Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 42267-42269 [05-14173]
Download as PDF
<![CDATA[
42267
Federal Register / Vol. 70, No. 140 / Friday, July 22, 2005 / Rules and Regulations
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE—Continued
Service bulletin
Effective pages
Revision level
shown on page
(26) Lockheed TriStar L–1011 Service Bulletin 093–57–058,
Revision 5, dated June 9, 1983.
1, 3, 4, 7 ..................................
2 ...............................................
5, 6, 9, 10, 12–14 ....................
8, 11, 16–19 ............................
15 .............................................
1–51 .........................................
5 .............................
4 .............................
Basic Issue ............
3 .............................
2 .............................
2 .............................
June 9, 1983.
July 6, 1981.
September 16, 1975.
October 19, 1978.
June 30, 1978.
July 27, 1990.
1–6, 23–28, 33, 34, 41, 42,
45–52.
7–22, 29–32, 35–40, 43, 44 ....
1–19 .........................................
3 .............................
2 .............................
June 30, 1992.
July 27, 1990.
Basic Issue ............
December 9, 1994.
(27) Lockheed TriStar L–1011 Service Bulletin 093–53–070,
Revision 2, dated July 27, 1990.
(28) Lockheed TriStar L–1011 Service Bulletin 093–53–070,
Revision 3, dated June 30, 1992.
(29) Lockheed TriStar L–1011 Service Bulletin 093–53–070,
Basic Issue, dated December 9, 1994.
Effective Date
(g) This amendment becomes effective on
August 26, 2005.
Issued in Renton, Washington, on July 8,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–14089 Filed 7–21–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20867; Directorate
Identifier 2004–NM–188–AD; Amendment
39–14194; AD 2005–15–05]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–600, B4–600R, and F4–600R
Series Airplanes, and Model A300 C4–
605R Variant F Airplanes (Collectively
Called A300–600 Series Airplanes)
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A300–600 series
airplanes. This AD requires an
inspection for evidence of chafing
between the hydraulic flexible hose and
the ram air turbine (RAT) hub, and
related investigative and corrective
actions if necessary. This AD is
prompted by reports of holes in the RAT
hub cover. We are issuing this AD to
prevent a hole in the RAT hub cover. A
hole in the RAT hub cover could allow
water to enter the RAT governing
mechanism, freeze during flight, and
jam the governing mechanism. In
addition, the metal particles that result
from chafing between the hydraulic
VerDate jul<14>2003
15:02 Jul 21, 2005
Jkt 205001
flexible hose and the RAT could mix
with the lubricant grease and degrade
the governing mechanism. In an
emergency, a jammed or degraded RAT
could result in its failure to deploy, loss
of hydraulic pressure or electrical power
to the airplane, and consequent reduced
controllability of the airplane.
DATES: This AD becomes effective
August 26, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of August 26, 2005.
ADDRESSES: For service information
identified in this AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the 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 U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20867; the directorate
identifier for this docket is 2004–NM–
188–AD.
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: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Airbus Model A300
B4–600, B4–600R, and F4–600R series
airplanes, and Model A300 C4–605R
Variant F airplanes (collectively called
A300–600 series airplanes). That action,
published in the Federal Register on
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
Date
April 6, 2005 (70 FR 17340), proposed
to require an inspection for evidence of
chafing between the hydraulic flexible
hose and the ram air turbine (RAT) hub,
and related investigative and corrective
actions if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that was
submitted on the proposed AD.
Request To Revise Compliance Time
The commenter requests that the
compliance time be revised from the
proposed 2,500 flight hours after the
effective date of the AD to 15 months
after the effective date of the AD.
However, the commenter acknowledges
that the 2,500-flight-hour compliance
time should be sufficient for the 12 U.S.registered airplanes to receive the
required inspection. The commenter
notes that revising the compliance time
would allow the proposed inspection to
be accomplished during a regularly
scheduled C-check. The commenter
notes that it has no affected airplanes in
its fleet. The commenter also states that,
based on its experience, replacing the
RAT would take about 3 hours.
We do not concur with the
commenter’s request to revise the
compliance time. In developing an
appropriate compliance time for this
AD, we considered the manufacturer’s
recommendation; the recommendation
´ ´
of the Direction Generale de l’Aviation
Civile, which is the airworthiness
authority for France; the degree of
urgency associated with the subject
unsafe condition; the average utilization
of the affected fleet; the maintenance
schedules of the majority of affected
operators; and the time necessary to
perform the inspection (1 work hour). In
light of all of these factors, we find that
a 2,500-flight-hour compliance time
represents an appropriate interval of
E:\FR\FM\22JYR1.SGM
22JYR1
42268
Federal Register / Vol. 70, No. 140 / Friday, July 22, 2005 / Rules and Regulations
corrective action would be required—
regardless of AD direction—to correct
an unsafe condition identified in an
airplane and to ensure that the airplane
is operated in an airworthy condition, as
required by the Federal Aviation
Regulations. We have not changed the
AD in this regard.
time for affected airplanes to continue to
operate without compromising safety.
We have determined that this
compliance time will also allow the
majority of affected operators to comply
with the requirements of this AD at a
scheduled maintenance visit. We have
not changed the AD in this regard.
We acknowledge the commenter’s
estimate that replacing the RAT would
take about 3 hours. However, the
economic analysis of an AD is limited
to the cost of actions that are actually
required. The economic analysis does
not consider the costs of conditional
actions, such as replacing the RAT if
damage found during the required
inspection exceeds the limits specified
in the Airbus A300–600 Component
Maintenance Manual. Such conditional
Explanation of Change to Applicability
We have revised the applicability of
this AD to identify model designations
as published in the most recent type
certificate data sheet for the affected
models.
Explanation of Additional Change to
Final Rule
We have revised paragraph (f) of this
AD to correct a typographical error. (In
one place, the proposed AD contained
the term ‘‘RAMs’’ instead of ‘‘RATs.’’)
Conclusion
We have carefully reviewed the
available data, including the comment
that was submitted, 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
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Inspection ..........................................
Rework binding .................................
1
1
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:
VerDate jul<14>2003
15:02 Jul 21, 2005
Average
labor rate
per hour
Work
hours
Action
Jkt 205001
$65
65
None required ..................................
None required ..................................
(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:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
I
PO 00000
Frm 00016
Cost per
airplane
Parts
Fmt 4700
Sfmt 4700
$65
65
Number
of U.S.registered
airplanes
12
12
Fleet cost
$780
780
2005–15–05 Airbus: Amendment 39–14194.
Docket No. FAA–2005–20867;
Directorate Identifier 2004–NM–188–AD.
Effective Date
(a) This AD becomes effective August 26,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300
B4–601, B4–603, B4–620, B4–622, B4–605R,
B4–622R, F4–605R, F4–622R, and C4–605R
Variant F airplanes; certificated in any
category; having serial numbers 0812, 0813,
0815 through 0818 inclusive, 0821 through
0828 inclusive, and 0836 through 0838
inclusive.
Unsafe Condition
(d) This AD was prompted by reports of
holes in the ram air turbine (RAT) hub. We
are issuing this AD to prevent a hole in the
RAT hub cover. A hole in the RAT hub cover
could allow water to enter the RAT governing
mechanism, freeze during flight, and jam the
governing mechanism. In addition, the metal
particles that result from chafing between the
hydraulic flexible hose and the RAT could
mix with the lubricant grease and degrade
the governing mechanism. In an emergency,
a jammed or degraded RAT could result in
failure of RAT deployment, loss of hydraulic
pressure or electrical power to the airplane,
and consequent reduced controllability of the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
E:\FR\FM\22JYR1.SGM
22JYR1
Federal Register / Vol. 70, No. 140 / Friday, July 22, 2005 / Rules and Regulations
the compliance times specified, unless the
actions have already been done.
Inspection and Related Investigative/
Corrective Actions
(f) Within 2,500 flight hours after the
effective date of this AD: Do a one-time
detailed inspection for evidence of chafing
between the hydraulic flexible hose and the
RAT hub, and any applicable related
investigative and corrective actions, by
accomplishing all of the applicable actions
specified in the Accomplishment
Instructions of Airbus Service Bulletin A300–
29–6054, Revision 01, excluding Appendix
01, dated November 4, 2004. Any applicable
corrective actions must be accomplished
before further flight. Although the service
bulletin specifies to submit certain
information to the manufacturer, and to
submit damaged RATs to the vendor or a
repair station, this AD does not include those
requirements.
Note 1: 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.’’
Actions Accomplished Previously
(g) Actions accomplished before the
effective date of this AD, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A300–29–6054, excluding
Appendix 01, dated June 8, 2004, are
acceptable for compliance with the
corresponding actions specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
Related Information
(i) French airworthiness directive F–2004–
133, dated August 4, 2004, also addresses the
subject of this AD.
Material Incorporated by Reference
(j) You must use Airbus Service Bulletin
A300–29–6054, Revision 01, excluding
Appendix 01, dated November 4, 2004, 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 this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get copies of the service
information, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France. To view the AD docket, go to the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street SW., room PL–401, Nassif Building,
Washington, DC. To review copies of the
service information, go to the National
Archives and Records Administration
VerDate jul<14>2003
15:02 Jul 21, 2005
Jkt 205001
(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 July 11,
2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–14173 Filed 7–21–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20690; Directorate
Identifier 2003–NM–230–AD; Amendment
39–14195; AD 2005–15–06]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–200C and 747–200F Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 747–200C and 747–200F
series airplanes. This AD requires onetime inspections for cracks and material
loss in the fuselage skin above the
stringer (STR) 23 lap splice, between
Body Station (BS) 282 and BS 298, and
repair if necessary. This AD is prompted
by a report of a crack above the STR 23
lap splice on one airplane. We are
issuing this AD to detect and correct
cracks or material loss in the fuselage
skin, and consequent reduced structural
integrity of the skin panel, which could
result in rapid depressurization of the
airplane.
This AD becomes effective
August 26, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of August 26, 2005.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the 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
DATES:
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
42269
Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the U.S. Department of Transportation,
400 Seventh Street SW., room PL–401,
Washington, DC. This docket number is
FAA–2005–20690; the directorate
identifier for this docket is 2003–NM–
230–AD.
FOR FURTHER INFORMATION CONTACT: Nick
Kusz, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6432;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Boeing Model 747–
200C and 747–200F series airplanes.
That action, published in the Federal
Register on March 23, 2005 (70 FR
14587), proposed to require one-time
inspections for cracks and material loss
in the fuselage skin above the stringer
(STR) 23 lap splice, between Body
Station (BS) 282 and BS 298, and repair
if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comment that has been
submitted on the proposed AD.
Request To Re-Evaluate Need for the
Proposed Rule
One commenter, an airplane operator,
notes that it has previously inspected
the fuselage skin thickness at the
affected area on two of its ten
production freighter airplanes. The
inspections, which the commenter
points out were conducted at the
manufacturer’s recommendation,
showed skin thickness of 0.060 inch or
greater on both airplanes. The
commenter asserts that our justification
for adopting the proposed AD should
cite the results of its inspections and
any similar inspections conducted at the
manufacturer’s request by other
operators; and notes that Boeing Special
Attention Service Bulletin 747–53–
2493, dated July 3, 2003, cites only one
instance of the problem that is
prompting the proposed AD. The
commenter acknowledges the
significance of fuselage skin cracking,
and recognizes the fact that the
maintenance program for the affected
Model 747–200C and 747–200F series
airplanes includes external visual
inspections of the affected area at
regular intervals. However, the
commenter questions our justification
for adopting the proposed AD.
E:\FR\FM\22JYR1.SGM
22JYR1
]]>Agencies
[Federal Register Volume 70, Number 140 (Friday, July 22, 2005)]
[Rules and Regulations]
[Pages 42267-42269]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-141]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20867; Directorate Identifier 2004-NM-188-AD;
Amendment 39-14194; AD 2005-15-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and
F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes
(Collectively Called A300-600 Series Airplanes)
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Airbus Model A300-600 series airplanes. This AD requires an
inspection for evidence of chafing between the hydraulic flexible hose
and the ram air turbine (RAT) hub, and related investigative and
corrective actions if necessary. This AD is prompted by reports of
holes in the RAT hub cover. We are issuing this AD to prevent a hole in
the RAT hub cover. A hole in the RAT hub cover could allow water to
enter the RAT governing mechanism, freeze during flight, and jam the
governing mechanism. In addition, the metal particles that result from
chafing between the hydraulic flexible hose and the RAT could mix with
the lubricant grease and degrade the governing mechanism. In an
emergency, a jammed or degraded RAT could result in its failure to
deploy, loss of hydraulic pressure or electrical power to the airplane,
and consequent reduced controllability of the airplane.
DATES: This AD becomes effective August 26, 2005.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of August
26, 2005.
ADDRESSES: For service information identified in this AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the 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 U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401,
Washington, DC. This docket number is FAA-2005-20867; the directorate
identifier for this docket is 2004-NM-188-AD.
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: The FAA proposed to amend 14 CFR part 39
with an AD for certain Airbus Model A300 B4-600, B4-600R, and F4-600R
series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called A300-600 series airplanes). That action, published
in the Federal Register on April 6, 2005 (70 FR 17340), proposed to
require an inspection for evidence of chafing between the hydraulic
flexible hose and the ram air turbine (RAT) hub, and related
investigative and corrective actions if necessary.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comment that was
submitted on the proposed AD.
Request To Revise Compliance Time
The commenter requests that the compliance time be revised from the
proposed 2,500 flight hours after the effective date of the AD to 15
months after the effective date of the AD. However, the commenter
acknowledges that the 2,500-flight-hour compliance time should be
sufficient for the 12 U.S.-registered airplanes to receive the required
inspection. The commenter notes that revising the compliance time would
allow the proposed inspection to be accomplished during a regularly
scheduled C-check. The commenter notes that it has no affected
airplanes in its fleet. The commenter also states that, based on its
experience, replacing the RAT would take about 3 hours.
We do not concur with the commenter's request to revise the
compliance time. In developing an appropriate compliance time for this
AD, we considered the manufacturer's recommendation; the recommendation
of the Direction G[eacute]n[eacute]rale de l'Aviation Civile, which is
the airworthiness authority for France; the degree of urgency
associated with the subject unsafe condition; the average utilization
of the affected fleet; the maintenance schedules of the majority of
affected operators; and the time necessary to perform the inspection (1
work hour). In light of all of these factors, we find that a 2,500-
flight-hour compliance time represents an appropriate interval of
[[Page 42268]]
time for affected airplanes to continue to operate without compromising
safety. We have determined that this compliance time will also allow
the majority of affected operators to comply with the requirements of
this AD at a scheduled maintenance visit. We have not changed the AD in
this regard.
We acknowledge the commenter's estimate that replacing the RAT
would take about 3 hours. However, the economic analysis of an AD is
limited to the cost of actions that are actually required. The economic
analysis does not consider the costs of conditional actions, such as
replacing the RAT if damage found during the required inspection
exceeds the limits specified in the Airbus A300-600 Component
Maintenance Manual. Such conditional corrective action would be
required--regardless of AD direction--to correct an unsafe condition
identified in an airplane and to ensure that the airplane is operated
in an airworthy condition, as required by the Federal Aviation
Regulations. We have not changed the AD in this regard.
Explanation of Change to Applicability
We have revised the applicability of this AD to identify model
designations as published in the most recent type certificate data
sheet for the affected models.
Explanation of Additional Change to Final Rule
We have revised paragraph (f) of this AD to correct a typographical
error. (In one place, the proposed AD contained the term ``RAMs''
instead of ``RATs.'')
Conclusion
We have carefully reviewed the available data, including the
comment that was submitted, 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
The following table provides the estimated costs for U.S. operators
to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Work Average Cost per U.S.-
Action hours labor rate Parts airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Inspection..................... 1 $65 None required..... $65 12 $780
Rework binding................. 1 65 None required..... 65 12 780
----------------------------------------------------------------------------------------------------------------
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. 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 adding the following new airworthiness
directive (AD):
2005-15-05 Airbus: Amendment 39-14194. Docket No. FAA-2005-20867;
Directorate Identifier 2004-NM-188-AD.
Effective Date
(a) This AD becomes effective August 26, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620,
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F
airplanes; certificated in any category; having serial numbers 0812,
0813, 0815 through 0818 inclusive, 0821 through 0828 inclusive, and
0836 through 0838 inclusive.
Unsafe Condition
(d) This AD was prompted by reports of holes in the ram air
turbine (RAT) hub. We are issuing this AD to prevent a hole in the
RAT hub cover. A hole in the RAT hub cover could allow water to
enter the RAT governing mechanism, freeze during flight, and jam the
governing mechanism. In addition, the metal particles that result
from chafing between the hydraulic flexible hose and the RAT could
mix with the lubricant grease and degrade the governing mechanism.
In an emergency, a jammed or degraded RAT could result in failure of
RAT deployment, loss of hydraulic pressure or electrical power to
the airplane, and consequent reduced controllability of the
airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within
[[Page 42269]]
the compliance times specified, unless the actions have already been
done.
Inspection and Related Investigative/Corrective Actions
(f) Within 2,500 flight hours after the effective date of this
AD: Do a one-time detailed inspection for evidence of chafing
between the hydraulic flexible hose and the RAT hub, and any
applicable related investigative and corrective actions, by
accomplishing all of the applicable actions specified in the
Accomplishment Instructions of Airbus Service Bulletin A300-29-6054,
Revision 01, excluding Appendix 01, dated November 4, 2004. Any
applicable corrective actions must be accomplished before further
flight. Although the service bulletin specifies to submit certain
information to the manufacturer, and to submit damaged RATs to the
vendor or a repair station, this AD does not include those
requirements.
Note 1: 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.''
Actions Accomplished Previously
(g) Actions accomplished before the effective date of this AD,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-29-6054, excluding Appendix 01, dated June 8, 2004,
are acceptable for compliance with the corresponding actions
specified in this AD.
Alternative Methods of Compliance (AMOCs)
(h) The Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA, has the authority to approve AMOCs for
this AD, if requested in accordance with the procedures found in 14
CFR 39.19.
Related Information
(i) French airworthiness directive F-2004-133, dated August 4,
2004, also addresses the subject of this AD.
Material Incorporated by Reference
(j) You must use Airbus Service Bulletin A300-29-6054, Revision
01, excluding Appendix 01, dated November 4, 2004, 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 this document in accordance with 5
U.S.C. 552(a) and 1 CFR part 51. To get copies of the service
information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France. To view the AD docket, go to the Docket
Management Facility, U.S. Department of Transportation, 400 Seventh
Street SW., room PL-401, Nassif Building, Washington, DC. To review
copies of the service information, go to 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 July 11, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-14173 Filed 7-21-05; 8:45 am]
BILLING CODE 4910-13-P
