AD 2000-05-26

[Federal Register Volume 65, Number 56 (Wednesday, March 22, 2000)]
[Rules and Regulations]
[Pages 15226-15230]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-6328]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-94-AD; Amendment 39-11636; AD 2000-05-26]
RIN 2120-AA64


Airworthiness Directives; Aerospatiale Model ATR42-200, ATR42-
300, and ATR42-320 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 ATR42-300 and ATR42-320 
series airplanes, that currently requires inspections to determine the 
proper installation of rivets in certain key holes and to detect cracks 
in the area of the key holes where rivets are missing; and correction 
of discrepancies. This amendment increases the compliance time for the 
existing requirements and expands the applicability of the existing

[[Page 15227]]

AD to include additional airplanes. This action also requires various 
inspections of the subject area for discrepancies, and corrective 
actions, if necessary; and replacement of certain cargo door hinges 
with new hinges. For certain airplanes, this action also requires 
replacement of friction plates, stop fittings, and bolts with new 
parts. 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 cracks 
of the cargo door skin, certain frames, and entry door stop fittings 
and friction plates, which could result in reduced structural integrity 
of the airplane.

DATES: Effective April 26, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 26, 2000.
    The incorporation by reference of Avions de Transport Regionale 
(ATR) Service Bulletin ATR42-53-0070, Revision 2, dated March 22, 1993, 
was approved previously by the Director of the Federal Register as of 
November 18, 1993 (58 FR 53853, October 19, 1993).

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) by superseding 93-18-04, 
amendment 39-8689 (58 FR 53853, October 19, 1993), which is applicable 
to certain Aerospatiale Model ATR42-300 and ATR42-320 series airplanes, 
was published in the Federal Register on October 25, 1999 (64 FR 
57409). The action proposed to increase the compliance time for the 
existing requirements and expand the applicability of the existing AD 
to include additional airplanes. The action also proposed to require 
various inspections of the subject area for discrepancies, and 
corrective actions, if necessary; and replacement of certain cargo door 
hinges with new hinges. For certain airplanes, the action also proposed 
to require replacement of friction plates, stop fittings, and bolts 
with new parts.
    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 Genrale 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 
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.

Service Bulletin Revisions

    The same commenter requests that the proposed AD be revised to 
include later revisions of two service bulletins, and notes that the 
changes made do not affect the technical content of either bulletin. 
The commenter states that ATR Service Bulletin ATR42-53-0070, Revision 
3, dated February 19, 1999, is the most current version and should be 
included in paragraph (a) of the AD. The commenter also states that ATR 
Service Bulletin ATR42-53-0076, Revision 3, dated February 19, 1999, 
has been released and should be included in paragraph (d) of the AD. 
Revision 2 of each of these service bulletins was cited as the 
appropriate source of service information in the referenced paragraph 
of the proposed AD.
    The FAA concurs. The FAA has reviewed the referenced service 
bulletins and agrees that equivalent technical information is contained 
in the later revisions of the service bulletins. The FAA has revised 
paragraphs (a) and (d) of the final rule to include these revisions as 
appropriate sources of service information.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 106 airplanes of U.S. registry that will be 
affected by this AD.
    The general visual inspection of fuselage frames 25 and 27 that is 
required by this AD will take approximately 3 work hours per airplane 
to accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of this inspection required by this AD 
on U.S.

[[Page 15228]]

operators is estimated to be $180 per airplane.
    The cargo door hinge and skin replacement that is required by this 
AD will take approximately 250 work hours per airplane to accomplish, 
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 the door structure replacement required by this AD on U.S. 
operators is estimated to be $24,880 per airplane.
    The general visual inspection of the key and tooling holes that is 
required by this AD will take approximately 100 work hours per airplane 
to accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of this inspection required by this AD 
on U.S. operators is estimated to be $6,000 per airplane.
    The eddy current and detailed visual inspections of the forward 
entry door stop fitting and friction plate that are required by this AD 
will take approximately 2 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact of this inspection required by this AD on U.S. operators is 
estimated to be $120 per airplane.
    The replacement of the forward entry door stop fitting, friction 
plate, and upper door corner that is required in this AD action will 
take approximately 50 work hours per airplane to accomplish. The 
manufacturer has committed previously to its customers that it will 
bear the cost of replacement parts. As a result, the cost of those 
parts is not attributable to this AD. Based on this figure, the cost 
impact of the replacement required by this AD on U.S. operators is 
estimated to be $3,000 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.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-8689 (58 FR 
53853, October 19, 1993), and by adding a new airworthiness directive 
(AD), amendment 39-11636, to read as follows:

2000-05-26 Aerospatiale: Amendment 39-11636. Docket 98-NM-94-AD. 
Supersedes AD 93-18-04, Amendment 39-8689.

    Applicability: All Model ATR42-200, ATR42-300, and ATR42-320 
series airplanes; certificated in any category.

    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 (h) 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 cracks of the cargo door skin, certain 
frames, entry door stop fittings, or friction plates, which could 
result in reduced structural integrity of the airplane, accomplish 
the following:

Frame 25 and 27 Inspection

    (a) For airplanes having serial numbers 005 through 016 
inclusive, 018 through 030 inclusive, 032 through 036 inclusive, 
038, 040, 042, 043, 048 through 062 inclusive, 064 through 090 
inclusive, 092 through 094 inclusive, and 096 through 228 inclusive: 
Prior to the accumulation of 36,000 total flight cycles, or within 
180 days after the effective date of this AD, whichever occurs 
later, conduct a general visual inspection of fuselage frames 25 and 
27 to verify the proper installation of a rivet in each of the key 
holes, in accordance with Avions de Transport Regional (ATR) Service 
Bulletin ATR42-53-0070, Revision 2, dated March 22, 1993, or 
Revision 3, dated February 19, 1999.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being check.''


    Note 3: Inspection of fuselage frames 25 and 27 accomplished 
prior to the effective date of this AD in accordance with ATR 
Service Bulletin ATR42-53-0070, dated June 10, 1991, or Revision 1, 
dated June 12, 1992, is considered acceptable for compliance with 
the requirements of paragraph (a) of this AD.

    (1) If a rivet is installed in each of the key holes, no further 
action is required by this paragraph.
    (2) If a rivet is not installed in each of the key holes, prior 
to further flight, perform an eddy current inspection of each open 
key hole to detect cracks, in accordance with the service bulletin.
    (i) If no crack is found during the eddy current inspection, 
prior to further flight, install a rivet in the open key hole in 
accordance with the service bulletin. After such installation, no 
further action is required by this paragraph for that key hole.
    (ii) If any crack is found during the eddy current inspection, 
prior to further flight, repair the crack 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). For a repair 
method to be approved by the Manager, International Branch, ANM-116, 
as required by this paragraph, the Manager's approval letter must 
specifically reference this AD.

Inspection and Modification of Cargo Door Structure

    (b) For airplanes equipped with a cargo compartment door on 
which Aerospatiale Modification 3191 has not been accomplished: 
Prior to the accumulation of 27,000 total flight cycles, or within 
180 days after the effective date of this AD, whichever occurs 
later, except as provided by paragraph (c) of this AD, replace the 
hinges on the cargo

[[Page 15229]]

compartment door and fuselage (including inspections for fastener 
type and tolerances, hole diameters, or cracking, and repair; as 
applicable) with new improved hinges, in accordance with paragraph 
2. of the Accomplishment Instructions of ATR Service Bulletin ATR42-
52-0058, Revision 1, dated March 1, 1995.
    (c) Where the instructions in ATR Service Bulletin ATR42-52-
0058, Revision 1, dated March 1, 1995, specify that ATR is to be 
contacted for a repair, 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).

Frame Inspection

    (d) For airplanes having serial numbers 003 through 208 
inclusive: Prior to the accumulation of 36,000 total flight cycles, 
or within 180 days after the effective date of this AD, whichever 
occurs later, conduct a general visual inspection of the identified 
fuselage frames for proper installation of a rivet in each of the 
tooling and key holes, in accordance with ATR Service Bulletin 
ATR42-53-0076, Revision 2, dated October 15, 1996, or Revision 3, 
dated February 19, 1999.
    (1) If a rivet is installed in each of the tooling or key holes, 
no further action is required by this paragraph.
    (2) If a rivet is not installed in each of the tooling and key 
holes, prior to further flight, perform a detailed visual inspection 
of each open tooling or key hole to detect cracks, in accordance 
with the service bulletin.

    Note 4: For the purposes of this AD, a detailed visual 
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.''

    (i) If no crack is found during the detailed visual inspection 
required by paragraph (d)(2) of this AD, prior to further flight, 
install a rivet in the open hole in accordance with the service 
bulletin.
    (ii) If any crack is found during the visual inspection required 
by paragraph (d)(2) of this AD, prior to further flight, repair the 
crack in accordance with a method approved by the Manager, 
International Branch, ANM-116, or the DGAC (or its delegated agent).

Inspection and/or Replacement of Entry Door Structure

    (e) For Model ATR42-300 series airplanes having serial numbers 
listed in ATR Service Bulletin ATR42-52-0052, Revision 1, dated 
March 2, 1993: Except as provided by paragraph (f) of this AD, prior 
to the accumulation of 10,000 total flight cycles, or within 90 days 
after the effective date of this AD, whichever occurs later, 
accomplish the requirements of paragraphs (e)(1) and (e)(2) of this 
AD.
    (1) Perform an eddy current inspection of the forward entry door 
stop holes to detect cracking, in accordance with the service 
bulletin. If any cracking is detected, prior to further flight, 
replace any cracked forward entry door stop fitting with a new 
fitting, in accordance with the service bulletin.
    (2) Perform a detailed visual inspection of the forward entry 
door friction plates for wear, in accordance with the service 
bulletin. If wear is found on any friction plate, and the wear has a 
depth equal to or greater than 0.8mm (0.0315 in.), prior to further 
flight, replace the friction plate with a new or serviceable part in 
accordance with the service bulletin.
    (f) For Model ATR42-300 series airplanes listed in ATR Service 
Bulletin ATR42-52-0052, Revision 1, dated March 2, 1993, 
accomplishment of the requirements of paragraph (g) of this AD at 
the time specified in paragraph (e) of this AD constitutes 
terminating action for the requirements of paragraph (e) of this AD.
    (g) For Model ATR42-300 series airplanes listed in ATR Service 
Bulletin ATR42-52-0059, dated February 16, 1995: Prior to the 
accumulation of 18,000 total flight cycles, or within 180 days after 
the effective date of this AD, whichever occurs later, accomplish 
the requirements of paragraphs (g)(1), (g)(2), and (g)(3) of this AD 
in accordance with the service bulletin.
    (1) Replace the forward entry door friction plates with improved 
friction plates.
    (2) Replace the upper corners of the forward entry door surround 
structure with improved door surround corners.
    (3) Replace the forward entry door stop fittings and bolts with 
improved fittings and bolts.

Alternative Methods of Compliance

    (h) 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 5: 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

    (i) 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.

Incorporation by Reference

    (j) Except as required by paragraphs (a)(2)(ii), (c), and 
(d)(2)(ii) of this AD, the actions shall be done in accordance with 
the following Avions de Transport Regionale service bulletins, as 
applicable:
      

----------------------------------------------------------------------------------------------------------------
                                                        Revision level shown on
 Service bulletin referenced and date    Page number             page                   Date shown on page
----------------------------------------------------------------------------------------------------------------
ATR42-53-0070, Revision 2, March 22,          1, 2, 9  2.......................  March 22, 1993.
 1993.
                                           3-7, 10-12  1.......................  June 12, 1992.
                                                8, 13  Original................  June 10, 1991.
ATR42-53-0070, Revision 3, February            1-6, 9  3.......................  February 19, 1999
 19, 1999..
                                             7, 10-12  1.......................  June 12, 1992.
                                                8, 13  Original................  June 10, 1991.
ATR42-52-0058, Revision 1, March 1,             1-117  1.......................  March 1, 1995
 1995..
                                                39-99  (These pages are not
                                                        used).
ATR42-53-0076, Revision 2, October                1-6  2.......................  October 15, 1996
 15, 1996..
                                        7, 8, 11, 12,  1.......................  November 4, 1994.
                                                17-19
                                         9, 10, 13-16  Original................  May 13, 1993.
ATR42-53-0076, Revision 3, February               1-6  3.......................  February 19, 1999
 19, 1999..
                                        7, 8, 11, 12,  1.......................  November 4, 1994.
                                                17-19
                                         9, 10, 13-16  Original................  May 13, 1993.
ATR42-52-0052, Revision 1, March 2,        1-4, 9, 10  1.......................  March 2, 1993
 1993..
                                           5-8, 11-17  Original................  January 11, 1991.
ATR42-52-0059, February 16, 1995.....            1-43  Original................  February 16, 1995.
----------------------------------------------------------------------------------------------------------------


[[Page 15230]]

    (1) The incorporation by reference of Avions de Transport 
Regionale Service Bulletin ATR42-53-0070, Revision 3, dated February 
19, 1999; Avions de Transport Regionale Service Bulletin ATR42-52-
0058, Revision 1, dated March 1, 1995; Avions de Transport Regionale 
Service Bulletin ATR42-53-0076, Revision 2, dated October 15, 1996; 
Avions de Transport Regionale Service Bulletin ATR42-53-0076, 
Revision 3, dated February 19, 1999; Avions de Transport Regionale 
Service Bulletin ATR42-52-0052, Revision 1, dated March 2, 1993; and 
Avions de Transport Regionale Service Bulletin ATR42-52-0059, dated 
February 16, 1995; 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 Avions de Transport 
Regionale Service Bulletin ATR42-53-0070, Revision 2, dated March 
22, 1993, was approved previously by the Director of the Federal 
Registeras of November 18, 1993 (58 FR 53853, October 19, 1993).
    (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 6: The subject of this AD is addressed in French 
airworthiness directive 92-044-046(B)R2, dated November 5, 1997.

    (k) This amendment becomes effective on April 26, 2000.

    Issued in Renton, Washington, on March 9, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-6328 Filed 3-22-00; 8:45 am]
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