Airworthiness Directives; Aerospatiale Model ATR42-200, ATR42-300, and ATR42-320 Airplanes, 72368-72371 [05-23556]
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Federal Register / Vol. 70, No. 232 / Monday, December 5, 2005 / Rules and Regulations
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March 18, 2005.
Nov. 9, 2004.
April 6, 2004.
The Director of the Federal Register
approved the incorporation by reference of
this document in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Empresa
Brasileira de Aeronautica S.A. (EMBRAER),
P.O. Box 343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil, for a 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 https://
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 https://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. 05–23555 Filed 12–2–05; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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
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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 https://
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
https://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
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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
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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
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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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–11636 (65 FR
15226, March 22, 2000) and adding the
following new airworthiness directive
(AD):
I
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.
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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.
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(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 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
(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 § 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
ATR42–52–0052
ATR42–52–0058
ATR42–52–0058
ATR42–52–0059
ATR42–53–0070
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March 2, 1993.
March 1, 1995.
June 22, 2000.
February 16, 1995.
March 22, 1993.
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72371
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE—Continued
Avions de Transport regional service bulletin
Revision level
ATR42–53–0070 ...............................................................
ATR42–53–0076 ...............................................................
ATR42–53–0076 ...............................................................
3 .........................................
2 .........................................
3 .........................................
(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
Date
February 19, 1999.
October 15, 1996.
February 19, 1999.
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
ATR42–52–0052
ATR42–52–0058
ATR42–52–0059
ATR42–53–0070
ATR42–53–0076
ATR42–53–0076
...............................................................
...............................................................
...............................................................
...............................................................
...............................................................
...............................................................
(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
https://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 https://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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2005–21256; Airspace
Docket No. 05–AGL–04]
Establishment of Class D Airspace;
Eau Claire, WI
Federal Aviation
Administration (FAA), DOT.
ACTION: Direct final rule; confirmation of
effective date.
AGENCY:
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18:02 Dec 02, 2005
Jkt 208001
Date
1 .........................................
1 .........................................
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3 .........................................
2 .........................................
3 .........................................
March 2, 1993.
March 1, 1995.
February 16, 1995.
February 19, 1999.
October 15, 1996.
February 19, 1999.
SUMMARY: This document confirms the
effective date of the direct final rule
which establishes Class D airspace at
Eau Claire, WI.
EFFECTIVE DATE:
0901 UTC, October 27,
2005.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA 2005–20417; Airspace
Docket No. 05–ANM–06]
FOR FURTHER INFORMATION CONTACT:
Steve Davis, FAA Terminal Operations,
Central Service Office, Airspace and
Procedures Branch, AGL–530, Federal
Aviation Administration, 2300 East
Devon Avenue, Des Plaines, Illinois
60018, telephone (847) 294–7131, or
David Sapadin (847) 294–7477.
The FAA
published this direct final rule with a
request for comments in the Federal
Register on September 6, 2005 (70 FR
52903). The FAA uses the direct final
rulemaking procedure for a noncontroversial rule where the FAA
believes that there will be no adverse
public comment. This direct final rule
advised the public that no adverse
comments were anticipated, and that
unless a written adverse comment, or a
written notice of intent to submit such
an adverse comment, were received
within the comment period, the
regulation would become effective on
that date.
SUPPLEMENTARY INFORMATION:
Issued in Des Plaines, Illinois, on
November 1, 2005.
Nancy B. Kort,
Area Director, Central Terminal Operations.
[FR Doc. 05–23633 Filed 12–2–05; 8:45 am]
BILLING CODE 4910–13–M
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Amendment to Class E Airspace;
Wenatchee, WA
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This final rule will revise the
Class E airspace area at Wenatchee, WA.
Additional Class E airspace is necessary
to accommodate aircraft using a new
Instrument Landing System (ILS)
Standard Instrument Approach
Procedure (SIAP) at Wenatchee/
Pangborn Memorial Memorial Airport.
This change is necessary for the safety
of Instrument Flight Rules (IFR) aircraft
executing the new SIAP at Wenatchee/
Pangborn Memorial Airport, Wenatchee,
WA.
EFFECTIVE DATE: 0901 UTC, January 19,
2006.
FOR FURTHER INFORMATION CONTACT: Ed
Haeseker, Federal Aviation
Administration, Western En Route and
Oceanic Area Office, Airspace Branch,
1601 Lind Avenue, SW., Renton, WA
98055–4056; telephone (425) 227–2527.
SUPPLEMENTARY INFORMATION:
History
On May 25, 2005, the FAA proposed
to amend Title 14 Code of Federal
Regulations part 71 (CFR part 71) by
revising Class E airspace at Wenatchee,
WA (70 FR 20093). The proposed action
E:\FR\FM\05DER1.SGM
05DER1
]]>Agencies
[Federal Register Volume 70, Number 232 (Monday, December 5, 2005)]
[Rules and Regulations]
[Pages 72368-72371]
From the Federal Register Online via the Government Printing 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 https://
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 https://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 https://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 https://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
