision 2 (2 U.S.-registered airplanes), it 
will take approximately 100 work hours per airplane to accomplish the 
required actions, at an average labor rate of $60 per work hour. Based 
on these figures, the cost impact of these actions required by this AD 
on U.S. operators is estimated to be $12,000, or $6,000 per airplane.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-52-1028 (2 U.S.-registered airplanes), it will take 
approximately 5 work hours per airplane to accomplish the required 
actions, at an average labor rate of $60 per work hour. Based on these 
figures, the cost impact of these actions required by this AD on U.S. 
operators is estimated to be $600, or $300 per airplane, per inspection 
cycle.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-52-1033, and ATR72-52-1029, Revision 1 (2 U.S.-
registered airplanes), it will take approximately 145 work hours per 
airplane to accomplish the required door stop fitting replacement, at 
an average labor rate of $60 per work hour. Required parts will be 
provided by the manufacturer at no cost to the operators. Based on 
these figures, the cost impact of the stop fittings replacement 
required by this AD on U.S. operators is estimated to be $17,400 or 
$8,700 per airplane.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-53-1021, Revision 1 (2 U.S.-registered airplanes), it 
will take approximately 30 work hours per airplane to accomplish the 
required actions, at an average labor rate of $60 per work hour. Based 
on these figures, the cost impact of these actions required by this AD 
on U.S. operators is estimated to be $3,600, or $1,800 per airplane.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-53-1014, Revision 2 (2 U.S.-registered airplanes), it 
will take approximately 8 work hours per airplane to accomplish the 
required actions, at an average labor rate of $60 per work hour. Based 
on these figures, the cost impact of these actions required by this AD 
on U.S. operators is estimated to be $960, or $480 per airplane.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-53-1020 (14 U.S.-registered airplanes), it will take 
approximately 6 work hours per airplane to accomplish the required 
actions, at an average labor rate of $60 per work hour. Based on these 
figures, the cost impact of these actions required by this AD on U.S. 
operators is estimated to be $5,040, or $360 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 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.

[[Page 10383]]

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:

2000-04-13 Aerospatiale: Amendment 39-11596. Docket 98-NM-240-AD.

    Applicability: Model ATR72 series airplanes, certificated in any 
category; listed in the following Avions de Transport Regional (ATR) 
Service Bulletins:
    <bullet> ATR72-52-1018, dated May 18, 1995;
    <bullet> ATR72-53-1013, Revision 2, dated March 22, 1993;
    <bullet> ATR72-53-1019, Revision 2, dated October 15, 1996;
    <bullet> ATR72-52-1028, dated July 5, 1993;
    <bullet> ATR72-52-1033, dated April 28, 1995;
    <bullet> ATR72-52-1029, Revision 1, dated November 16, 1994;
    <bullet> ATR72-53-1021, Revision 1, dated February 20, 1995;
    <bullet> ATR72-53-1014, Revision 2, dated October 15, 1992; and
    <bullet> ATR72-53-1020, dated October 6, 1992.

    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 (i) 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 of the fuselage and the passenger 
and service doors, which could result in reduced structural 
integrity of the airplane, accomplish the following:

Inspections and Corrective Actions

    (a) For airplanes on which Aerospatiale Modification 03191 
(reference Avions de Transport Regional Service Bulletin ATR72-52-
1018, dated May 18, 1995) has not been accomplished: Prior to the 
accumulation of 27,000 total flight cycles, or within 30 days after 
the effective date of this AD, whichever occurs later, perform a 
preliminary inspection of the existing fasteners to determine if the 
fasteners are out of tolerance in accordance with paragraph 2.C.(1) 
of the Accomplishment Instructions of Avions de Transport Regional 
Service Bulletin ATR72-52-1018, dated May 18, 1995. Depending on the 
results of the inspection, prior to further flight, accomplish the 
requirements in paragraphs (a)(1) and (a)(2), or (a)(2) and (a)(3), 
of this AD, as applicable, as specified by paragraph 2.C.(1) of the 
service bulletin.
    (1) Remove the fasteners and inspect the fastener holes to 
determine if they are out of tolerance or cracking, in accordance 
with Part A of the Accomplishment Instructions of the service 
bulletin. Perform a visual inspection of the holes for correct 
tolerance, and a high frequency eddy current (HFEC) inspection for 
cracking.
    (i) If any discrepancy is detected, prior to further flight, 
repair in accordance with Part C of the Accomplishment Instructions 
of the service bulletin.
    (ii) If no discrepancy is detected, prior to further flight, 
replace the cargo compartment door hinges with new hinges in 
accordance with Part A of the Accomplishment Instructions of the 
service bulletin.
    (2) Remove the existing fasteners and inspect the fastener holes 
for correct tolerance in accordance with Part B of the 
Accomplishment Instructions of the service bulletin.
    (i) If any discrepancy is detected, prior to further flight, 
repair in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate; or 
the Direction Generale de l'Aviation Civile (DGAC) (or its delegated 
agent).
    (ii) If no discrepancy is detected, prior to further flight, 
replace the cargo compartment door hinges with new hinges in 
accordance with Part B of the Accomplishment Instructions of the 
service bulletin.
    (3) Remove the existing fasteners, repair, and replace the cargo 
compartment door hinges with new hinges in accordance with Part C of 
the Accomplishment Instructions of the service bulletin.
    (b) For airplanes having serial numbers 108 through 210 
inclusive: Prior to the accumulation of 36,000 total flight cycles, 
or within 30 days after the effective date of this AD, whichever 
occurs later, perform a one-time visual inspection to determine if 
rivets are installed in the key holes located on main frames 25 and 
27 of the fuselage, between stringers 14 and 15, in accordance with 
Avions de Transport Regional Service Bulletin ATR72-53-1013, 
Revision 3, dated January 22, 1999.
    (1) If all rivets are installed, no further action is required 
by paragraph (b) of this AD.
    (2) If any rivet is missing, prior to further flight, perform an 
eddy current inspection of the affected key holes to detect cracks, 
in accordance with the service bulletin.
    (i) If no crack is detected during the inspection required by 
paragraph (b)(2) of this AD, prior to further flight, install rivets 
in all affected key holes, in accordance with the service bulletin. 
If installation of rivets is not possible, 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).
    (ii) If any crack is detected during the inspection required by 
paragraph (b)(2) 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).
    (c) For airplanes having serial numbers 108 through 207 
inclusive: Prior to the accumulation of 36,000 total flight cycles, 
or within 30 days after the effective date of this AD, whichever 
occurs later, perform a one-time visual inspection to determine if 
rivets are installed in the tooling and key holes located on the 
standard frames of the fuselage, in accordance with Avions de 
Transport Regional Service Bulletin ATR72-53-1019, Revision 3, dated 
January 22, 1999.
    (1) If all rivets are installed, no further action is required 
by paragraph (c) of this AD.
    (2) If any rivet is missing, prior to further flight, perform a 
visual inspection of the affected tooling and key holes to detect 
cracks, in accordance with the service bulletin.
    (i) If no crack is detected during the inspection required by 
paragraph (c)(2) of this AD, prior to further flight, install new 
rivets in all affected tooling and key holes, in accordance with the 
service bulletin.
    (ii) If any crack is detected during the inspection required by 
paragraph (c)(2) 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).
    (d) For airplanes on which Aerospatiale Modification 03775 
(reference Avions de Transport Regional Service Bulletin ATR72-52-
1029, Revision 1, dated November 16, 1994) or Aerospatiale 
Modification 03776 (reference Avions de Transport Regional Service 
Bulletin ATR72-52-1033, dated April 28, 1995) has not been 
accomplished: Prior to the accumulation of 12,000 total flight 
cycles, or within 30 days after the effective date of this AD, 
whichever occurs later, perform an eddy current inspection to detect 
cracks in the plug door stop fittings of the forward and aft 
passenger and service doors, in accordance with Avions de Transport 
Regional Service Bulletin ATR72-52-1028, dated July 5, 1993.
    (1) If no crack is detected, repeat the eddy current inspection 
required by paragraph (d) of this AD thereafter at intervals not to 
exceed 6,000 flight cycles.
    (2) If any crack is detected, prior to further flight, replace 
the cracked stop fittings with new, improved fittings, in accordance 
with Avions de Transport Regional Service Bulletin ATR72-52-1033, 
dated April 28, 1995, or ATR72-52-1029, Revision 1, dated November 
16, 1994; as applicable. Accomplishment of the replacement 
constitutes terminating action for the repetitive inspection 
requirements of paragraph (d)(1) of this AD for that fitting.
    (e) For airplanes on which Aerospatiale Modification 03775 or 
Aerospatiale Modification 03776 has not been accomplished: Prior to 
the accumulation of 18,000 total flight cycles, or within 30 days 
after the effective date of this AD, whichever occurs later, replace 
the plug door stop fittings of the forward and aft passenger and 
service doors with new, improved fittings, in

[[Page 10384]]

accordance with Avions de Transport Regional Service Bulletin ATR72-
52-1033, dated April 28, 1995; or ATR72-52-1029, Revision 1, dated 
November 16, 1994; as applicable. Accomplishment of the replacement 
constitutes terminating action for the repetitive inspection 
requirements of paragraph (d)(1) of this AD.
    (f) For airplanes on which Aerospatiale Modification 02986 
(reference Avions de Transport Regional Service Bulletin ATR72-53-
1021, Revision 1, dated February 20, 1995) has not been 
accomplished: Prior to the accumulation of 18,000 total flight 
cycles, or within 30 days after the effective date of this AD, 
whichever occurs later, perform a one-time eddy current inspection 
to detect cracks in the rivet holes of the door surround corners of 
the forward and aft passenger and service doors, in accordance with 
Avions de Transport Regional Service Bulletin ATR72-53-1021, 
Revision 1, dated February 20, 1995.
    (1) If no crack is detected during the inspection required by 
paragraph (f) of this AD, prior to further flight, modify the rivet 
holes, and replace the door surround corners with modified corners, 
in accordance with the service bulletin.
    (2) If any crack is detected during the inspection required by 
paragraph (f) of this AD, prior to further flight, repair and modify 
in accordance with a method approved by the Manager, International 
Branch, ANM-116; or the DGAC (or its delegated agent).
    (g) For airplanes on which Aerospatiale Modification 02397 
(reference Avions de Transport Regional Service Bulletin ATR72-53-
1014, Revision 2, dated October 15, 1992) has not been accomplished: 
Prior to the accumulation of 12,000 total flight cycles, or within 
30 days after the effective date of this AD, whichever occurs later, 
perform a one-time eddy current inspection to detect cracks of the 
rivet holes located on the left and right sides of external stringer 
4 at frames 24 and 28 of the fuselage, in accordance with Avions de 
Transport Regional Service Bulletin ATR72-53-1014, Revision 2, dated 
October 15, 1992.
    (1) If no crack is detected during the inspection required by 
paragraph (g) of this AD, prior to further flight, install 
reinforcement angles on the left and right sides of external 
stringer 4 at frames 24 and 28 of the fuselage, in accordance with 
the service bulletin.
    (2) If any crack is detected during the inspection required by 
paragraph (g) 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).
    (h) For airplanes on which Aerospatiale Modification 03185 
(reference Avions de Transport Regional Service Bulletin ATR72-53-
1020, dated October 6, 1992) has not been accomplished: Prior to the 
accumulation of 12,000 total flight cycles, or within 30 days after 
the effective date of this AD, whichever occurs later, perform a 
one-time eddy current inspection to detect cracks of the rivet holes 
located on stringer 11 of frame 26 of the fuselage, in accordance 
with Avions de Transport Regional Service Bulletin ATR72-53-1020, 
dated October 6, 1992.
    (1) If no crack is detected during the inspection required by 
paragraph (h) of this AD, prior to further flight, install doublers 
and stringer clips on the left and right sides on stringer 11 of 
frame 26 of the fuselage, in accordance with the service bulletin.
    (2) If any crack is detected during the inspection required by 
paragraph (h) 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).

    Note 2: Inspections and repairs accomplished prior to the 
effective date of this AD in accordance with Avions de Transport 
Regional Service Bulletins ATR72-53-1013, dated June 10, 1991, or 
Revision 1, dated June 12, 1992, or Revision 2, dated March 22, 
1993; ATR72-53-1019, dated May 13, 1993, or Revision 1, dated 
November 11, 1994, or Revision 2, dated October 15, 1996; ATR72-52-
1029, dated July 20, 1994; or ATR72-53-1014, Revision 1, dated June 
30, 1992; are considered acceptable for compliance with the 
applicable actions specified in this amendment.

Alternative Methods of Compliance

    (i) 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 3: 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

    (j) 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

    (k) Except as required by paragraphs (a)(2)(i), (b)(2)(i), 
(b)(2)(ii), (c)(2)(ii), (f)(2), (g)(2), and (h)(2) of this AD, the 
actions shall be done in accordance with the following Avions de 
Transport Regional service bulletins, as applicable:

----------------------------------------------------------------------------------------------------------------
 Service bulletin referenced and                      Revision level shown on
              date                     Page No.                 page                   Date shown on page
----------------------------------------------------------------------------------------------------------------
ATR72-52-1018, May 18, 1995.....  1-116.............  Original...............  May 18, 1995.
ATR72-53-1013, Revision 3,        1-4, 7............  3......................  January 22, 1999.
 January 22, 1999.                5, 8-10...........  1......................  June 12, 1992.
                                  6, 11.............  Original...............  June 10, 1991.
ATR72-53-1019, Revision 3,        1-4...............  3......................  January 22, 1999.
 January 22, 1999.                5, 6, 9-14, 16, 17  1......................  November 11, 1994.
                                  7, 8, 15..........  Original...............  May 13, 1993.
ATR72-52-1028, July 5, 1993.....  1-21..............  Original...............  July 5, 1993.
ATR72-52-1033, April 28, 1995...  1-41..............  Original...............  April 28, 1995.
ATR72-52-1029, Revision 1,        1, 8-14, 33, 34...  1......................  November 16, 1994.
 November 16, 1994.               2-7, 15-32, 35-50.  Original...............  July 20, 1994.
ATR72-53-1021, Revision 1,        1, 3, 5, 8, 11,     1......................  February 20, 1995.
 February 20, 1995.                35, 36.            Original...............  July 8, 1993.
                                  2, 4, 6, 7, 9, 10,
                                   12-34.
ATR72-53-1014, Revision 2,        1, 9-11, 15.......  2......................  October 15, 1992.
 October 15, 1992.                2-8, 12-14........  1......................  June 30, 1992.
ATR72-53-1020, October 6, 1992..  1-15..............  Original...............  October 6, 1992.
----------------------------------------------------------------------------------------------------------------

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 Aerospatiale, 316 Route de Bayonne, 
31060 Toulouse, Cedex 03, 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 4: The subject of this AD is addressed in French 
airworthiness directive 92-046-012(B)R4, dated November 5, 1997.

    (l) This amendment becomes effective on April 3, 2000.


[[Page 10385]]


    Issued in Renton, Washington, on February 17, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-4338 Filed 2-25-00; 8:45 am]
BILLING CODE 4910-13-U