[Federal Register Volume 68, Number 229 (Friday, November 28, 2003)]
[Proposed Rules]
[Pages 66772-66775]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-29701]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-376-AD]
RIN 2120-AA64


Airworthiness Directives; Aerospatiale Model ATR72 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 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 action would require a new inspection for oversized fastener holes 
and cracking, and repair if necessary. The actions specified by the 
proposed 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: Comments must be received by December 29, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-376-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-376-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 
03, France. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

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:

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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-376-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. 2001-NM-376-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On February 17, 2000, the FAA issued AD 2000-04-13, amendment 39-
11596 (65 FR 10381, February 28, 2000), applicable to certain 
Aerospatiale Model ATR72 series airplanes, to require initial and 
repetitive inspections to detect fatigue cracking in certain areas of 
the fuselage, and corrective actions if necessary. That action was 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The requirements of that 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.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 2000-04-13, the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may continue to exist on certain ATR72 series airplanes on 
which Aerospatiale Modification 3191 (specified in Service Bulletin 
ATR72-52-1018, dated May 18, 1995, which is required by the existing 
AD) has not been done, but Aerospatiale Modification 3184 (accomplished 
during production and unrelated to the actions of the existing AD) has 
been done. Investigation revealed that during fatigue testing of these 
airplanes, damage was found at the attachment holes at the hinge 
fitting of the cargo compartment door outer skin due to oversized 
fastener holes drilled during incorporation of Modification 3184.

Explanation of Relevant Service Information

    The manufacturer has issued Avions de Transport Regional Service 
Bulletin ATR72-52-1018, Revision 1, dated March 13, 2001. The original 
issue of the service bulletin was referenced as the appropriate source 
of service information for the accomplishment of certain inspections 
and corrective actions specified in the existing AD. For

[[Page 66773]]

airplanes on which Aerospatiale Modification 3191 has not been done, 
but Aerospatiale Modification 3184 has been done, Revision 1 adds 
procedures for a detailed visual inspection of the fastener holes at 
the hinge fitting of the cargo compartment doors to determine if the 
holes are oversized, and the outer skin around the fastener holes for 
cracking, and repair of any discrepancies found. For airplanes on which 
neither modification 3191 nor 3184 has been done, the new actions 
specified in Revision 1 of the service bulletin need not be done. The 
DGAC classified this service bulletin as mandatory and issued French 
airworthiness directive 2001-142-056(B), dated April 18, 2001, to 
ensure the continued airworthiness of these airplanes in France. The 
new French airworthiness directive covers all the service bulletins 
specified in the existing AD, and replaces French airworthiness 
directive 92-046-012(B)R4, dated November 5, 1997; which was referenced 
in the existing AD.

FAA's Conclusions

    This airplane model is manufactured in France and is 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 us informed of the 
situation described above. We have 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 AD

    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 2000-04-13 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, the proposed AD also would 
require repair of oversized fastener holes. The actions would be 
required to be accomplished in accordance with the service bulletin 
described previously, except as discussed below.

Differences Between Proposed AD and Service Bulletin

    The service bulletin specifies that the manufacturer should be 
notified if the measured diameter of the fastener holes is out of 
tolerance, but this proposed AD does not include such a requirement.
    The service bulletin also describes procedures for completing an 
inspection report and submitting it to the manufacturer, but this 
proposed AD would not require those actions. We do not need this 
information from operators.

Cost Impact

    There are approximately 39 airplanes of U.S. registry that would be 
affected by this proposed 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 ATR72-53-1018 (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 ATR72-52-1013, 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 $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 ATR72-52-1019, 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 $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 proposed in this AD are as follows:
    For airplanes identified in Avions de Transport Regional Service 
Bulletin ATR72-53-1018, Revision 1, accomplishment of the new proposed 
actions, if required, would take approximately 250 work hours per 
airplane to accomplish, at an average labor rate of $65 per work hour. 
Required parts would cost approximately $9,880 per airplane. Based on 
these figures, the cost impact of the new actions proposed 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

[[Page 66774]]

the current or proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    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, 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 39-11596 (65 FR 
10381, February 28, 2000), and by adding a new airworthiness directive 
(AD), to read as follows:

Aerospatiale: 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:
    [sbull] ATR72-52-1018, dated May 18, 1995;
    [sbull] ATR72-52-1018, Revision 1, dated March 13, 2001;
    [sbull] ATR72-53-1013, Revision 2, dated March 22, 1993;
    [sbull] ATR72-53-1019, Revision 2, dated October 15, 1996;
    [sbull] ATR72-52-1028, dated July 5, 1993;
    [sbull] ATR72-52-1033, dated April 28, 1995;
    [sbull] ATR72-52-1029, Revision 1, dated November 16, 1994;
    [sbull] ATR72-53-1021, Revision 1, dated February 20, 1995;
    [sbull] ATR72-53-1014, Revision 2, dated October 15, 1992; and
    [sbull] ATR72-53-1020, dated October 6, 1992.
    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

[[Page 66775]]

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 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

    (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.

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


    Issued in Renton, Washington, on November 21, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-29701 Filed 11-26-03; 8:45 am]
BILLING CODE 4910-13-P