Airworthiness Directives; Airbus Model A319 and A320-200 Series Airplanes, 685-687 [05-103]
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Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Rules and Regulations
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. 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:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
2004–26–08 Bombardier, Inc. (Formerly
Canadair): Amendment 39–13920.
Docket No. FAA–2004–19496;
Directorate Identifier 2003–NM–181–AD.
Effective Date
(a) This AD becomes effective February 9,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model
CL–215–6B11 (CL215T variant) series
airplanes, having serial numbers (S/N) 1056
through 1125 inclusive, and Model CL–215–
6B11 (CL415 variant) series airplanes having
S/Ns 2001 through 2053 inclusive;
certificated in any category.
Unsafe Condition
(d) This AD was prompted by a few
incidents of external oil leaks from the oil
pump of the power control unit due to a
malfunction of the pressure regulating valve.
We are issuing this AD to prevent fracturing
of the pump body, which could result in loss
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Compliance
Issued in Renton, Washington, on
December 20, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–101 Filed 1–4–05; 8:45 am]
(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.
BILLING CODE 4910–13–P
Replacement
DEPARTMENT OF TRANSPORTATION
(f) Within 12 months after the effective
date of this AD, replace the mounting pad
studs of the auxiliary feather pump with
new, longer studs, and install a pressure
relief valve; in accordance with the
Accomplishment Instructions of Bombardier
Service Bulletin 215–3108, dated March 28,
2001 (for Model CL–215–6B11 (CL215T
variant) series airplanes); or Bombardier
Service Bulletin 215–4234, dated March 28,
2001 (for Model CL–215–6B11 (CL415
variant) series airplanes); as applicable.
Note 1: Bombardier Service Bulletin 215–
3108 and Bombardier Service Bulletin 215–
4234 refer to Pratt & Whitney Canada Service
Bulletin PW100–72–21636, Revision 2, dated
June 26, 2002, as an additional source of
service information for accomplishing the
replacement of the mounting pad studs.
No Reporting
(g) Although the service bulletin refers to
a reporting requirement in paragraph 2.B,
that reporting is not required by this AD.
Alternative Methods of Compliance
(AMOCs)
I
§ 39.13
of engine oil, and consequent inability to
maintain engine oil pressure and to feather
the propeller.
685
(h) The Manager, New York Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Related Information
(i) Canadian airworthiness directive CF–
2002–14, dated February 13, 2002, also
addresses the subject of this AD.
Material Incorporated by Reference
(j) You must use Bombardier Service
Bulletin 215–3108, dated March 28, 2001; or
Bombardier Service Bulletin 215–4234, dated
March 28, 2001; as applicable; to perform the
actions that are required by this AD, unless
the AD specifies otherwise. The Director of
the Federal Register approves the
incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. For copies of the
service information, contact Bombardier,
Inc., Canadair, Aerospace Group, P.O. Box
6087, Station Centre-ville, Montreal, Quebec
H3C 3G9, Canada. For information on the
availability of this material at the National
Archives and Records Administration
(NARA), call (202) 741–6030, or go to http:/
/www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
You may view the AD docket at the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
Room PL–401, Nassif Building, Washington,
DC.
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Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003–NM–135–AD; Amendment
39–13925; AD 2005–01–01]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A319 and A320–200 Series Airplanes
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment supersedes
an existing airworthiness directive (AD),
applicable to certain Airbus Model
A319 and A320–200 series airplanes,
that currently requires repetitive
inspections to detect loose, missing, or
discrepant rivets in specified areas of
the door frames of the overwing
emergency exits; measurement of the
grip length of all rivets in the specified
areas; and corrective action if necessary,
which terminates the repetitive
inspections. This new amendment also
requires an inspection for correct
dimensions of the interior countersinks
of the rivet holes, and related corrective
action. The actions specified by this AD
are intended to prevent loose, missing,
or discrepant rivets, which could lead to
reduced structural integrity of the door
frames of the overwing emergency exits.
This action is intended to address the
identified unsafe condition.
DATES: Effective February 9, 2005.
The incorporation by reference of
certain service information, as listed in
the regulations, is approved by the
Director of the Federal Register as of
February 9, 2005.
The incorporation by reference of
certain other service information, as
listed in the regulations, was approved
previously by the Director of the Federal
Register as of April 5, 2002 (67 FR 9392,
March 1, 2002).
ADDRESSES: The service information
referenced in this AD may be obtained
from Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France.
This information may be examined at
the Federal Aviation Administration
(FAA), Transport Airplane Directorate,
Rules Docket, 1601 Lind Avenue, SW.,
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686
Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Rules and Regulations
Renton, Washington; or at the National
Archives and Records Administration
(NARA). For information on the
availability of this material at NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2125;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION: A
proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39)
by superseding AD 2002–04–10,
amendment 39–12667 (67 FR 9392,
March 1, 2002), which is applicable to
certain Airbus Model A319 and A320–
200 series airplanes, was published in
the Federal Register on April 7, 2004
(69 FR 18304). The action proposed to
retain the existing requirements for
repetitive inspections for loose, missing,
or discrepant rivets in specified areas of
the door frames of the overwing
emergency exits; and measurement of
the grip length of all rivets in the
specified areas; and corrective action if
necessary, which terminates the
repetitive inspections. The proposed AD
also proposed to add an inspection for
correct dimensions of the interior
countersinks of the rivet holes, and
related corrective action.
FOR FURTHER INFORMATION CONTACT:
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
The commenters support the proposed
AD.
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
public interest require adopting the AD
as proposed.
Cost Impact
This AD affects about 168 airplanes of
U.S. registry.
The inspections required by AD
2002–04–10 take about 1 work hour per
airplane, at an average labor rate of $65
per work hour. Based on these figures,
the cost impact of those inspections is
estimated to be $65 per airplane, per
inspection cycle.
The new inspection required by this
AD takes about 1 work hour per
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airplane, at an average labor rate of $65
per work hour. Based on these figures,
the cost impact of the new inspection on
U.S. operators is estimated to be
$10,920, or $65 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, and that no
operator would accomplish those
actions in the future if this AD were not
adopted. The cost impact figures
discussed in AD rulemaking actions
represent only the time necessary to
perform the specific actions actually
required by the AD. These figures
typically do not include incidental
costs, such as the time required to gain
access and close up, planning time, or
time necessitated by other
administrative actions.
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 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
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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:
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. Section 39.13 is amended by
removing amendment 39–12667 (67 FR
9392, March 1, 2002), and by adding a
new airworthiness directive (AD),
amendment 39–13925, to read as
follows:
I
2005–01–01 Airbus: Amendment 39–13925.
Docket 2003–NM–135–AD. Supersedes
AD 2002–04–10, Amendment 39–12667.
Applicability: Model A319 series airplanes
and A320–200 series airplanes; certificated in
any category; as listed in Airbus Service
Bulletin A320–53–1147, dated September 22,
2000; Revision 02, dated December 3, 2002;
or Revision 03, dated August 5, 2003.
Compliance: Required as indicated, unless
accomplished previously.
To prevent loose, missing, or discrepant
rivets in specified areas of the door frames of
the overwing emergency exits, which could
lead to reduced structural integrity of the
door frames, accomplish the following:
Restatement of Requirements of AD 2002–
04–10
Repetitive Inspections
(a) Within 3,500 flight cycles after April 5,
2002 (the effective date of AD 2002–04–10,
amendment 39–12667): Conduct a detailed
inspection of the specified areas of the door
frames of the overwing emergency exits for
loose, missing, or discrepant rivets, in
accordance with Part B and Figure 5 of the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1147, dated
September 22, 2000; Revision 02, dated
December 3, 2002; or Revision 03, dated
August 5, 2003. If no loose, missing, or
discrepant rivets are found, repeat the
inspection at intervals not to exceed 3,500
flight cycles until the requirements of
paragraph (d) have been accomplished. As of
the effective date of this AD, only Revision
02 or Revision 03 of the service bulletin may
be used.
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Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Rules and Regulations
Note 1: For the purposes of this AD, a
detailed inspection is defined as: ‘‘An
intensive visual examination of a specific
structural area, system, installation, or
assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface
cleaning and elaborate access procedures
may be required.’’
countersinks of the rivet holes of the door
frames of the overwing emergency exits; and
any related corrective action; per the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1147, Revision 02,
including Appendix 01, dated December 3,
2002; or Revision 03, including Appendix 01,
dated August 5, 2003. Do any related
corrective action within 1,000 flight cycles
after doing the inspection.
Corrective Action
(b) If the inspection required by paragraph
(a) of this AD reveals that there are loose,
missing, or discrepant rivets: Prior to further
flight, accomplish the requirements of either
paragraph (b)(1) or (b)(2) of this AD, in
accordance with Part C and Figure 5 of the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1147, dated
September 22, 2000; Revision 02, dated
December 3, 2002; or Revision 03, dated
August 5, 2003. As of the effective date of
this AD, only Revision 02 or Revision 03 of
the service bulletin may be used.
(1) Measure the grip length of all rivets in
the specified areas in which the loose,
missing, or discrepant rivets were detected
and perform corrective action (e.g.,
inspecting rivet holes for cracks, opening up
rivet holes, repairing cracks at rivet holes,
and installing new rivets) as applicable, per
the service bulletin; except as specified in
paragraph (c) of this AD. Repeat the detailed
visual inspection required by paragraph (a) of
this AD at intervals not to exceed 3,500 flight
cycles until the requirements of paragraph (d)
of this AD have been accomplished.
(2) Measure the grip length of all rivets in
all specified areas and perform corrective
action (e.g., inspecting rivet holes for cracks,
opening up rivet holes, repairing cracks at
rivet holes, and installing new rivets) as
applicable, per the service bulletin; except as
specified in paragraph (c) of this AD.
(c) If Airbus Service Bulletin A320–53–
1147, dated September 22, 2000; Revision 02,
dated December 3, 2002; or Revision 03,
dated August 5, 2003; recommends
contacting the manufacturer for instructions
concerning certain repairs, perform those
repairs in accordance with a method
approved by the Manager, International
Branch, ANM–116, FAA, Transport Airplane
´ ´
Directorate, or by the Direction Generale de
l’Aviation Civile or its delegated agent.
(f)(1) In accordance with 14 CFR 39.19, the
Manager, International Branch, ANM–116, is
authorized to approve alternative methods of
compliance for this AD.
(2) Alternative methods of compliance,
approved previously per AD 2002–04–10,
amendment 39–12667, are approved as
alternative methods of compliance with
paragraphs (a) and (b) of this AD.
Note 2: The subject of this AD is addressed
in French airworthiness directive 2003–
147(B) R1, dated May 14, 2003.
Terminating Action
(d) Prior to the accumulation of 24,000
total flight cycles or within 3,500 flight
cycles after April 5, 2002, whichever occurs
later: Accomplish the requirements of
paragraph (b)(2) of this AD, which constitutes
terminating action for the requirements
specified in paragraphs (a) and (b) of this AD.
New Requirements of This AD
Inspection of Interior Countersinks/
Corrective Action
(e) Prior to the accumulation of 24,000 total
flight cycles or within 3,500 flight cycles
after the effective date of this AD, whichever
occurs later: Do a detailed inspection for
correct dimensions of the interior
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Alternative Methods of Compliance
Incorporation by Reference
(g) Unless otherwise specified in this AD,
the actions must be done in accordance with
Airbus Service Bulletin A320–53–1147,
dated September 22, 2000; Airbus Service
Bulletin A320–53–1147, Revision 02,
including Appendix 01, dated December 3,
2002; or Airbus Service Bulletin A320–53–
1147, Revision 03, including Appendix 01,
dated August 5, 2003.
(1) The incorporation by reference of
Airbus Service Bulletin A320–53–1147,
Revision 02, including Appendix 01, dated
December 3, 2002; and Airbus Service
Bulletin A320–53–1147, Revision 03,
including Appendix 01, dated August 5,
2003, 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
Airbus Service Bulletin A320–53–1147,
dated September 22, 2000, was approved
previously by the Director of the Federal
Register as of April 5, 2002 (67 FR 9392,
March 1, 2002).
(3) Copies may be obtained from Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France. Copies may be inspected at
the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Effective Date
(h) This amendment becomes effective on
February 9, 2005.
Issued in Renton, Washington, on
December 27, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–103 Filed 1–4–05; 8:45 am]
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687
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–18557; Directorate
Identifier 2003–NM–174–AD; Amendment
39–13926; AD 2005–01–02]
RIN 2120–AA64
Airworthiness Directives; Lockheed
Model 1329 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Lockheed Model 1329 series airplanes.
This AD requires repetitive inspections
to detect crack damage in the front spar
cap assembly of the lower vertical
stabilizer; reworking the spar cap
doublers if no crack damage is found
during any inspection; and repairing if
any crack damage is found during any
inspection. This AD is prompted by
reports of cracks in the front spar cap
assembly of the lower vertical stabilizer
at box beam station 24 on the aft side
of the 25% chord line. We are issuing
this AD to find and fix cracks in the
front spar cap assembly of the lower
vertical stabilizer, which could result in
rapid crack propagation and failure of
the front spar cap. Failure of the front
spar cap could lead to loss of rudder
control and consequent reduced
controllability of the airplane.
DATES: This AD becomes effective
February 9, 2005.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of February 9, 2005.
ADDRESSES: For service information
identified in this AD, contact Lockheed
Martin Aircraft & Logistics Center, 120
Orion Street, Greenville, South Carolina
29605. You can examine this
information at the National Archives
and Records Administration (NARA).
For information on the availability of
this material at NARA, call (202) 741–
6030, or go to: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2004–
18557; the directorate identifier for this
docket is 2003–NM–174–AD.
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]]>Agencies
[Federal Register Volume 70, Number 3 (Wednesday, January 5, 2005)]
[Rules and Regulations]
[Pages 685-687]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-103]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-135-AD; Amendment 39-13925; AD 2005-01-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A319 and A320-200 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Airbus Model A319 and A320-200 series
airplanes, that currently requires repetitive inspections to detect
loose, missing, or discrepant rivets in specified areas of the door
frames of the overwing emergency exits; measurement of the grip length
of all rivets in the specified areas; and corrective action if
necessary, which terminates the repetitive inspections. This new
amendment also requires an inspection for correct dimensions of the
interior countersinks of the rivet holes, and related corrective
action. The actions specified by this AD are intended to prevent loose,
missing, or discrepant rivets, which could lead to reduced structural
integrity of the door frames of the overwing emergency exits. This
action is intended to address the identified unsafe condition.
DATES: Effective February 9, 2005.
The incorporation by reference of certain service information, as
listed in the regulations, is approved by the Director of the Federal
Register as of February 9, 2005.
The incorporation by reference of certain other service
information, as listed in the regulations, was approved previously by
the Director of the Federal Register as of April 5, 2002 (67 FR 9392,
March 1, 2002).
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France. This information may be examined at the Federal Aviation
Administration (FAA), Transport Airplane Directorate, Rules Docket,
1601 Lind Avenue, SW.,
[[Page 686]]
Renton, Washington; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/ibr_
locations.html.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2002-04-10,
amendment 39-12667 (67 FR 9392, March 1, 2002), which is applicable to
certain Airbus Model A319 and A320-200 series airplanes, was published
in the Federal Register on April 7, 2004 (69 FR 18304). The action
proposed to retain the existing requirements for repetitive inspections
for loose, missing, or discrepant rivets in specified areas of the door
frames of the overwing emergency exits; and measurement of the grip
length of all rivets in the specified areas; and corrective action if
necessary, which terminates the repetitive inspections. The proposed AD
also proposed to add an inspection for correct dimensions of the
interior countersinks of the rivet holes, and related corrective
action.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD. The commenters support the proposed AD.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD as proposed.
Cost Impact
This AD affects about 168 airplanes of U.S. registry.
The inspections required by AD 2002-04-10 take about 1 work hour
per airplane, at an average labor rate of $65 per work hour. Based on
these figures, the cost impact of those inspections is estimated to be
$65 per airplane, per inspection cycle.
The new inspection required by this AD takes about 1 work hour per
airplane, at an average labor rate of $65 per work hour. Based on these
figures, the cost impact of the new inspection on U.S. operators is
estimated to be $10,920, or $65 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, and that no operator would accomplish those actions in the future
if this AD were not adopted. The cost impact figures discussed in AD
rulemaking actions represent only the time necessary to perform the
specific actions actually required by the AD. These figures typically
do not include incidental costs, such as the time required to gain
access and close up, planning time, or time necessitated by other
administrative actions.
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 Impact
The regulations adopted herein will not have a substantial direct
effect on the States, on the relationship between the national
Government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. Section 39.13 is amended by removing amendment 39-12667 (67 FR 9392,
March 1, 2002), and by adding a new airworthiness directive (AD),
amendment 39-13925, to read as follows:
2005-01-01 Airbus: Amendment 39-13925. Docket 2003-NM-135-AD.
Supersedes AD 2002-04-10, Amendment 39-12667.
Applicability: Model A319 series airplanes and A320-200 series
airplanes; certificated in any category; as listed in Airbus Service
Bulletin A320-53-1147, dated September 22, 2000; Revision 02, dated
December 3, 2002; or Revision 03, dated August 5, 2003.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loose, missing, or discrepant rivets in specified
areas of the door frames of the overwing emergency exits, which
could lead to reduced structural integrity of the door frames,
accomplish the following:
Restatement of Requirements of AD 2002-04-10
Repetitive Inspections
(a) Within 3,500 flight cycles after April 5, 2002 (the
effective date of AD 2002-04-10, amendment 39-12667): Conduct a
detailed inspection of the specified areas of the door frames of the
overwing emergency exits for loose, missing, or discrepant rivets,
in accordance with Part B and Figure 5 of the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1147, dated
September 22, 2000; Revision 02, dated December 3, 2002; or Revision
03, dated August 5, 2003. If no loose, missing, or discrepant rivets
are found, repeat the inspection at intervals not to exceed 3,500
flight cycles until the requirements of paragraph (d) have been
accomplished. As of the effective date of this AD, only Revision 02
or Revision 03 of the service bulletin may be used.
[[Page 687]]
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
Corrective Action
(b) If the inspection required by paragraph (a) of this AD
reveals that there are loose, missing, or discrepant rivets: Prior
to further flight, accomplish the requirements of either paragraph
(b)(1) or (b)(2) of this AD, in accordance with Part C and Figure 5
of the Accomplishment Instructions of Airbus Service Bulletin A320-
53-1147, dated September 22, 2000; Revision 02, dated December 3,
2002; or Revision 03, dated August 5, 2003. As of the effective date
of this AD, only Revision 02 or Revision 03 of the service bulletin
may be used.
(1) Measure the grip length of all rivets in the specified areas
in which the loose, missing, or discrepant rivets were detected and
perform corrective action (e.g., inspecting rivet holes for cracks,
opening up rivet holes, repairing cracks at rivet holes, and
installing new rivets) as applicable, per the service bulletin;
except as specified in paragraph (c) of this AD. Repeat the detailed
visual inspection required by paragraph (a) of this AD at intervals
not to exceed 3,500 flight cycles until the requirements of
paragraph (d) of this AD have been accomplished.
(2) Measure the grip length of all rivets in all specified areas
and perform corrective action (e.g., inspecting rivet holes for
cracks, opening up rivet holes, repairing cracks at rivet holes, and
installing new rivets) as applicable, per the service bulletin;
except as specified in paragraph (c) of this AD.
(c) If Airbus Service Bulletin A320-53-1147, dated September 22,
2000; Revision 02, dated December 3, 2002; or Revision 03, dated
August 5, 2003; recommends contacting the manufacturer for
instructions concerning certain repairs, perform those repairs in
accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate, or by the
Direction G[eacute]n[eacute]rale de l'Aviation Civile or its
delegated agent.
Terminating Action
(d) Prior to the accumulation of 24,000 total flight cycles or
within 3,500 flight cycles after April 5, 2002, whichever occurs
later: Accomplish the requirements of paragraph (b)(2) of this AD,
which constitutes terminating action for the requirements specified
in paragraphs (a) and (b) of this AD.
New Requirements of This AD
Inspection of Interior Countersinks/Corrective Action
(e) Prior to the accumulation of 24,000 total flight cycles or
within 3,500 flight cycles after the effective date of this AD,
whichever occurs later: Do a detailed inspection for correct
dimensions of the interior countersinks of the rivet holes of the
door frames of the overwing emergency exits; and any related
corrective action; per the Accomplishment Instructions of Airbus
Service Bulletin A320-53-1147, Revision 02, including Appendix 01,
dated December 3, 2002; or Revision 03, including Appendix 01, dated
August 5, 2003. Do any related corrective action within 1,000 flight
cycles after doing the inspection.
Alternative Methods of Compliance
(f)(1) In accordance with 14 CFR 39.19, the Manager,
International Branch, ANM-116, is authorized to approve alternative
methods of compliance for this AD.
(2) Alternative methods of compliance, approved previously per
AD 2002-04-10, amendment 39-12667, are approved as alternative
methods of compliance with paragraphs (a) and (b) of this AD.
Note 2: The subject of this AD is addressed in French
airworthiness directive 2003-147(B) R1, dated May 14, 2003.
Incorporation by Reference
(g) Unless otherwise specified in this AD, the actions must be
done in accordance with Airbus Service Bulletin A320-53-1147, dated
September 22, 2000; Airbus Service Bulletin A320-53-1147, Revision
02, including Appendix 01, dated December 3, 2002; or Airbus Service
Bulletin A320-53-1147, Revision 03, including Appendix 01, dated
August 5, 2003.
(1) The incorporation by reference of Airbus Service Bulletin
A320-53-1147, Revision 02, including Appendix 01, dated December 3,
2002; and Airbus Service Bulletin A320-53-1147, Revision 03,
including Appendix 01, dated August 5, 2003, 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 Airbus Service Bulletin
A320-53-1147, dated September 22, 2000, was approved previously by
the Director of the Federal Register as of April 5, 2002 (67 FR
9392, March 1, 2002).
(3) Copies may be obtained from Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW.,
Renton, Washington; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
Effective Date
(h) This amendment becomes effective on February 9, 2005.
Issued in Renton, Washington, on December 27, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-103 Filed 1-4-05; 8:45 am]
BILLING CODE 4910-13-P
