Airworthiness Directives; Aerospatiale Model ATR42-200, ATR42-300, and ATR42-320 Airplanes

[Federal Register Volume 70, Number 232 (Monday, December 5, 2005)]
[Rules and Regulations]
[Pages 72368-72371]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-23556]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22454; Directorate Identifier 2001-NM-108-AD; 
Amendment 39-14395; AD 2005-25-02]
RIN 2120-AA64


Airworthiness Directives; Aerospatiale Model ATR42-200, ATR42-
300, and ATR42-320 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Aerospatiale Model ATR42-200, ATR42-300, and 
ATR42-320 airplanes. That AD 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. The existing AD 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, the existing AD also requires 
replacement of friction plates, stop fittings, and bolts with new 
parts. This new AD requires additional corrective actions for certain 
airplanes. This AD results from discovery of cracks around key holes on 
certain fuselage frames where rivets were missing. We are issuing this 
AD 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: This AD becomes effective January 9, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of January 9, 
2006.
    On April 26, 2000 (65 FR 15226, March 22, 2000), the Director of 
the Federal Register approved the incorporation by reference of certain 
other publications.
    On November 18, 1993 (58 FR 53853, October 19, 1993), the Director 
of the Federal Register approved the incorporation by reference of a 
certain publication.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 
03, France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1137; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2000-05-26, amendment 
39-11636 (65 FR 15226, March 22, 2000). The existing AD applies to all 
ATR42-200, ATR42-300 and ATR42-320 airplanes. That NPRM was published 
in the Federal Register on September 19, 2005 (70 FR 54856). That NPRM 
proposed to continue to require 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. That NPRM also proposed to continue 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, that NPRM proposed to continue to 
require replacement of friction plates, stop fittings, and bolts with 
new parts. That NPRM further proposed to require additional corrective 
actions for certain airplanes.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM or 
on the determination of the cost to the public.

Clarification of Effective Date

    We have revised Note 2 of this AD to include the effective date of 
AD 2000-05-26.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD with the 
changes described previously. We have determined that these changes 
will neither increase the economic burden on any operator nor increase 
the scope of the AD.

Costs of Compliance

    This AD will affect about 106 Aerospatiale Model ATR42-200, ATR42-
300, and ATR42-320 airplanes of U.S. registry.
    The general visual inspection of fuselage frames 25 and 27 that is 
required by AD 2000-05-26 and

[[Page 72369]]

retained in this AD takes about 3 work hours per airplane, at an 
average labor rate of $65 per work hour. Based on these figures, the 
estimated cost of that currently required action is $195 per airplane.
    The cargo door hinge and skin replacement that is required by AD 
2000-05-26 and retained in this AD takes about 250 work hours per 
airplane, at an average labor rate of $65 per work hour. Required parts 
will cost approximately $9,880 per airplane. Based on these figures, 
the estimated cost of the currently required action is $26,130 per 
airplane.
    The general visual inspection of the key and tooling holes that is 
required by AD 2000-05-26 takes about 100 work hours per airplane, at 
an average rate of $65 per work hour. Based on these figures, the 
estimated cost of that currently required action is $6,500 per 
airplane.
    The eddy current and detailed visual inspections of the forward 
entry door stop fitting and friction plate that are required by AD 
2000-05-26 take about 2 work hours per airplane, at an average rate of 
$65 per work hour. Based on these figures, the estimated cost of those 
currently required actions is $130 per airplane.
    The replacement of the forward entry door stop fitting, friction 
plate, and upper door corner that is required by AD 2000-05-26 takes 
about 50 work hours per airplane, at an average rate of $65 per work 
hour. 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 these figures, the 
estimated cost of that currently required action is $3,250 per 
airplane.
    The new actions required by this AD will take about 250 work hours 
per airplane, at an average labor rate of $65 per work hour. Required 
parts will cost about $9,880 per airplane. Based on these figures, the 
estimated cost of the new actions required by this AD is $26,130 per 
airplane.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The FAA amends Sec.  39.13 by removing amendment 39-11636 (65 FR 
15226, March 22, 2000) and adding the following new airworthiness 
directive (AD):

2005-25-02 Aerospatiale: Amendment 39-14395. Docket No. FAA-2005-
22454; Directorate Identifier 2001-NM-108-AD.

Effective Date

    (a) This AD becomes effective January 9, 2006.

Affected ADs

    (b) This AD supersedes AD 2000-05-26.

Applicability

    (c) This AD applies to all Aerospatiale Model ATR42-200, ATR42-
300, and ATR-320 airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from discovery of cracks around key holes on 
certain fuselage frames where rivets were missing. We are issuing 
this AD 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.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of the Requirements of AD 2000-05-26

Frame 25 and 27 Inspection

    (f) 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 April 26, 2000, (the effective date of AD 2000-05-26) 
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 Regionale (ATR) Service Bulletin ATR42-53-0070, Revision 
2, dated March 22, 1993; or Revision 3, dated February 19, 1999.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``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 from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight 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 checked.''


    Note 2: Inspection of fuselage frames 25 and 27 accomplished 
prior to April 26, 2000, 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 (f) 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.

[[Page 72370]]

    (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, 
Transport Airplane Directorate, FAA; or the Direction 
G[eacute]n[eacute]rale 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

    (g) 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 April 26, 2000, whichever occurs later, except as 
provided by paragraph (h) of this AD, replace the hinges on the 
cargo 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; or ATR42-
52-0058, Revision 2, dated June 22, 2000.
    (h) Where the instructions in ATR Service Bulletin ATR42-52-
0058, Revision 1, dated March 1, 1995; or ATR42-52-0058, Revision 2, 
dated June 22, 2000, 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

    (i) For airplanes having serial numbers 003 through 208 
inclusive: Prior to the accumulation of 36,000 total flight cycles, 
or within 180 days after April 26, 2000, 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 inspection of 
each open tooling or key hole to detect cracks, in accordance with 
the service bulletin.

    Note 3: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

    (i) If no crack is found during the detailed inspection required 
by paragraph (i)(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 inspection required by 
paragraph (i)(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

    (j) For Model ATR42-300 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 
April 26, 2000, whichever occurs later, accomplish the requirements 
of paragraphs (j)(1) and (j)(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 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.
    (k) For Model ATR42-300 airplanes listed in ATR Service Bulletin 
ATR42-52-0052, Revision 1, dated March 2, 1993, accomplishment of 
the requirements of paragraph (l) of this AD at the time specified 
in paragraph (j) of this AD constitutes terminating action for the 
requirements of paragraph (j) of this AD.
    (l) For Model ATR42-300 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 April 26, 2000, 
whichever occurs later, accomplish the requirements of paragraphs 
(l)(1), (l)(2), and (l)(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.

New Requirements of This AD

Replacing Hinges on the Cargo Compartment Door and Fuselage

    (m) For airplanes identified as having main serial numbers 
(MSNs) 317, 319, 321, 323, 325, 327, 329 through 335 inclusive, 360, 
and 368, that are equipped with a cargo compartment door on which 
Aerospatiale Modification 3191 has not been accomplished: Prior to 
the accumulation of 27,000 total flight hours, or within 180 days 
after the effective date of this AD, whichever occurs later, replace 
the hinges on the cargo 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 the Accomplishment Instructions of Avions de 
Transport Regional (ATR) Service Bulletin ATR42-52-0058, Revision 2, 
dated June 22, 2000.
    (n) Where the instructions in ATR Service Bulletin ATR42-52-
0058, Revision 2, dated June 22, 2000, 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).

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (p) French airworthiness directive 2000-337-079(B), dated July 
26, 2000, also addresses the subject of this AD.

Material Incorporated by Reference

    (q) You must use the service bulletins listed in Table 1 of this 
AD to perform the actions that are required by this AD, unless the 
AD specifies otherwise.

              Table 1.--Material Incorporated by Reference
------------------------------------------------------------------------
 Avions de Transport regional
       service bulletin           Revision level            Date
------------------------------------------------------------------------
ATR42-52-0052.................  1................  March 2, 1993.
ATR42-52-0058.................  1................  March 1, 1995.
ATR42-52-0058.................  2................  June 22, 2000.
ATR42-52-0059.................  Original.........  February 16, 1995.
ATR42-53-0070.................  2................  March 22, 1993.

[[Page 72371]]

 
ATR42-53-0070.................  3................  February 19, 1999.
ATR42-53-0076.................  2................  October 15, 1996.
ATR42-53-0076.................  3................  February 19, 1999.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of Avions de Transport Regional Service 
Bulletin ATR42-52-0058, Revision 2, dated June 22, 2000, in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On April 26, 2000 (65 FR 15226, March 22, 2000), the 
Director of the Federal Register approved the incorporation by 
reference of the Avions de Transport Regionale service information 
as listed in Table 2 of this AD.

          Table 2.--Previous Material Incorporated by Reference
------------------------------------------------------------------------
 Avions de Transport regionale
       service bulletin           Revision level            Date
------------------------------------------------------------------------
ATR42-52-0052.................  1................  March 2, 1993.
ATR42-52-0058.................  1................  March 1, 1995.
ATR42-52-0059.................  Original.........  February 16, 1995.
ATR42-53-0070.................  3................  February 19, 1999.
ATR42-53-0076.................  2................  October 15, 1996.
ATR42-53-0076.................  3................  February 19, 1999.
------------------------------------------------------------------------

    (3) On November 18, 1993, (58 FR 53853, October 19, 1993), the 
Director of the Federal Register approved the incorporation by 
reference of Avions de Transport Regionale Service Bulletin ATR42-
53-0070, Revision 2, dated March 22, 1993.
    (4) Contact Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, 
Cedex 03, France, for copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on November 25, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-23556 Filed 12-2-05; 8:45 am]
BILLING CODE 4910-13-P

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