[Federal Register Volume 69, Number 26 (Monday, February 9, 2004)]
[Rules and Regulations]
[Pages 5914-5918]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2586]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-376-AD; Amendment 39-13456; AD 2004-03-12]
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 supersedes an existing airworthiness directive 
(AD), applicable to certain Aerospatiale Model ATR72 series airplanes, 
that currently requires initial and repetitive inspections to detect 
fatigue cracking in certain areas of the fuselage, and corrective 
actions if necessary. For certain airplanes, this amendment requires a 
new inspection for oversized fastener holes and cracking, and repair if 
necessary. 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. 
This action is intended to address the identified unsafe condition.

DATES: Effective March 15, 2004.
    The incorporation by reference of a certain publication, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of March 15, 2004.
    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 April 3, 2000 (65 FR 10381, February 28, 
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: Tony Jopling, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2190; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-04-13, 
amendment 39-11596 (65 FR 10381, February 28, 2000), which is 
applicable to certain Aerospatiale Model ATR72 series airplanes, was 
published in the Federal Register on November 28, 2003 (68 FR 66772). 
The action proposed to continue to require initial and repetitive 
inspections to detect fatigue cracking in certain areas of the 
fuselage, and corrective actions if necessary. For certain airplanes, 
that action also proposed to require repair of oversized fastener 
holes.

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.

[[Page 5915]]

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 39 airplanes of U.S. registry that will be 
affected by this AD.
    The actions that are currently required by AD 2000-04-13 are as 
follows:
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-52-1018 (14 U.S.-registered airplanes), it takes 
approximately 250 work hours per airplane to accomplish the required 
actions, at an average labor rate of $65 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 $365,820, or $26,130 per airplane.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-53-1013, 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 $65 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 $390, or $195 per airplane.
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-53-1019, 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 $65 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 $13,000, or $6,500 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 $65 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 $650 or $325 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 $65 per work hour. Required parts are 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 $18,850 or $9,425 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 
proposed actions, at an average labor rate of $65 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 $3,900, or $1,950 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 $65 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 $1,040, or $520 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 $65 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 $5,460, or $390 per airplane.
    The new actions required by this AD are as follows:
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-52-1018, Revision 1, accomplishment of the new actions, 
if required, will take approximately 250 work hours per airplane to 
accomplish, at an average labor rate of $65 per work hour. Required 
parts will cost approximately $9,880 per airplane. Based on these 
figures, the cost impact of the new actions required by this AD on U.S. 
operators is estimated to be $26,130 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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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

0
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

0
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]

0
2. Section 39.13 is amended by removing amendment 39-11596 (65 FR 
10381, February 28, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-13456, to read as follows:

2004-03-12 Aerospatiale: Amendment 39-13456. Docket 2001-NM-376-AD. 
Supersedes AD 2000-04-13, Amendment 39-11596.

    Applicability: Model ATR72 series airplanes; certificated in any 
category; listed in the following Avions de Transport Regional 
Service Bulletins:
    <bullet<ls-thn-eq> ATR72-52-1018, dated May 18, 1995;
    <bullet<ls-thn-eq> ATR72-52-1018, Revision 1, dated March 13, 
2001;

[[Page 5916]]

    <bullet<ls-thn-eq> ATR72-52-1028, dated July 5, 1993;
    <bullet<ls-thn-eq> ATR72-52-1029, Revision 1, dated November 16, 
1994;
    <bullet<ls-thn-eq> ATR72-52-1033, dated April 28, 1995;
    <bullet<ls-thn-eq> ATR72-53-1013, Revision 2, dated March 22, 
1993;
    <bullet<ls-thn-eq> ATR72-53-1014, Revision 2, dated October 15, 
1992;
    <bullet<ls-thn-eq> ATR72-53-1019, Revision 2, dated October 15, 
1996;
    <bullet<ls-thn-eq> ATR72-53-1020, dated October 6, 1992; and
    <bullet<ls-thn-eq> ATR72-53-1021, Revision 1, dated February 20, 
1995.
    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:

Restatement of Requirements of AD 2000-04-13

Inspections/Corrective Actions

    (a) For airplanes on which Aerospatiale Modification 03191 
(reference Avions de Transport Regional Service Bulletin ATR72-52-
1018) has not been accomplished as of April 3, 2000 (the effective 
date of AD 2000-04-13, amendment 39-11596); prior to the 
accumulation of 27,000 total flight cycles, or within 30 days after 
April 3, 2000: 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.
    (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, in accordance with the service bulletin.
    (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 G[eacute]n[eacute]rale 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 1 month after April 3, 2000, 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 1 month after April 3, 2000, 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 as of April 3, 2000: Prior to the accumulation of 
12,000 total flight cycles, or within 1 month after April 3, 2000, 
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 as of 
April 3, 2000: Prior to the accumulation of 18,000 total flight 
cycles, or within 1 month after April 3, 2000, whichever occurs 
later, replace the plug door stop fittings of the forward and aft 
passenger and service doors 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.
    (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 
as of April 3, 2000: Prior to the accumulation of 18,000 total 
flight cycles, or within 1 month after April 3, 2000, 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 
as of April 3, 2000: Prior to the accumulation of 12,000

[[Page 5917]]

total flight cycles, or within 1 month after April 3, 2000, 
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 as of April 
3, 2000: Prior to the accumulation of 12,000 total flight cycles, or 
within 1 month after April 3, 2000, 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 1: 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; ATR72-53-1019, dated May 13, 1993, 
or Revision 1, dated November 11, 1994; 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 AD.

New Requirements of this AD

Inspection/Repair

    (i) Prior to the accumulation of 27,000 total flight cycles, or 
within 30 days after the effective date of this AD, whichever is 
later; do the actions specified in paragraph (i)(1) or (i)(2) of 
this AD, as applicable.
    (1) For airplanes on which Aerospatiale Modification 3191 and 
Aerospatiale Modification 3184 have not been accomplished as of the 
effective date of this AD: No further action is required by 
paragraph (i) of this AD.
    (2) For airplanes on which Aerospatiale Modification 3191 has 
not been accomplished as of the effective date of this AD, and 
Aerospatiale Modification 3184 has been accomplished as of the 
effective date of this AD: Do a detailed inspection of the fastener 
holes at the hinge fitting of the cargo compartment doors to 
determine if the holes are oversized, and inspect the outer skin 
around the fastener holes for cracking, in accordance with the 
Accomplishment Instructions of Avions de Transport Regional Service 
Bulletin ATR72-52-1018, Revision 1, dated March 13, 2001.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

    (j) Prior to further flight, repair any discrepancies detected 
during any inspection required by paragraph (i) of this AD in 
accordance with the Accomplishment Instructions of Avions de 
Transport Regional Service Bulletin ATR72-52-1018, Revision 1, dated 
March 13, 2001. Where the service bulletin specifies contacting the 
manufacturer for repair disposition, 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

    (k) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, is authorized to approve alternative methods of 
compliance for this AD.

Incorporation by Reference

    (l) Unless otherwise specified in this AD, the actions shall be 
done in accordance with the applicable Avions de Transport Regional 
Service Bulletins, as listed in Table 1 of this AD:

                       Table 1.--Service Bulletins
------------------------------------------------------------------------
      Service bulletin         Revision level             Date
------------------------------------------------------------------------
ATR72-52-1018...............  Original.......  May 18, 1995.
ATR72-52-1018...............  Revision 1.....  March 13, 2001.
ATR72-52-1028...............  Original.......  July 5, 1993.
ATR72-52-1029...............  Revision 1.....  November 16, 1994.
ATR72-52-1033...............  Original.......  April 28, 1995.
ATR72-53-1013...............  Revision 3.....  January 22, 1999.
ATR72-53-1014...............  Revision 2.....  October 15, 1992.
ATR72-53-1019...............  Revision 3.....  January 22, 1999.
ATR72-53-1020...............  Original.......  October 6, 1992.
ATR72-53-1021...............  Revision 1.....  February 20, 1995.
------------------------------------------------------------------------

    (1) The incorporation by reference of Avions de Transport 
Regional Service Bulletin ATR72-52-1018, Revision 1, dated March 13, 
2001; 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 Avions de Transport 
Regional Service Bulletins listed in Table 2 of this AD was approved 
previously by the Director of the Federal Register as of April 3, 
2000 (65 FR 10381, February 28, 2000):

             Table 2.--Previously Approved Service Bulletins
------------------------------------------------------------------------
      Service bulletin         Revision level             Date
------------------------------------------------------------------------
ATR72-52-1018...............  Original.......  May 18, 1995.
ATR72-52-1028...............  Original.......  July 5, 1993.
ATR72-52-1029...............  Revision 1.....  November 16, 1994.
ATR72-52-1033...............  Original.......  April 28, 1995.
ATR72-53-1013...............  Revision 3.....  January 22, 1999.
ATR72-53-1014...............  Revision 2.....  October 15, 1992.
ATR72-53-1019...............  Revision 3.....  January 22, 1999.

[[Page 5918]]

 
ATR72-53-1020...............  Original.......  October 6, 1992.
ATR72-53-1021...............  Revision 1.....  February 20, 1995.
------------------------------------------------------------------------

    (3) 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 3: The subject of this AD is addressed in French 
airworthiness directive 2001-142-056(B), dated April 18, 2001.

Effective Date

    (m) This amendment becomes effective on March 15, 2004.

    Issued in Renton, Washington, on January 29, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-2586 Filed 2-6-04; 8:45 am]
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