Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes, 65906-65909 [E7-22925]
Download as PDF
<![CDATA[
65906
Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–0230; Directorate
Identifier 2007–NM–043–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200, A330–300, A340–200, and
A340–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Airbus
Model A330–200, A330–300, A340–200,
and A340–300 series airplanes. The
existing AD currently requires an
accelerated schedule of repetitive
testing of the elevator servo control
loops, and corrective actions if
necessary. This proposed AD would
retain the existing requirements, reduce
the applicability of the existing AD, and
add terminating actions. This proposed
AD results from reports of failed
elevator servo controls due to broken
guides. We are proposing this AD to
prevent failure of the elevator servo
controls during certain phases of
takeoff, which could result in an
unannounced loss of elevator control
and consequent reduced controllability
of the airplane.
DATES: We must receive comments on
this proposed AD by December 26,
2007.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Airbus, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–0230; Directorate Identifier
2007–NM–043–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On October 31, 2005, we issued AD
2005–23–10, amendment 39–14368 (70
FR 69065, November 14, 2005), for all
Airbus Model A330–200, A330–300,
A340–200, and A340–300 series
airplanes. That AD requires an
accelerated schedule of repetitive
testing of the elevator servo control
loops, and corrective actions if
necessary. That AD resulted from
reports of failed elevator servo controls
due to broken guides. We issued that
AD to ensure proper functioning of the
elevator servo controls. Failure of the
elevator servo controls during certain
phases of takeoff could result in an
unannounced loss of elevator control
and consequent reduced controllability
of the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2005–23–10
explains that we consider the
requirements ‘‘interim action’’ and were
considering further rulemaking. We now
have determined that further
rulemaking is indeed necessary, and
this proposed AD follows from that
determination.
Relevant Service Information
Airbus has issued Revision 02 of
Airbus Service Bulletins A330–27–3138
(for Model A330–200 and –300 series
airplanes) and A340–27–4137 (for
Model A340–200 and –300 series
airplanes); both dated May 30, 2006.
These service bulletins supersede,
respectively, Revision 01 of Airbus All
Operator Telexes (AOT) A330–27A3138
and A340–27A4137, both dated October
3, 2005. The AOTs are referenced in AD
2005–23–10 as the appropriate source of
service information for accomplishing
the required testing of the elevator servo
control loops, and corrective actions if
necessary. The procedures specified in
Revision 02 of the service bulletins are
identical to those in Revision 01 of the
AOTs. No additional work is necessary
for airplanes on which the actions
specified in Revision 01 of the
applicable AOT have been done.
Airbus also has issued the following
service bulletins:
SERVICE BULLETINS
ebenthall on PROD1PC69 with PROPOSALS
Airbus service bulletins—
Describe procedures for—
And refer to—
A330–27–3136, Revision 01, dated July 19,
2006 (for Model A330–200 and –300 series
airplanes); and A340–27–4135, dated January 12, 2006 (for Model A340–200 and –300
series airplanes).
Modification of four elevator servo controls by
installing a new plug-guide assembly.
Goodrich Actuation Systems Service Bulletin
SC4800–27–18, Revision 1, dated May 19,
2006, as an additional source of service information for accomplishing the modification.
VerDate Aug<31>2005
15:37 Nov 23, 2007
Jkt 214001
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
E:\FR\FM\26NOP1.SGM
26NOP1
Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
65907
SERVICE BULLETINS—Continued
Airbus service bulletins—
Describe procedures for—
And refer to—
A330–27–3134, Revision 01, dated May 12,
2006 (for Model A330–200 and –300 series
airplanes); and A340–27–4132, dated October 13, 2005 (for Model A340–200 and –300
series airplanes).
Modification of four elevator servo controls by
replacing the o-ring of the solenoid valves
with a new o-ring.
Goodrich Actuation Systems Service Bulletin
SC4800–27–17, Revision 2, dated May 19,
2006, as an additional source of service information for accomplishing the modification.
Accomplishing the modification
specified in the service bulletins
eliminates the need for the repetitive
inspection requirements of AD 2005–
23–10 and is intended to adequately
address the unsafe condition. The
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, mandated the service
information and issued airworthiness
directive 2007–0008, dated January 9,
2007, to ensure the continued
airworthiness of these airplanes in the
European Union.
FAA’s Determination and Requirements
of the Proposed AD
These airplanes are manufactured in
France and are type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. As described
in FAA Order 8100.14A, ‘‘Interim
Procedures for Working with the
European Community on Airworthiness
Certification and Continued
Airworthiness,’’ dated August 12, 2005,
the EASA has kept the FAA informed of
the situation described above. We have
examined the EASA’s findings,
evaluated all pertinent information, and
determined that AD action is necessary
for airplanes of this type design that are
certificated for operation in the United
States.
This proposed AD would supersede
AD 2005–23–10 and would retain the
requirements of the existing AD. This
proposed AD also would require
accomplishing the actions specified in
service information described
previously. Accomplishing the
modification specified in the service
bulletins described previously
eliminates the need for the retained
requirements of 2005–23–10. This
proposed AD also would remove
airplanes from the applicability of the
existing AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators of the
affected Model A330–200 and A330–
300 series airplanes to comply with this
proposed AD.
ESTIMATED COSTS
Average
labor rate
per hour
Work
hour(s)
Action
Inspection (required by
AD 2005–23–10).
Modifications (new proposed actions).
None ...........................
28
$80
The manufacturer
states that it will supply required parts to
the operators at no
cost.
ebenthall on PROD1PC69 with PROPOSALS
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
Jkt 214001
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
proposed AD would not have federalism
implications under Executive Order
PO 00000
Frm 00019
Number of
U.S.-registered airplanes
$80, per inspection
cycle.
$2,240 .........................
$80
Authority for This Rulemaking
15:37 Nov 23, 2007
Cost per airplane
1
Currently, there are no affected Model
A340–200 and A340–300 series
airplanes on the U.S. Register. However,
if an affected airplane is imported and
placed on the U.S. Register in the future,
the proposed modification would take
about 10 work hours, at an average labor
rate of $80 per work hour. The
manufacturer states that it would supply
required parts to the operators at no
cost. Based on these figures, we estimate
the cost of this proposed AD for Model
A340–200 and A340–300 series
airplanes to be $800 per airplane.
VerDate Aug<31>2005
Parts
Fmt 4702
Sfmt 4702
18
18
Fleet cost
$1,440, per inspection
cycle.
$40,320.
13132. This proposed AD would 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 the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
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 proposed AD and placed it in the
E:\FR\FM\26NOP1.SGM
26NOP1
65908
Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
Airbus: Docket No. FAA–2007–0230;
Directorate Identifier 2007–NM–043–AD.
1. The authority citation for part 39
continues to read as follows:
Comments Due Date
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
(a) The FAA must receive comments on
this AD action by December 26, 2007.
Affected ADs
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14368 (70
FR 69065, November 14, 2005) and
adding the following new airworthiness
directive (AD):
(b) This AD supersedes AD 2005–23–10.
Applicability
(c) This AD applies to the airplanes
identified in Table 1 of this AD, certificated
in any category.
TABLE 1.—APPLICABILITY
Airbus model—
Excluding those airplanes on which any of the following—
Has been installed—
A330–200, A330–300, A340–200,
and A340–300 series airplanes.
Airbus modification 54833 .....................................................................
In production.
Airbus Service Bulletin A330–27–3136, Revision 01, dated July 19,
2006.
Airbus Service Bulletin A340–27–4135, dated January 12, 2006 ........
In service.
Unsafe Condition
(d) This AD results from reports of failed
elevator servo controls due to broken guides.
We are proposing this AD to prevent failure
of the elevator servo controls during certain
phases of takeoff, which could result in an
unannounced loss of elevator control and
consequent 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.
Requirements of AD 2005–23–10
Service Information
(f) The term ‘‘AOT,’’ as used in paragraphs
(g) through (i) of this AD, means section 4.2.
‘‘Description’’ of the following service
information, as applicable:
(1) For Model A330–200 and –300 series
airplanes: Airbus All Operators Telex A330–
27A3138, Revision 01, dated October 3, 2005;
and
(2) For Model A340–200 and –300 series
airplanes: Airbus All Operators Telex A340–
27A4137, Revision 01, dated October 3, 2005.
ebenthall on PROD1PC69 with PROPOSALS
Initial and Repetitive Elevator Servo-Loop
Tests
(g) Within 200 flight hours after November
29, 2005 (the effective date of AD 2005–23–
10): Test the elevator servo-loops, in
accordance with the AOT, except as provided
by paragraph (j) of this AD. If the test of the
elevator servo-loops passes, repeat the test at
intervals not to exceed 140 flight hours or 8
days, whichever occurs first.
Failed Tests
(h) If any test of the elevator servo-loops
required by paragraph (g) of this AD fails:
Before further flight, troubleshoot the cause
of the test failure, and do the applicable
corrective actions; in accordance with the
AOT, except as provided by paragraph (j) of
VerDate Aug<31>2005
15:37 Nov 23, 2007
Jkt 214001
this AD. Thereafter, repeat the test at the
times specified in paragraph (g) of this AD.
Reporting Requirement
(i) Following each test required by
paragraph (g) of this AD, submit a report of
the findings of only failed elevator servo-loop
tests to Airbus Customer Services,
Engineering and Technical Support,
Attention: Mr. J. Laurent, SEE53, fax +33/
(0)5.61.93.44.25; at the applicable time
specified in paragraph (i)(1) or (i)(2) of this
AD. The report must include the description
of the failure experienced during the test, the
identified cause of the failure, and the
number of flight hours and flight cycles on
the airplane. Under the provisions of the
Paperwork Reduction Act of 1980 (44 U.S.C.
3501 et seq.), the Office of Management and
Budget (OMB) has approved the information
collection requirements contained in this AD
and has assigned OMB Control Number
2120–0056.
(1) If the test was done after November 29,
2005: Submit the report within 10 days after
the test.
(2) If the test was done prior to November
29, 2005: Submit the report within 10 days
after November 29, 2005.
New Requirements of This AD
New Service Information for Testing
(j) As of the effective date of this AD, do
the actions required by paragraphs (g) and (h)
of this AD in accordance with the
Accomplishment Instructions of the
following service bulletins, as applicable.
(1) For Model A330–200 and –300 series
airplanes: Airbus Service Bulletin A330–27–
3138, Revision 02, dated May 30, 2006; and
(2) For Model A340–200 and –300 series
airplanes: Airbus Service Bulletin A340–27–
4137, Revision 02, dated May 30, 2006.
Terminating Actions
(k) Within 17 months after the effective
date of this AD, modify the four elevator
servo controls in accordance with the
PO 00000
Frm 00020
Fmt 4702
Sfmt 4702
In service.
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3136, Revision 01,
dated July 19, 2006 (for Model A330–200 and
–300 series airplanes); or Airbus Service
Bulletin A340–27–4135, dated January 12,
2006 (for Model A340–200 and –300 series
airplanes); as applicable.
Note 1: Airbus Service Bulletins A330–27–
3136 and A340–27–4135 refer to Goodrich
Actuation Systems Service Bulletin SC4800–
27–18, Revision 1, dated May 19, 2006, as an
additional source of service information for
accomplishing the modification required by
paragraph (k) of this AD.
(l) Modifications done before the effective
date of this AD in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3136, dated
January 12, 2006, are acceptable for
compliance with the modification required
by paragraph (k) of this AD.
(m) Concurrently with the modification
required by paragraph (k) of this AD, modify
the four elevator servo controls in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–27–3134,
Revision 01, dated May 12, 2006 (for Model
A330–200 and –300 series airplanes); or
Airbus Service Bulletin A340–27–4132,
dated October 13, 2005 (for Model A340–200
and –300 series airplanes); as applicable.
Note 2: Airbus Service Bulletins A330–27–
3134 and A340–27–4132 refer to Goodrich
Actuation Systems Service Bulletin SC4800–
27–17, Revision 2, dated May 19, 2006, as an
additional source of service information for
accomplishing the modification required by
paragraph (m) of this AD.
(n) Modifications done before the effective
date of this AD in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3134, dated
October 13, 2005, are acceptable for
compliance with the modification required
by paragraph (m) of this AD.
(o) Accomplishment of the modifications
required by paragraphs (k) and (m) of this AD
constitutes terminating action for the
E:\FR\FM\26NOP1.SGM
26NOP1
Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules
requirements of paragraphs (f) through (i) of
this AD.
Parts Installation
(p) As of the effective date of this AD, no
person may install, on any airplane, an
elevator servo control, unless it has been
modified in accordance with paragraphs (k)
and (m) of this AD.
Alternative Methods of Compliance
(AMOCs)
(q)(1) 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.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(r) EASA airworthiness directive 2007–
0008, dated January 9, 2007, also addresses
the subject of this AD.
Issued in Renton, Washington, on
November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–22925 Filed 11–23–07; 8:45 am]
BILLING CODE 4910–13–P
inspection requirements. This proposed
AD results from reports of cracking due
to fatigue and stress corrosion of the
support fittings of the Krueger flap
actuator. We are proposing this AD to
prevent cracking of the support fittings,
which could result in fracturing of the
actuator attach lugs, separation of the
actuator from the support fitting,
severing of the hydraulic lines, resultant
loss of hydraulic fluids, and consequent
reduced controllability of the airplane.
DATES: We must receive comments on
this proposed AD by January 10, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 737–200 series
airplanes. This proposed AD would
require repetitive inspections to detect
cracking of the support fittings of the
Krueger flap actuators, and corrective
actions if necessary. This proposed AD
also would require eventual
replacement of any existing aluminum
support fitting on each wing with a steel
fitting, and modification of the aft
attachment of the actuator. Doing these
actions would terminate the repetitive
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
14 CFR Part 39
[Docket No. FAA–2007–0228; Directorate
Identifier 2007–NM–107–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–200 Series Airplanes
ebenthall on PROD1PC69 with PROPOSALS
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
VerDate Aug<31>2005
15:37 Nov 23, 2007
Jkt 214001
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2007–0228; Directorate Identifier
PO 00000
Frm 00021
Fmt 4702
Sfmt 4702
65909
2007–NM–107–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We have received reports of cracks in
the support fitting of the Krueger flap
actuator mounted on the front spar of
eight affected airplanes. On one
airplane, the lugs on the No. 1 Krueger
flap actuator support fitting severed
completely, the actuator separated from
the front spar, and the hydraulic lines
were severed. On another airplane, both
actuator attach lugs of a No. 1 flap
support fitting were also completely
severed. The cracking is attributed to
fatigue and stress corrosion, and it is
suspected that high clamp-up stresses
may be contributing to cracks in the
actuator attach lugs. Cracking of the
support fittings, if not corrected, could
result in fracturing of the actuator attach
lugs, separation of the actuator from the
support fitting, severing of the hydraulic
lines, resultant loss of hydraulic fluids,
and consequent reduced controllability
of the airplane.
Other Relevant Rulemaking
On July 31, 2000, we issued AD 2000–
15–18, amendment 39–11851 (65 FR
48371, August 8, 2000). That AD applies
to certain Boeing Model 737–100 and
–200 series airplanes, line numbers 001
through 813 inclusive. That AD requires
inspections to detect cracking of the
support fittings of the Krueger flap
actuator; and, if necessary, replacement
of existing fittings with new steel
fittings and modification of the aft
attachment of the actuator. That AD also
requires eventual replacement of any
existing aluminum Krueger flap actuator
support fitting on each wing with a steel
fitting, which terminates the repetitive
inspection requirements. That AD
resulted from reports of cracking due to
fatigue and stress corrosion of the
support fittings of the Krueger flap
actuator. The actions in that AD are
intended to prevent such cracking,
which could result in fracturing of the
actuator attach lugs, separation of the
actuator from the support fitting,
severing of the hydraulic lines, and
E:\FR\FM\26NOP1.SGM
26NOP1
]]>Agencies
[Federal Register Volume 72, Number 226 (Monday, November 26, 2007)]
[Proposed Rules]
[Pages 65906-65909]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22925]
[[Page 65906]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-0230; Directorate Identifier 2007-NM-043-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
200, and A340-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Airbus Model A330-200, A330-300,
A340-200, and A340-300 series airplanes. The existing AD currently
requires an accelerated schedule of repetitive testing of the elevator
servo control loops, and corrective actions if necessary. This proposed
AD would retain the existing requirements, reduce the applicability of
the existing AD, and add terminating actions. This proposed AD results
from reports of failed elevator servo controls due to broken guides. We
are proposing this AD to prevent failure of the elevator servo controls
during certain phases of takeoff, which could result in an unannounced
loss of elevator control and consequent reduced controllability of the
airplane.
DATES: We must receive comments on this proposed AD by December 26,
2007.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0230;
Directorate Identifier 2007-NM-043-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On October 31, 2005, we issued AD 2005-23-10, amendment 39-14368
(70 FR 69065, November 14, 2005), for all Airbus Model A330-200, A330-
300, A340-200, and A340-300 series airplanes. That AD requires an
accelerated schedule of repetitive testing of the elevator servo
control loops, and corrective actions if necessary. That AD resulted
from reports of failed elevator servo controls due to broken guides. We
issued that AD to ensure proper functioning of the elevator servo
controls. Failure of the elevator servo controls during certain phases
of takeoff could result in an unannounced loss of elevator control and
consequent reduced controllability of the airplane.
Actions Since Existing AD Was Issued
The preamble to AD 2005-23-10 explains that we consider the
requirements ``interim action'' and were considering further
rulemaking. We now have determined that further rulemaking is indeed
necessary, and this proposed AD follows from that determination.
Relevant Service Information
Airbus has issued Revision 02 of Airbus Service Bulletins A330-27-
3138 (for Model A330-200 and -300 series airplanes) and A340-27-4137
(for Model A340-200 and -300 series airplanes); both dated May 30,
2006. These service bulletins supersede, respectively, Revision 01 of
Airbus All Operator Telexes (AOT) A330-27A3138 and A340-27A4137, both
dated October 3, 2005. The AOTs are referenced in AD 2005-23-10 as the
appropriate source of service information for accomplishing the
required testing of the elevator servo control loops, and corrective
actions if necessary. The procedures specified in Revision 02 of the
service bulletins are identical to those in Revision 01 of the AOTs. No
additional work is necessary for airplanes on which the actions
specified in Revision 01 of the applicable AOT have been done.
Airbus also has issued the following service bulletins:
Service Bulletins
------------------------------------------------------------------------
Describe procedures
Airbus service bulletins-- for-- And refer to--
------------------------------------------------------------------------
A330-27-3136, Revision 01, Modification of four Goodrich Actuation
dated July 19, 2006 (for elevator servo Systems Service
Model A330-200 and -300 controls by Bulletin SC4800-27-
series airplanes); and A340- installing a new 18, Revision 1,
27-4135, dated January 12, plug-guide assembly. dated May 19, 2006,
2006 (for Model A340-200 as an additional
and -300 series airplanes). source of service
information for
accomplishing the
modification.
[[Page 65907]]
A330-27-3134, Revision 01, Modification of four Goodrich Actuation
dated May 12, 2006 (for elevator servo Systems Service
Model A330-200 and -300 controls by Bulletin SC4800-27-
series airplanes); and A340- replacing the o- 17, Revision 2,
27-4132, dated October 13, ring of the dated May 19, 2006,
2005 (for Model A340-200 solenoid valves as an additional
and -300 series airplanes). with a new o-ring. source of service
information for
accomplishing the
modification.
------------------------------------------------------------------------
Accomplishing the modification specified in the service bulletins
eliminates the need for the repetitive inspection requirements of AD
2005-23-10 and is intended to adequately address the unsafe condition.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, mandated the
service information and issued airworthiness directive 2007-0008, dated
January 9, 2007, to ensure the continued airworthiness of these
airplanes in the European Union.
FAA's Determination and Requirements of the Proposed AD
These airplanes are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 2005-23-10 and would retain the
requirements of the existing AD. This proposed AD also would require
accomplishing the actions specified in service information described
previously. Accomplishing the modification specified in the service
bulletins described previously eliminates the need for the retained
requirements of 2005-23-10. This proposed AD also would remove
airplanes from the applicability of the existing AD.
Costs of Compliance
The following table provides the estimated costs for U.S. operators
of the affected Model A330-200 and A330-300 series airplanes to comply
with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Work Average U.S.-
Action hour(s) labor rate Parts Cost per airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2005-23- 1 $80 None.................... $80, per inspection 18 $1,440, per inspection
10). cycle. cycle.
Modifications (new proposed actions). 28 $80 The manufacturer states $2,240................. 18 $40,320.
that it will supply
required parts to the
operators at no cost.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Currently, there are no affected Model A340-200 and A340-300 series
airplanes on the U.S. Register. However, if an affected airplane is
imported and placed on the U.S. Register in the future, the proposed
modification would take about 10 work hours, at an average labor rate
of $80 per work hour. The manufacturer states that it would supply
required parts to the operators at no cost. Based on these figures, we
estimate the cost of this proposed AD for Model A340-200 and A340-300
series airplanes to be $800 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed AD and placed it in the
[[Page 65908]]
AD docket. See the ADDRESSES section for a location to examine the
regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
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.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14368 (70 FR 69065, November 14, 2005) and adding
the following new airworthiness directive (AD):
Airbus: Docket No. FAA-2007-0230; Directorate Identifier 2007-NM-
043-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by December
26, 2007.
Affected ADs
(b) This AD supersedes AD 2005-23-10.
Applicability
(c) This AD applies to the airplanes identified in Table 1 of
this AD, certificated in any category.
Table 1.--Applicability
------------------------------------------------------------------------
Excluding those
Airbus model-- airplanes on which any Has been
of the following-- installed--
------------------------------------------------------------------------
A330-200, A330-300, A340-200, Airbus modification In production.
and A340-300 series airplanes. 54833.
Airbus Service In service.
Bulletin A330-27-
3136, Revision 01,
dated July 19, 2006.
Airbus Service In service.
Bulletin A340-27-
4135, dated January
12, 2006.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from reports of failed elevator servo
controls due to broken guides. We are proposing this AD to prevent
failure of the elevator servo controls during certain phases of
takeoff, which could result in an unannounced loss of elevator
control and consequent 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.
Requirements of AD 2005-23-10
Service Information
(f) The term ``AOT,'' as used in paragraphs (g) through (i) of
this AD, means section 4.2. ``Description'' of the following service
information, as applicable:
(1) For Model A330-200 and -300 series airplanes: Airbus All
Operators Telex A330-27A3138, Revision 01, dated October 3, 2005;
and
(2) For Model A340-200 and -300 series airplanes: Airbus All
Operators Telex A340-27A4137, Revision 01, dated October 3, 2005.
Initial and Repetitive Elevator Servo-Loop Tests
(g) Within 200 flight hours after November 29, 2005 (the
effective date of AD 2005-23-10): Test the elevator servo-loops, in
accordance with the AOT, except as provided by paragraph (j) of this
AD. If the test of the elevator servo-loops passes, repeat the test
at intervals not to exceed 140 flight hours or 8 days, whichever
occurs first.
Failed Tests
(h) If any test of the elevator servo-loops required by
paragraph (g) of this AD fails: Before further flight, troubleshoot
the cause of the test failure, and do the applicable corrective
actions; in accordance with the AOT, except as provided by paragraph
(j) of this AD. Thereafter, repeat the test at the times specified
in paragraph (g) of this AD.
Reporting Requirement
(i) Following each test required by paragraph (g) of this AD,
submit a report of the findings of only failed elevator servo-loop
tests to Airbus Customer Services, Engineering and Technical
Support, Attention: Mr. J. Laurent, SEE53, fax +33/(0)5.61.93.44.25;
at the applicable time specified in paragraph (i)(1) or (i)(2) of
this AD. The report must include the description of the failure
experienced during the test, the identified cause of the failure,
and the number of flight hours and flight cycles on the airplane.
Under the provisions of the Paperwork Reduction Act of 1980 (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements contained in this
AD and has assigned OMB Control Number 2120-0056.
(1) If the test was done after November 29, 2005: Submit the
report within 10 days after the test.
(2) If the test was done prior to November 29, 2005: Submit the
report within 10 days after November 29, 2005.
New Requirements of This AD
New Service Information for Testing
(j) As of the effective date of this AD, do the actions required
by paragraphs (g) and (h) of this AD in accordance with the
Accomplishment Instructions of the following service bulletins, as
applicable.
(1) For Model A330-200 and -300 series airplanes: Airbus Service
Bulletin A330-27-3138, Revision 02, dated May 30, 2006; and
(2) For Model A340-200 and -300 series airplanes: Airbus Service
Bulletin A340-27-4137, Revision 02, dated May 30, 2006.
Terminating Actions
(k) Within 17 months after the effective date of this AD, modify
the four elevator servo controls in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3136,
Revision 01, dated July 19, 2006 (for Model A330-200 and -300 series
airplanes); or Airbus Service Bulletin A340-27-4135, dated January
12, 2006 (for Model A340-200 and -300 series airplanes); as
applicable.
Note 1: Airbus Service Bulletins A330-27-3136 and A340-27-4135
refer to Goodrich Actuation Systems Service Bulletin SC4800-27-18,
Revision 1, dated May 19, 2006, as an additional source of service
information for accomplishing the modification required by paragraph
(k) of this AD.
(l) Modifications done before the effective date of this AD in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-27-3136, dated January 12, 2006, are acceptable for
compliance with the modification required by paragraph (k) of this
AD.
(m) Concurrently with the modification required by paragraph (k)
of this AD, modify the four elevator servo controls in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-27-3134, Revision 01, dated May 12, 2006 (for Model A330-200
and -300 series airplanes); or Airbus Service Bulletin A340-27-4132,
dated October 13, 2005 (for Model A340-200 and -300 series
airplanes); as applicable.
Note 2: Airbus Service Bulletins A330-27-3134 and A340-27-4132
refer to Goodrich Actuation Systems Service Bulletin SC4800-27-17,
Revision 2, dated May 19, 2006, as an additional source of service
information for accomplishing the modification required by paragraph
(m) of this AD.
(n) Modifications done before the effective date of this AD in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-27-3134, dated October 13, 2005, are acceptable for
compliance with the modification required by paragraph (m) of this
AD.
(o) Accomplishment of the modifications required by paragraphs
(k) and (m) of this AD constitutes terminating action for the
[[Page 65909]]
requirements of paragraphs (f) through (i) of this AD.
Parts Installation
(p) As of the effective date of this AD, no person may install,
on any airplane, an elevator servo control, unless it has been
modified in accordance with paragraphs (k) and (m) of this AD.
Alternative Methods of Compliance (AMOCs)
(q)(1) 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.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Related Information
(r) EASA airworthiness directive 2007-0008, dated January 9,
2007, also addresses the subject of this AD.
Issued in Renton, Washington, on November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-22925 Filed 11-23-07; 8:45 am]
BILLING CODE 4910-13-P
