Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes, 17591-17594 [05-6685]
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Federal Register / Vol. 70, No. 66 / Thursday, April 7, 2005 / Rules and Regulations
17591
products identified in this rulemaking
action.
any category, as identified in Boeing Service
Bulletin 777–25–0217, dated July 17, 2003.
code_of_federal_regulations/
ibr_locations.html.
Regulatory Findings
Unsafe Condition
(d) This AD was prompted by a report that
tie-down fitting studs were found damaged.
We are issuing this AD to prevent a galley,
purser work station, or closet from detaching
from the tie-down fitting studs during an
emergency landing, which could injure
passengers or crewmembers, or obstruct
escape routes and impede emergency
evacuation.
Issued in Renton, Washington, on March
24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–6684 Filed 4–6–05; 8:45 am]
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
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
2005–07–16 Boeing: Amendment 39–14040.
Docket No. FAA–2005–20026;
Directorate Identifier 2004–NM–150–AD.
Effective Date
(a) This AD becomes effective May 12,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767–
400ER series airplanes, certificated in any
category, having Variable Numbers VQ071
through VQ076 inclusive; and Model 777–
200 and –300 series airplanes, certificated in
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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.
Replacement
(f) Within 60 months after the effective
date of this AD: Replace, with new parts, the
existing tie-down fitting studs that secure
galleys, purser work stations, and floormounted closets to the seat tracks, by doing
all of the actions specified in the
Accomplishment Instructions of Boeing
Service Bulletin 767–25–0338, dated October
9, 2003 (for Boeing Model 767–400ER series
airplanes); or Boeing Service Bulletin 777–
25–0217, dated July 17, 2003 (for Boeing
Model 777–200 and –300 series airplanes); as
applicable.
Replacements Accomplished According to
Previous Issue of Service Bulletin
(g) For Boeing Model 777–200 and –300
series airplanes: Replacements accomplished
before the effective date of this AD according
to Boeing Service Bulletin 777–25–0217,
dated July 18, 2002, are considered
acceptable for compliance with the
corresponding action specified in this AD.
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
Material Incorporated by Reference
(i) You must use Boeing Service Bulletin
767–25–0338, dated October 9, 2003; or
Boeing Service Bulletin 777–25–0217, dated
July 17, 2003; 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. To get copies of
the service information, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207. 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/
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19762; Directorate
Identifier 2004–NM–168–AD; Amendment
39–14038; AD 2005–07–14]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320, and A321 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 all
Airbus Model A318, A319, A320, and
A321 series airplanes. This AD requires
an inspection of the spoiler servo
control for certain part numbers, and
corrective action if necessary. This AD
is prompted by a report of a broken
piston rod bearing of the spoiler servo
control. We are issuing this AD to
prevent breakage of the piston rod
bearing, which could cause loss of the
associated hydraulic system and spoiler
extension, and could result in reduced
controllability of the airplane.
DATES: This AD becomes effective May
12, 2005.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of May 12, 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,
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17592
Federal Register / Vol. 70, No. 66 / Thursday, April 7, 2005 / Rules and Regulations
Washington, DC. This docket number is
FAA–2004–19762; the directorate
identifier for this docket is 2004–NM–
168–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 all Airbus Model A318, A319,
A320, and A321 series airplanes. That
action, published in the Federal
Register on December 7, 2004 (69 FR
70568), proposed to require an
inspection of the spoiler servo control
for certain part numbers and corrective
action if necessary.
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.
Request To Change Applicability
One commenter asks that the
applicability statement in the proposed
AD be changed. The commenter states
that, as written, the applicability does
not limit the effectivity, but instead
applies to every Model A318, A319,
A320, and A321 series airplane
previously delivered or that is yet to be
delivered. The commenter adds that the
proposed visual inspection would have
to be done regardless of the documented
status of the spoiler servo controls,
which introduces unnecessary
maintenance activity. The commenter
notes that paragraph (j) of the proposed
AD prohibits installation of an affected
spoiler servo control on any airplane;
therefore, the applicability statement
could be altered to limit the effectivity
to those airplanes affected by the service
bulletins referenced therein. The
commenter states that limiting the
applicability would apply if supporting
documentation is provided which
verifies that no spoiler servo control has
been changed before the effective date of
the AD. The commenter adds that this
change would provide assurance that all
affected spoiler servo controls are
removed from service and would also
eliminate unnecessary maintenance
activity. The commenter operates 148
Model A319 and A320 series airplanes,
but of those airplanes, only one spoiler
servo control is affected. The
commenter states that the applicability
statement, as written, would require that
the general visual inspection be done on
all 148 airplanes. In conclusion, the
commenter states that the applicability
should be limited to Model A318, A319,
A320, and A321 series airplanes, all
certified models, all serial numbers, on
which Goodrich spoiler actuators with
part number (P/N) 31077–050, –060,
–070, –110, or –112 are installed.
We do not agree to change the
applicability identified in the proposed
AD. As specified in the Differences
section of the proposed AD, ‘‘French
airworthiness directive F–2004–122,
dated July 21, 2004, has an effectivity of
‘AIRBUS A318, A319, A320 and A321
aircraft, all certified models, all serials
numbers, fitted with GOODRICH spoiler
actuators P/N 31077–050, –060, –070,
–110 or –112.’ However, because spoiler
actuators are interchangeable on Airbus
Model A318, A319, A320, and A321
series airplanes, airplanes not fitted
with the spoiler actuators P/N 31077–
050, –060, –070, –110 or –112 may have
a spoiler actuator P/N 31077–050, –060,
–070, –110 or –112 installed in the
future by operators during normal
maintenance. Therefore, the
applicability of this proposed AD
includes all Airbus Model A318, A319,
A320, and A321 series airplanes. Both
the proposed AD and French
airworthiness directive require an
inspection for the part number of the
spoiler actuator (spoiler servo control).’’
We do agree to allow a review of the
airplane maintenance records instead of
accomplishing the Phase 1 or Phase 2
inspection. We have changed
paragraphs (f) and (g) of this final rule
to allow a review of the airplane
maintenance records to determine the
part number of the spoiler servo
controls. However, if the part number
cannot be positively identified from the
records review, the inspection will need
to be done.
Request To Reference New Service
Information
One commenter asks that Airbus
Service Bulletins A320–27–1158 and
A320–27–1159; both Revision 01; both
dated September 3, 2004; be included as
the sources of service information for
accomplishing the inspections in the
proposed AD. The original issues of
those service bulletins were referenced
as the appropriate sources of service
information for accomplishing the
actions specified in the proposed AD.
We agree with the commenter’s
request. We have added Revision 01,
which is the most current source of
service information for the actions in
this AD, to this final rule as the source
of service information for accomplishing
those actions. Revision 01 adds no
further work to the original issues of the
service bulletin; operators are merely
informed that the revised service
bulletins are mandatory. We have also
added a new paragraph (i) to this final
rule which allows credit for actions
done in accordance with the original
issue of the service bulletins. We have
re-identified subsequent paragraphs
accordingly.
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
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
Action
Work
hours
Average
labor rate
per hour
Cost per
airplane
Number of
U.S.registered
airplanes
Inspection .....................................................................................
3–5
$65
$195–$325
648
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
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Fleet cost
$126,360–$210,600
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
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Federal Register / Vol. 70, No. 66 / Thursday, April 7, 2005 / Rules and Regulations
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
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
2005–07–14 Airbus: Amendment 39–14038.
Docket No. FAA–2004–19762; Directorate
Identifier 2004–NM–168–AD.
Effective Date
(a) This AD becomes effective May 12,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model
A318, A319, A320, and A321 series
airplanes; certificated in any category.
Unsafe Condition
(d) This AD was prompted by a report of
a broken piston rod bearing of the spoiler
17593
servo control. We are issuing this AD to
prevent breakage of the piston rod bearing,
which could cause loss of the associated
hydraulic system and spoiler extension, and
could result in reduced controllability 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.
Phase 1 Inspection or Review of
Maintenance Records
(f) Within 12 months after the effective
date of this AD, do a general visual
inspection for the part number (P/N) of the
spoiler servo control at the applicable
locations specified in Table 1 of this AD, in
accordance with Airbus Service Bulletin
A320–27–1158, Revision 01, excluding
Appendices 01 and 02, dated September 3,
2004. Instead of inspecting the spoiler servo
control, a review of the airplane maintenance
records is acceptable if the P/N of the spoiler
servo control can be conclusively determined
from that review.
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 normal 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.’’
TABLE 1.—PHASE 1 SPOILER SERVO CONTROL INSPECTION
For airbus model—
Inspect spoiler servo controls at—
A318 and A319 series airplanes ..............................................................
A320 series airplanes ...............................................................................
A321 series airplanes ...............................................................................
Positions 2, 3, 4, and 5.
Position 2.
Positions 2, 3, and 4.
Phase 2 Inspection or Review of
Maintenance Records
(g) Within 30 months after the effective
date of this AD, do a general visual
inspection for the P/N of the spoiler servo
control at the applicable locations specified
in Table 2 of this AD, in accordance with
Airbus Service Bulletin A320–27–1159,
Revision 01, excluding Appendices 01 and
02, dated September 3, 2004. Instead of
inspecting the spoiler servo control, a review
of the airplane maintenance records is
acceptable if the P/N of the spoiler servo
control can be conclusively determined from
that review.
TABLE 2.—PHASE 2 SPOILER SERVO CONTROL INSPECTION
For airbus model—
Inspect spoiler servo controls at—
A318 and A319 series airplanes ..............................................................
A320 series airplanes on which Airbus modification 26335 and Airbus
Service Bulletin A320–27–1115, dated October 27, 1997; and Revision 01, dated June 22, 1999; has not been done.
A320 series airplanes on which Airbus modification 26335 or Airbus
Service Bulletin A320–27–1115, dated October 27, 1997; or Revision
01, dated June 22, 1999; has been done.
A321 series airplanes ...............................................................................
Position 1.
Positions 1 and 3.
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Positions 1, 3, 4, and 5.
Positions 1 and 5.
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17594
Federal Register / Vol. 70, No. 66 / Thursday, April 7, 2005 / Rules and Regulations
Corrective Action
(h) If, during any inspection specified in
paragraph (f) or (g) of this AD, P/N 31077–
050, –060, –070, –110, or –112 is found or
if unable to determine the P/N, before further
flight, replace the spoiler servo control with
a new or modified spoiler servo control, in
accordance with Airbus Service Bulletin
A320–27–1158 or A320–27–1159; both
Revision 01; both excluding Appendices 01
and 02; both dated September 3, 2004; as
applicable.
Note 2: Airbus Service Bulletins A320–27–
1158, Revision 01; and A320–27–1159,
Revision 01; refer to Goodrich Service
Bulletin 31077–27–14, dated May 24, 2004;
as an additional source of service information
for modifying the spoiler servo control.
Actions Accomplished Per Previous Issues of
Service Information
(i) Actions accomplished before the
effective date of this AD in accordance with
Airbus Service Bulletin A320–27–1158; or
Airbus Service Bulletin A320–27–1159; both
excluding Appendices 01 and 02; both dated
May 26, 2004; are considered acceptable for
compliance with the corresponding actions
required by this AD.
Reporting Not Required
(j) Although Airbus Service Bulletin A320–
27–1158, Revision 01, dated September 3,
2004; and Airbus Service Bulletin A320–27–
1159, Revision 01, dated September 3, 2004;
specify to submit certain information to the
manufacturer, this AD does not include that
requirement.
Parts Installation
(k) As of the effective date of this AD, no
person may install a spoiler servo control, P/
N 31077–050, –060, –070, –110, or –112, on
any airplane, unless it has been modified
according to Airbus Service Bulletin A320–
27–1158 or A320–27–1159; both Revision 01;
both excluding Appendices 01 and 02; both
dated September 3, 2004.
Alternative Methods of Compliance
(AMOCs)
(l) 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
(m) French airworthiness directive F–
2004–122, dated July 21, 2004, also addresses
the subject of this AD.
Material Incorporated by Reference
(n) You must use Airbus Service Bulletin
A320–27–1158, Revision 01, excluding
Appendices 01 and 02, dated September 3,
2004; and Airbus Service Bulletin A320–27–
1159, Revision 01, excluding Appendices 01
and 02, dated September 3, 2004; 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. To
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20:15 Apr 06, 2005
Jkt 205001
get copies of the service information, go to
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), 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 March
24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–6685 Filed 4–6–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20222; Directorate
Identifier 2004–NM–230–AD; Amendment
39–14041; AD 2005–07–17]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–102, –103, –106, –201,
–202, –301, –311, and –315 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
Bombardier Model DHC–8–102, –103,
–106, –201, –202, –301, –311, and–315
airplanes. This AD requires revising the
airplane flight manual to include
applicable procedures to follow when
the flightcrew receives abnormal
indications of airspeed, altitude, or
vertical airspeed. This AD also requires
modifying the static system. This AD is
prompted by a report of a leak in the
static pressure system, which could
result in loss of the static systems and
consequent erroneous data displayed on
the pilot’s flight instruments. We are
issuing this AD to advise the flightcrew
of applicable procedures in the event of
abnormal indications of airspeed,
altitude, or vertical airspeed; and to
prevent leaks in the static system, which
could result in the loss of critical flight
information that could result in reduced
controllability of the airplane or
controlled flight into terrain.
DATES: This AD becomes effective May
12, 2005.
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The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of May 12, 2005.
ADDRESSES: For service information
identified in this AD, contact
Bombardier, Inc., Bombardier Regional
Aircraft Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
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–2005–20222; the directorate
identifier for this docket is 2004–NM–
230–AD.
FOR FURTHER INFORMATION CONTACT: Ezra
Sasson, Aerospace Engineer, Systems
and Flight Test Branch, ANE–172, FAA,
New York Aircraft Certification Office,
1600 Stewart Avenue, suite 410,
Westbury, New York 11590; telephone
(516) 228–7320; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Bombardier Model
DHC–8–102, –103, –106, –201, –202,
–301, –311, and –315 airplanes. That
action, published in the Federal
Register on February 1, 2005 (70 FR
5078), proposed to require revising the
airplane flight manual (AFM) to include
applicable procedures to follow when
the flightcrew receives abnormal
indications of airspeed, altitude, or
vertical airspeed. That action also
proposed to require modifying the static
system.
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been submitted on the proposed
AD or on the determination of the cost
to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
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]]>Agencies
[Federal Register Volume 70, Number 66 (Thursday, April 7, 2005)]
[Rules and Regulations]
[Pages 17591-17594]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6685]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19762; Directorate Identifier 2004-NM-168-AD;
Amendment 39-14038; AD 2005-07-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320, and A321
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 all
Airbus Model A318, A319, A320, and A321 series airplanes. This AD
requires an inspection of the spoiler servo control for certain part
numbers, and corrective action if necessary. This AD is prompted by a
report of a broken piston rod bearing of the spoiler servo control. We
are issuing this AD to prevent breakage of the piston rod bearing,
which could cause loss of the associated hydraulic system and spoiler
extension, and could result in reduced controllability of the airplane.
DATES: This AD becomes effective May 12, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of May
12, 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,
[[Page 17592]]
Washington, DC. This docket number is FAA-2004-19762; the directorate
identifier for this docket is 2004-NM-168-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 all Airbus Model A318, A319, A320, and A321 series
airplanes. That action, published in the Federal Register on December
7, 2004 (69 FR 70568), proposed to require an inspection of the spoiler
servo control for certain part numbers and corrective action if
necessary.
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.
Request To Change Applicability
One commenter asks that the applicability statement in the proposed
AD be changed. The commenter states that, as written, the applicability
does not limit the effectivity, but instead applies to every Model
A318, A319, A320, and A321 series airplane previously delivered or that
is yet to be delivered. The commenter adds that the proposed visual
inspection would have to be done regardless of the documented status of
the spoiler servo controls, which introduces unnecessary maintenance
activity. The commenter notes that paragraph (j) of the proposed AD
prohibits installation of an affected spoiler servo control on any
airplane; therefore, the applicability statement could be altered to
limit the effectivity to those airplanes affected by the service
bulletins referenced therein. The commenter states that limiting the
applicability would apply if supporting documentation is provided which
verifies that no spoiler servo control has been changed before the
effective date of the AD. The commenter adds that this change would
provide assurance that all affected spoiler servo controls are removed
from service and would also eliminate unnecessary maintenance activity.
The commenter operates 148 Model A319 and A320 series airplanes, but of
those airplanes, only one spoiler servo control is affected. The
commenter states that the applicability statement, as written, would
require that the general visual inspection be done on all 148
airplanes. In conclusion, the commenter states that the applicability
should be limited to Model A318, A319, A320, and A321 series airplanes,
all certified models, all serial numbers, on which Goodrich spoiler
actuators with part number (P/N) 31077-050, -060, -070, -110, or -112
are installed.
We do not agree to change the applicability identified in the
proposed AD. As specified in the Differences section of the proposed
AD, ``French airworthiness directive F-2004-122, dated July 21, 2004,
has an effectivity of `AIRBUS A318, A319, A320 and A321 aircraft, all
certified models, all serials numbers, fitted with GOODRICH spoiler
actuators P/N 31077-050, -060, -070, -110 or -112.' However, because
spoiler actuators are interchangeable on Airbus Model A318, A319, A320,
and A321 series airplanes, airplanes not fitted with the spoiler
actuators P/N 31077-050, -060, -070, -110 or -112 may have a spoiler
actuator P/N 31077-050, -060, -070, -110 or -112 installed in the
future by operators during normal maintenance. Therefore, the
applicability of this proposed AD includes all Airbus Model A318, A319,
A320, and A321 series airplanes. Both the proposed AD and French
airworthiness directive require an inspection for the part number of
the spoiler actuator (spoiler servo control).''
We do agree to allow a review of the airplane maintenance records
instead of accomplishing the Phase 1 or Phase 2 inspection. We have
changed paragraphs (f) and (g) of this final rule to allow a review of
the airplane maintenance records to determine the part number of the
spoiler servo controls. However, if the part number cannot be
positively identified from the records review, the inspection will need
to be done.
Request To Reference New Service Information
One commenter asks that Airbus Service Bulletins A320-27-1158 and
A320-27-1159; both Revision 01; both dated September 3, 2004; be
included as the sources of service information for accomplishing the
inspections in the proposed AD. The original issues of those service
bulletins were referenced as the appropriate sources of service
information for accomplishing the actions specified in the proposed AD.
We agree with the commenter's request. We have added Revision 01,
which is the most current source of service information for the actions
in this AD, to this final rule as the source of service information for
accomplishing those actions. Revision 01 adds no further work to the
original issues of the service bulletin; operators are merely informed
that the revised service bulletins are mandatory. We have also added a
new paragraph (i) to this final rule which allows credit for actions
done in accordance with the original issue of the service bulletins. We
have re-identified subsequent paragraphs accordingly.
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 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 airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Inspection......................... 3-5 $65 $195-$325 648 $126,360-$210,600
----------------------------------------------------------------------------------------------------------------
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.
[[Page 17593]]
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):
2005-07-14 Airbus: Amendment 39-14038. Docket No. FAA-2004-19762;
Directorate Identifier 2004-NM-168-AD.
Effective Date
(a) This AD becomes effective May 12, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Airbus Model A318, A319, A320, and
A321 series airplanes; certificated in any category.
Unsafe Condition
(d) This AD was prompted by a report of a broken piston rod
bearing of the spoiler servo control. We are issuing this AD to
prevent breakage of the piston rod bearing, which could cause loss
of the associated hydraulic system and spoiler extension, and could
result in reduced controllability 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.
Phase 1 Inspection or Review of Maintenance Records
(f) Within 12 months after the effective date of this AD, do a
general visual inspection for the part number (P/N) of the spoiler
servo control at the applicable locations specified in Table 1 of
this AD, in accordance with Airbus Service Bulletin A320-27-1158,
Revision 01, excluding Appendices 01 and 02, dated September 3,
2004. Instead of inspecting the spoiler servo control, a review of
the airplane maintenance records is acceptable if the P/N of the
spoiler servo control can be conclusively determined from that
review.
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 normal 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.''
Table 1.--Phase 1 Spoiler Servo Control Inspection
------------------------------------------------------------------------
Inspect spoiler servo controls
For airbus model-- at--
------------------------------------------------------------------------
A318 and A319 series airplanes......... Positions 2, 3, 4, and 5.
A320 series airplanes.................. Position 2.
A321 series airplanes.................. Positions 2, 3, and 4.
------------------------------------------------------------------------
Phase 2 Inspection or Review of Maintenance Records
(g) Within 30 months after the effective date of this AD, do a
general visual inspection for the P/N of the spoiler servo control
at the applicable locations specified in Table 2 of this AD, in
accordance with Airbus Service Bulletin A320-27-1159, Revision 01,
excluding Appendices 01 and 02, dated September 3, 2004. Instead of
inspecting the spoiler servo control, a review of the airplane
maintenance records is acceptable if the P/N of the spoiler servo
control can be conclusively determined from that review.
Table 2.--Phase 2 Spoiler Servo Control Inspection
------------------------------------------------------------------------
Inspect spoiler servo controls
For airbus model-- at--
------------------------------------------------------------------------
A318 and A319 series airplanes......... Position 1.
A320 series airplanes on which Airbus Positions 1 and 3.
modification 26335 and Airbus Service
Bulletin A320-27-1115, dated October
27, 1997; and Revision 01, dated June
22, 1999; has not been done.
A320 series airplanes on which Airbus Positions 1, 3, 4, and 5.
modification 26335 or Airbus Service
Bulletin A320-27-1115, dated October
27, 1997; or Revision 01, dated June
22, 1999; has been done.
A321 series airplanes.................. Positions 1 and 5.
------------------------------------------------------------------------
[[Page 17594]]
Corrective Action
(h) If, during any inspection specified in paragraph (f) or (g)
of this AD, P/N 31077-050, -060, -070, -110, or -112 is found or if
unable to determine the P/N, before further flight, replace the
spoiler servo control with a new or modified spoiler servo control,
in accordance with Airbus Service Bulletin A320-27-1158 or A320-27-
1159; both Revision 01; both excluding Appendices 01 and 02; both
dated September 3, 2004; as applicable.
Note 2: Airbus Service Bulletins A320-27-1158, Revision 01; and
A320-27-1159, Revision 01; refer to Goodrich Service Bulletin 31077-
27-14, dated May 24, 2004; as an additional source of service
information for modifying the spoiler servo control.
Actions Accomplished Per Previous Issues of Service Information
(i) Actions accomplished before the effective date of this AD in
accordance with Airbus Service Bulletin A320-27-1158; or Airbus
Service Bulletin A320-27-1159; both excluding Appendices 01 and 02;
both dated May 26, 2004; are considered acceptable for compliance
with the corresponding actions required by this AD.
Reporting Not Required
(j) Although Airbus Service Bulletin A320-27-1158, Revision 01,
dated September 3, 2004; and Airbus Service Bulletin A320-27-1159,
Revision 01, dated September 3, 2004; specify to submit certain
information to the manufacturer, this AD does not include that
requirement.
Parts Installation
(k) As of the effective date of this AD, no person may install a
spoiler servo control, P/N 31077-050, -060, -070, -110, or -112, on
any airplane, unless it has been modified according to Airbus
Service Bulletin A320-27-1158 or A320-27-1159; both Revision 01;
both excluding Appendices 01 and 02; both dated September 3, 2004.
Alternative Methods of Compliance (AMOCs)
(l) 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
(m) French airworthiness directive F-2004-122, dated July 21,
2004, also addresses the subject of this AD.
Material Incorporated by Reference
(n) You must use Airbus Service Bulletin A320-27-1158, Revision
01, excluding Appendices 01 and 02, dated September 3, 2004; and
Airbus Service Bulletin A320-27-1159, Revision 01, excluding
Appendices 01 and 02, dated September 3, 2004; 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. To get copies of the service
information, go to 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), 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 March 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-6685 Filed 4-6-05; 8:45 am]
BILLING CODE 4910-13-P
