Airworthiness Directives; Airbus Model A330-300, A340-200, and A340-300 Series Airplanes, 46313-46317 [E9-21408]
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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
Size Standards, (202) 205–6618 or
sizestandards@sba.gov.
SBA is
correcting language and references in its
Small Business Size Regulations
contained in part 121 of the Code of
Federal Regulations (CFR), chapter 13.
These are administrative corrections
only. Specifically, SBA is correcting 13
CFR 121.101, 121.410 and 121.1205.
SUPPLEMENTARY INFORMATION:
1. 13 CFR 121.101, ‘‘What are SBA size
standards?’’
The text of 13 CFR § 121.101(b)
provides the Internet Web address
where the public can obtain the North
American Industry Classification
System Manual–United States from the
National Technical Information Service
(NTIS), part of the U.S. Department of
Commerce. The Internet Web address
provided in the text is https://
www.ntis.gov/yellowbk/1nty205.htm.
The NTIS has established a new
address, specifically https://
www.ntis.gov/products/naics.aspx.
Although the existing Web address in
§ 121.101 will take a user to the updated
site, SBA believes it should update its
regulations as well to reflect the correct
Internet Web address.
jlentini on DSKJ8SOYB1PROD with RULES
2. 13 CFR 121.410, ‘‘What are the size
standards for SBA’s Section 8(d)
Subcontracting Program?’’
SBA published in the May 15, 2000,
Federal Register (65 FR 30836–30863) a
new table of small business size
standards effective October 1, 2000 for
industries as defined under NAICS.
Until October 1, 2000, the Standard
Industrial Classification (SIC) System
was the basis for SBA’s table of small
business size standards. The May 15,
2000 final rule amended 13 CFR
121.410 by replacing ‘‘SIC code 8711’’
with ‘‘NAICS code 541330.’’
However, an error was made when
SBA issued a proposed rule on
November 22, 2002, (67 FR 70339–
70352) to amend its small business size
regulations and the regulations that
apply to appeals of size determinations.
That rule proposed amending 13 CFR
121.410, which relates to size standards
under SBA’s Section 8(d)
Subcontracting Program. The proposed
amendment correctly preserved the
language of the May 15, 2000 final rule
that described Engineering Services.
However, the proposed rule wrongly
referenced NAICS code 541213, which
is the code for Tax Preparation Services.
The proposed rule should have
referenced NAICS code 541330, because
it is the correct code for Engineering
Services, described in 13 CFR 121.410.
The corresponding final rule that SBA
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18:05 Sep 08, 2009
Jkt 217001
published on May 21, 2004 (69 FR
29192–29209) did not correct this error,
thereby leaving NAICS code 541213 to
refer incorrectly to Engineering
Services.
The text of 13 CFR 121.410 plainly
refers to subcontracting activities that
are included within NAICS code
541330, Engineering Services.
Furthermore, NAICS code 541330 in
SBA’s ‘‘Small Business Size Standards
by NAICS Industry’’ (13 CFR 121.201)
clearly includes the same types of
contracting activities described in 13
CFR 121.410. The purpose of this
correction is to replace NAICS code
541213 in § 121.410 with NAICS code
541330.
3. 13 CFR 121.1205, ‘‘How is a list of
previously granted class waivers
obtained?’’
The text of 13 CFR 121.1205 provides
the Internet Web address where SBA
maintains for the public a list of waivers
of the Nonmanufacturer Rule that it has
granted. SBA has updated that Internet
Web address, and this action will
similarly update § 121.1205.
46313
§ 121.410 What are the size standards for
SBA’s Section 8(d) Subcontracting
Program?
* * * However, subcontracts for
engineering services awarded under the
National Energy Policy Act of 1992 have
the same size standard as Military and
Aerospace Equipment and Military
Weapons under NAICS code 541330.
■ 4. Amend § 121.1205 by revising the
first sentence to read as follows:
§ 121.1205 How is a list of previously
granted class waivers obtained?
A list of classes of products for which
waivers for the Nonmanufacturer Rule
have been granted is maintained in SBA
Web site at: https://www.sba.gov/
aboutsba/sbaprograms/gc/programs/gc_
waivers_nonmanufacturer.html. * * *
Dean R. Koppel,
Acting Director, Office of Government
Contracting.
[FR Doc. E9–21505 Filed 9–8–09; 8:45 am]
BILLING CODE 8025–01–P
DEPARTMENT OF TRANSPORTATION
List of Subjects in 13 CFR Part 121
Federal Aviation Administration
Administrative practice and
procedure, Government procurement,
Government property, Grant programs—
business, Individuals with disabilities,
Loan programs—business, Reporting
and recordkeeping requirements, Small
businesses.
14 CFR Part 39
For the reasons set forth in the
preamble, SBA amends part 13 CFR part
121 by making the following correcting
amendments.
■
PART 121—SMALL BUSINESS SIZE
REGULATIONS
1. The authority citation for part 121
continues to read as follows:
■
Authority: 15 U.S.C. 632, 634(b)(6), 636(b),
637(a), 644, and 662(5); and Pub. L. 105–135,
sec. 401 et seq., 111 Stat. 2592.
2. Amend § 121.101 by revising the
first sentence of paragraph (b) to read as
follows:
■
§ 121.101
What are SBA size standards?
*
*
*
*
*
(b) NAICS is described in the North
American Industry Classification
Manual–United States, which is
available from the National Technical
Information Service, 5285 Port Royal
Road, Springfield, VA 22161; by calling
1(800) 553–6847 or 1(703) 605–6000; or
via the Internet at https://www.ntis.gov/
products/naics.aspx. * * *
■ 3. Amend § 121.410 by revising the
second sentence to read as follows:
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[Docket No. FAA–2009–0264; Directorate
Identifier 2008–NM–174–AD; Amendment
39–16017; AD 2009–18–20]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–300, A340–200, and A340–300
Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
One Long Range operator experienced a
failure of one spoiler servo-control,
associated with surface deflection in flight
and hydraulic leak. On ground, this servocontrol Part Number (P/N) MZ4306000–02X
was found with the maintenance cover
broken. Investigations showed that the
rupture of the maintenance cover was due to
pressure pulse fatigue.
* * * The rupture of the maintenance
cover in flight may result in the deflection of
the associated spoiler surface up to the nullhinge position (loss of the hydraulic locking).
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Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
It may also result in the loss of the associated
hydraulic system (external leakage). In the
worst case, the three hydraulic systems may
be affected, which constitutes an unsafe
condition.
*
*
*
*
*
Loss of the three hydraulic systems
could result in reduced controllability
of the airplane. We are issuing this AD
to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective
October 14, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 14, 2009.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
jlentini on DSKJ8SOYB1PROD with RULES
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on March 26, 2009 (74 FR
13148). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
One Long Range operator experienced a
failure of one spoiler servo-control,
associated with surface deflection in flight
and hydraulic leak. On ground, this servocontrol Part Number (P/N) MZ4306000–02X
was found with the maintenance cover
broken. Investigations showed that the
rupture of the maintenance cover was due to
pressure pulse fatigue.
The maintenance cover allows switching
the servo-control from ‘‘Operational’’ to
‘‘Maintenance’’ modes. The same cover is
installed on all standard MZ spoiler servocontrols except on P/N MZ4339390–12 and
MZ4306000–12, which have a reinforced
maintenance cover. The rupture of the
maintenance cover in flight may result in the
deflection of the associated spoiler surface up
to the null-hinge position (loss of the
hydraulic locking). It may also result in the
loss of the associated hydraulic system
(external leakage). In the worst case, the three
hydraulic systems may be affected, which
constitutes an unsafe condition.
For the reasons described above, this EASA
(European Aviation Safety Agency) AD
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18:05 Sep 08, 2009
Jkt 217001
requires the identification and the
modification of all standard MZ spoiler
servo-controls with initial maintenance cover
(P/N MZ4339390–01X, –02X, –10X for
position 1 and P/N MZ4306000–01X, –02X,
–10X for positions 2 to 6) into standard MZ
servo-controls with reinforced maintenance
cover (P/N MZ4339390–12 for position 1 and
P/N MZ4306000–12 for positions 2 to 6).
Loss of the three hydraulic systems
could result in reduced controllability
of the airplane. You may obtain further
information by examining the MCAI in
the AD docket.
Revised Service Information
We have reviewed Airbus Service
Bulletin A330–27–3110, Revision 03,
dated September 3, 2008. We referred to
Airbus Service Bulletin A330–27–3110,
Revision 02, dated March 2, 2007, as the
appropriate source of service
information for accomplishing certain
actions specified in the NPRM. We have
determined that the actions specified in
Airbus Service Bulletin A330–27–3110,
Revision 03, dated September 3, 2008,
are essentially the same as the actions
specified in Airbus Service Bulletin
A330–27–3110, Revision 02, dated
March 2, 2007. Therefore, we find that
no additional work will be required for
airplanes that have done the
requirements of this AD in accordance
with Airbus Service Bulletin A330–27–
3110, Revision 02, dated March 2, 2007.
We have changed paragraphs (f)(2)
through (f)(6) of this AD to refer to
Revision 03, dated September 3, 2008,
of Airbus Service Bulletin A330–27–
3110. We have also changed paragraph
(f)(7) of this AD to give credit to
operators who have accomplished the
actions in accordance with Airbus
Service Bulletin A330–27–3110,
Revision 02, dated March 2, 2007, as
well as the earlier versions of the service
bulletin.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Request To Clarify Proposed
Applicability
Airbus asks that the applicability
specified in paragraph (c) of the NPRM
be clarified. Airbus notes that the
language ‘‘* * * except those identified
in paragraphs (c)(1) and (c)(2) of this
AD’’ is misleading, because the
exceptions are already included in
paragraphs (c)(1) and (c)(2) of the AD.
We agree with Airbus. We have
changed paragraph (c) of this AD as
follows: ‘‘This AD applies to Airbus
Model A330–300, A340–200, and A340–
300 series airplanes; certificated in any
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category; as identified in paragraphs
(c)(1) and (c)(2) of this AD.’’
Request To Clarify Paragraphs (f)(1),
(f)(2)(i), and (f)(2)(ii) of the NPRM
Airbus also asks that the words ‘‘of
the aircraft’’ be added to the applicable
paragraphs after the words ‘‘since first
flight’’ for clarification. Airbus notes
that the missing text is confusing to
operators, who are asking Airbus if
‘‘since first flight’’ refers to flight hours
on the equipment or flight hours on the
airplane.
We agree with Airbus. It was our
intent that the phrase ‘‘since first flight’’
apply to the subject airplanes, not
equipment. Therefore, we have changed
all applicable references in paragraphs
(f)(1) through (f)(6) of this AD to specify
‘‘since first flight of the airplane.’’
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a note within the AD.
Costs of Compliance
Based on the service information, we
estimate that this AD affects 16 products
of U.S. registry. We also estimate that it
takes 1 work-hour per product to
comply with the basic requirements of
this AD. The average labor rate is $80
per work-hour. Based on these figures,
we estimate the cost of the AD on U.S.
operators to be $1,280, or $80 per
product.
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
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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 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 this AD:
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 AD and placed it in the AD docket.
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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,
■
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16:13 Sep 08, 2009
Jkt 217001
the FAA amends 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2009–18–20 Airbus: Amendment 39–16017.
Docket No. FAA–2009–0264; Directorate
Identifier 2008–NM–174–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 14, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330–
300, A340–200, and A340–300 series
airplanes; certificated in any category; as
identified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Airbus Model A330–301, –302, –303,
–321, –322, –323, –341, –342, and –343
airplanes, manufacturer serial numbers
(MSNs) up to and including MSN 588, except
those on which Airbus Service Bulletin
A330–27–3110 has been embodied in service.
(2) Airbus Model A340–211, –212, –213,
–311, –312, and –313 airplanes, MSNs up to
and including MSN 598, except those on
which Airbus Service Bulletin A340–27–
4115 has been embodied in service.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
One Long Range operator experienced a
failure of one spoiler servo-control,
associated with surface deflection in flight
and hydraulic leak. On ground, this servocontrol Part Number (P/N) MZ4306000–02X
was found with the maintenance cover
broken. Investigations showed that the
rupture of the maintenance cover was due to
pressure pulse fatigue.
The maintenance cover allows switching
the servo-control from ‘‘Operational’’ to
‘‘Maintenance’’ modes. The same cover is
installed on all standard MZ spoiler servocontrols except on P/N MZ4339390–12 and
MZ4306000–12, which have a reinforced
maintenance cover. The rupture of the
maintenance cover in flight may result in the
deflection of the associated spoiler surface up
to the null-hinge position (loss of the
hydraulic locking). It may also result in the
loss of the associated hydraulic system
(external leakage). In the worst case, the three
hydraulic systems may be affected, which
constitutes an unsafe condition.
For the reasons described above, this EASA
(European Aviation Safety Agency) AD
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Fmt 4700
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46315
requires the identification and the
modification of all standard MZ spoiler
servo-controls with initial maintenance cover
(P/N MZ4339390–01X, –02X, –10X for
position 1 and
P/N MZ4306000–01X, 02X, –10X for
positions 2 to 6) into standard MZ servocontrols with reinforced maintenance cover
(P/N MZ4339390–12 for position 1 and P/N
MZ4306000–12 for positions 2 to 6).
Loss of the three hydraulic systems could
result in reduced controllability of the
airplane.
Actions and Compliance
(f) Unless already done, do the following
actions.
(1) For airplanes that have accumulated
more than 8,500 total flight cycles since first
flight of the airplane as of the effective date
of this AD: Do the actions required by
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, as
applicable.
(i) Within 3 months after the effective date
of this AD: Identify the part number of
spoiler servo-controls installed on the
airplane at all positions in order to determine
the number of affected hydraulic circuits in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A330–27A3154, Revision 01; or
Airbus Mandatory Service Bulletin A340–
27A4154, Revision 01; both dated July 25,
2008; as applicable. If there is no spoiler
servo-control installed with a part number
identified in Table 1 of this AD, no further
action is required by this paragraph.
(ii) If there is any spoiler servo-control
installed with a part number identified in
Table 1 of this AD, do all applicable actions
required by paragraph (f)(2), (f)(3), or (f)(4) of
this AD, as applicable.
TABLE 1—SPOILER SERVO-CONTROL
PART NUMBERS
Position 1
MZ4339390–01X .......
MZ4339390–02X .......
MZ4339390–10X .......
Positions 2 through 6
MZ4306000–01X
MZ4306000–02X
MZ4306000–10X
(2) If three affected hydraulic circuits are
identified during the inspection required by
paragraph (f)(1) of this AD, do the actions
required by paragraphs (f)(2)(i), (f)(2)(ii), and
(f)(2)(iii) of this AD, at the time specified.
(i) Before the accumulation of 10,400 total
flight cycles since first flight of the airplane,
or within 3 months after accomplishing the
requirements of paragraph (f)(1)(i) of this AD,
whichever occurs later: Modify the affected
spoiler servo-controls on one hydraulic
circuit in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3110, Revision 03,
dated September 3, 2008; or Airbus Service
Bulletin A340–27–4115, Revision 01, dated
March 2, 2007; as applicable.
(ii) Before the accumulation of 10,800 total
flight cycles since first flight of the airplane,
or within 6 months after accomplishing the
requirements in paragraph (f)(1)(i) of this AD,
whichever occurs later: Modify the affected
spoiler servo-controls on the second
hydraulic circuit in accordance with the
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Accomplishment Instructions of Airbus
Service Bulletin A330–27–3110, Revision 03,
dated September 3, 2008; or Airbus Service
Bulletin A340–27–4115, Revision 01, dated
March 2, 2007; as applicable.
(iii) Within 18 months after the effective
date of this AD: Modify the remaining
affected spoiler servo-controls in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–27–3110,
Revision 03, dated September 3, 2008; or
Airbus Service Bulletin A340–27–4115,
Revision 01, dated March 2, 2007; as
applicable.
(3) If two affected hydraulic circuits are
identified during the inspection required by
paragraph (f)(1) of this AD, do the actions
required by paragraphs (f)(3)(i) and (f)(3)(ii)
of this AD, at the time specified.
(i) Before the accumulation of 10,800 total
flight cycles since first flight of the airplane,
or within 6 months after accomplishing the
requirements specified in paragraph (f)(1)(i)
of this AD, whichever occurs later: Modify
the affected spoiler servo-controls on one
hydraulic circuit in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3110, Revision 03,
dated September 3, 2008; or Airbus Service
Bulletin A340–27–4115, Revision 01, dated
March 2, 2007; as applicable.
(ii) Within 18 months after the effective
date of this AD: Modify the remaining
affected spoiler servo-controls in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–27–3110,
Revision 03, dated September 3, 2008; or
Airbus Service Bulletin A340–27–4115,
Revision 01, dated March 2, 2007; as
applicable.
(4) If one affected hydraulic circuit is
identified during the inspection required by
paragraph (f)(1) of this AD: Within 18 months
after the effective date of this AD, modify the
affected spoiler servo-controls in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–27–3110,
Revision 03, dated September 3, 2008; or
Airbus Service Bulletin A340–27–4115,
Revision 01, dated March 2, 2007; as
applicable.
(5) For airplanes that have accumulated
less than or equal to 8,500 total flight cycles
since first flight of the airplane as of the
effective date of this AD: Do the actions
required by paragraphs (f)(5)(i) and (f)(5)(ii)
of this AD, as applicable.
(i) Within 9 months after the effective date
of this AD: Do the actions specified in
paragraph (f)(1)(i) of this AD. If there is no
spoiler servo-control installed with a part
number identified in Table 1 of this AD, no
further action is required by this paragraph.
(ii) If there is any spoiler servo-control
installed with a part number identified in
Table 1 of this AD: Within 18 months after
the effective date of this AD, modify all the
affected spoiler servo-controls in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A330–27–3110,
Revision 03, dated September 3, 2008; or
Airbus Service Bulletin A340–27–4115,
Revision 01, dated March 2, 2007; as
applicable.
(6) As of the effective date of this AD, no
person may install any spoiler servo-control
with a part number identified in Table 1 of
this AD on any airplane as a replacement
part, unless the part has been modified in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
27–3110, Revision 03, dated September 3,
2008; or Airbus Service Bulletin A340–27–
4115, Revision 01, dated March 2, 2007; as
applicable.
(7) Actions accomplished before the
effective date of this AD in accordance with
the service bulletins specified in Table 2 of
this AD are considered acceptable for
compliance with the corresponding
requirements of this AD.
TABLE 2—CREDIT SERVICE INFORMATION
Service Bulletin
Airbus
Airbus
Airbus
Airbus
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
A330–27–3110
A330–27–3110
A330–27–3110
A340–27–4115
Revision level
.............................
.............................
.............................
.............................
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International
Date
Original ...............................................................................
01 .......................................................................................
02 .......................................................................................
Original ...............................................................................
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
November 28, 2003.
March 26, 2004.
March 2, 2007.
November 28, 2003.
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to EASA Airworthiness Directive
2008–0160, dated August 22, 2008, and the
service bulletins specified in Table 3 of this
AD, for related information.
TABLE 3—RELATED SERVICE INFORMATION
Service Bulletin
jlentini on DSKJ8SOYB1PROD with RULES
Airbus
Airbus
Airbus
Airbus
Revision level
Mandatory Service Bulletin A330–27A3154 ...........................................................................
Mandatory Service Bulletin A340–27A4154 ...........................................................................
Service Bulletin A330–27–3110 ..............................................................................................
Service Bulletin A340–27–4115 ..............................................................................................
Material Incorporated by Reference
(i) You must use the service information
contained in Table 4 of this AD to do the
actions required by this AD, as applicable,
unless the AD specifies otherwise.
VerDate Nov<24>2008
16:13 Sep 08, 2009
Jkt 217001
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
01
01
03
01
Date
July 25, 2008.
July 25, 2008.
September 3, 2008.
March 2, 2007.
(2) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80, e-mail
E:\FR\FM\09SER1.SGM
09SER1
Federal Register / Vol. 74, No. 173 / Wednesday, September 9, 2009 / Rules and Regulations
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
46317
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr
_locations.html.
TABLE 4—MATERIAL INCORPORATED BY REFERENCE
Service Bulletin
Airbus
Airbus
Airbus
Airbus
Mandatory Service Bulletin A330–27A3154, excluding Appendix 1 ...................................
Mandatory Service Bulletin A340–27A4154, excluding Appendix 1 ...................................
Service Bulletin A330–27–3110 ..........................................................................................
Service Bulletin A340–27–4115 ..........................................................................................
Issued in Renton, Washington, on August
26, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–21408 Filed 9–8–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0526; Directorate
Identifier 2009–NM–029–AD; Amendment
39–16008; AD 2009–18–12]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
jlentini on DSKJ8SOYB1PROD with RULES
Revision level
Four aircraft have experienced a dual AC
[alternating current] generator shutdown,
caused by a broken propeller de-ice bus bar
which short-circuited with the backplate
assembly.
* * * A short circuit can cause a dual AC
generator shutdown that, particularly in
conjunction with an engine failure in icing
conditions, could result in reduced
controllability of the aircraft.
*
*
*
*
*
Reduced controllability of the
airplane in certain operating conditions
affects continued safe flight and
landing. We are issuing this AD to
VerDate Nov<24>2008
16:13 Sep 08, 2009
Jkt 217001
require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective
October 14, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 14, 2009.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Wing Chan, Aerospace Engineer,
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–
7311; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on June 10, 2009 (74 FR 27476).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
Four aircraft have experienced a dual AC
[alternating current] generator shutdown,
caused by a broken propeller de-ice bus bar
which short-circuited with the backplate
assembly.
It was subsequently determined that any
friction or contact between a propeller de-ice
bus bar and the backplate assembly can cause
an intermittent short circuit. Such a short
circuit can cause a dual AC generator
shutdown that, particularly in conjunction
with an engine failure in icing conditions,
could result in reduced controllability of the
aircraft.
This [Transport Canada Civil Aviation]
directive mandates revision of the Airplane
Flight Manual (AFM) to introduce a
procedure that restores AC power following
PO 00000
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Fmt 4700
Sfmt 4700
01
01
03
01
Date
July 25, 2008.
July 25, 2008.
September 3, 2008.
March 2, 2007.
a failure of No. 1 and No. 2 AC generators
with propeller de-ice on. Additionally, in
order to prevent similar dual AC generator
shutdowns, it mandates the application of
sealant as insulation between the propeller
de-ice bus bars and the backplate assembly.
Reduced controllability of the
airplane in certain operating conditions
affects continued safe flight and
landing. You may obtain further
information by examining the MCAI in
the AD docket.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
as proposed.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
policies. Any such differences are
highlighted in a Note within the AD.
Costs of Compliance
We estimate that this AD will affect
62 products of U.S. registry. We also
estimate that it will take about 6 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
E:\FR\FM\09SER1.SGM
09SER1
]]>Agencies
[Federal Register Volume 74, Number 173 (Wednesday, September 9, 2009)]
[Rules and Regulations]
[Pages 46313-46317]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-21408]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0264; Directorate Identifier 2008-NM-174-AD;
Amendment 39-16017; AD 2009-18-20]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-300, A340-200, and
A340-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
One Long Range operator experienced a failure of one spoiler
servo-control, associated with surface deflection in flight and
hydraulic leak. On ground, this servo-control Part Number (P/N)
MZ4306000-02X was found with the maintenance cover broken.
Investigations showed that the rupture of the maintenance cover was
due to pressure pulse fatigue.
* * * The rupture of the maintenance cover in flight may result
in the deflection of the associated spoiler surface up to the null-
hinge position (loss of the hydraulic locking).
[[Page 46314]]
It may also result in the loss of the associated hydraulic system
(external leakage). In the worst case, the three hydraulic systems
may be affected, which constitutes an unsafe condition.
* * * * *
Loss of the three hydraulic systems could result in reduced
controllability of the airplane. We are issuing this AD to require
actions to correct the unsafe condition on these products.
DATES: This AD becomes effective October 14, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 14,
2009.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on March 26, 2009 (74
FR 13148). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
One Long Range operator experienced a failure of one spoiler
servo-control, associated with surface deflection in flight and
hydraulic leak. On ground, this servo-control Part Number (P/N)
MZ4306000-02X was found with the maintenance cover broken.
Investigations showed that the rupture of the maintenance cover was
due to pressure pulse fatigue.
The maintenance cover allows switching the servo-control from
``Operational'' to ``Maintenance'' modes. The same cover is
installed on all standard MZ spoiler servo-controls except on P/N
MZ4339390-12 and MZ4306000-12, which have a reinforced maintenance
cover. The rupture of the maintenance cover in flight may result in
the deflection of the associated spoiler surface up to the null-
hinge position (loss of the hydraulic locking). It may also result
in the loss of the associated hydraulic system (external leakage).
In the worst case, the three hydraulic systems may be affected,
which constitutes an unsafe condition.
For the reasons described above, this EASA (European Aviation
Safety Agency) AD requires the identification and the modification
of all standard MZ spoiler servo-controls with initial maintenance
cover (P/N MZ4339390-01X, -02X, -10X for position 1 and P/N
MZ4306000-01X, -02X, -10X for positions 2 to 6) into standard MZ
servo-controls with reinforced maintenance cover (P/N MZ4339390-12
for position 1 and P/N MZ4306000-12 for positions 2 to 6).
Loss of the three hydraulic systems could result in reduced
controllability of the airplane. You may obtain further information by
examining the MCAI in the AD docket.
Revised Service Information
We have reviewed Airbus Service Bulletin A330-27-3110, Revision 03,
dated September 3, 2008. We referred to Airbus Service Bulletin A330-
27-3110, Revision 02, dated March 2, 2007, as the appropriate source of
service information for accomplishing certain actions specified in the
NPRM. We have determined that the actions specified in Airbus Service
Bulletin A330-27-3110, Revision 03, dated September 3, 2008, are
essentially the same as the actions specified in Airbus Service
Bulletin A330-27-3110, Revision 02, dated March 2, 2007. Therefore, we
find that no additional work will be required for airplanes that have
done the requirements of this AD in accordance with Airbus Service
Bulletin A330-27-3110, Revision 02, dated March 2, 2007. We have
changed paragraphs (f)(2) through (f)(6) of this AD to refer to
Revision 03, dated September 3, 2008, of Airbus Service Bulletin A330-
27-3110. We have also changed paragraph (f)(7) of this AD to give
credit to operators who have accomplished the actions in accordance
with Airbus Service Bulletin A330-27-3110, Revision 02, dated March 2,
2007, as well as the earlier versions of the service bulletin.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received.
Request To Clarify Proposed Applicability
Airbus asks that the applicability specified in paragraph (c) of
the NPRM be clarified. Airbus notes that the language ``* * * except
those identified in paragraphs (c)(1) and (c)(2) of this AD'' is
misleading, because the exceptions are already included in paragraphs
(c)(1) and (c)(2) of the AD.
We agree with Airbus. We have changed paragraph (c) of this AD as
follows: ``This AD applies to Airbus Model A330-300, A340-200, and
A340-300 series airplanes; certificated in any category; as identified
in paragraphs (c)(1) and (c)(2) of this AD.''
Request To Clarify Paragraphs (f)(1), (f)(2)(i), and (f)(2)(ii) of the
NPRM
Airbus also asks that the words ``of the aircraft'' be added to the
applicable paragraphs after the words ``since first flight'' for
clarification. Airbus notes that the missing text is confusing to
operators, who are asking Airbus if ``since first flight'' refers to
flight hours on the equipment or flight hours on the airplane.
We agree with Airbus. It was our intent that the phrase ``since
first flight'' apply to the subject airplanes, not equipment.
Therefore, we have changed all applicable references in paragraphs
(f)(1) through (f)(6) of this AD to specify ``since first flight of the
airplane.''
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a note within the AD.
Costs of Compliance
Based on the service information, we estimate that this AD affects
16 products of U.S. registry. We also estimate that it takes 1 work-
hour per product to comply with the basic requirements of this AD. The
average labor rate is $80 per work-hour. Based on these figures, we
estimate the cost of the AD on U.S. operators to be $1,280, or $80 per
product.
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
[[Page 46315]]
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 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 this AD:
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 AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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 AD:
2009-18-20 Airbus: Amendment 39-16017. Docket No. FAA-2009-0264;
Directorate Identifier 2008-NM-174-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
14, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330-300, A340-200, and
A340-300 series airplanes; certificated in any category; as
identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes, manufacturer serial numbers (MSNs) up to
and including MSN 588, except those on which Airbus Service Bulletin
A330-27-3110 has been embodied in service.
(2) Airbus Model A340-211, -212, -213, -311, -312, and -313
airplanes, MSNs up to and including MSN 598, except those on which
Airbus Service Bulletin A340-27-4115 has been embodied in service.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
One Long Range operator experienced a failure of one spoiler
servo-control, associated with surface deflection in flight and
hydraulic leak. On ground, this servo-control Part Number (P/N)
MZ4306000-02X was found with the maintenance cover broken.
Investigations showed that the rupture of the maintenance cover was
due to pressure pulse fatigue.
The maintenance cover allows switching the servo-control from
``Operational'' to ``Maintenance'' modes. The same cover is
installed on all standard MZ spoiler servo-controls except on P/N
MZ4339390-12 and MZ4306000-12, which have a reinforced maintenance
cover. The rupture of the maintenance cover in flight may result in
the deflection of the associated spoiler surface up to the null-
hinge position (loss of the hydraulic locking). It may also result
in the loss of the associated hydraulic system (external leakage).
In the worst case, the three hydraulic systems may be affected,
which constitutes an unsafe condition.
For the reasons described above, this EASA (European Aviation
Safety Agency) AD requires the identification and the modification
of all standard MZ spoiler servo-controls with initial maintenance
cover (P/N MZ4339390-01X, -02X, -10X for position 1 and P/N
MZ4306000-01X, 02X, -10X for positions 2 to 6) into standard MZ
servo-controls with reinforced maintenance cover (P/N MZ4339390-12
for position 1 and P/N MZ4306000-12 for positions 2 to 6).
Loss of the three hydraulic systems could result in reduced
controllability of the airplane.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) For airplanes that have accumulated more than 8,500 total
flight cycles since first flight of the airplane as of the effective
date of this AD: Do the actions required by paragraphs (f)(1)(i) and
(f)(1)(ii) of this AD, as applicable.
(i) Within 3 months after the effective date of this AD:
Identify the part number of spoiler servo-controls installed on the
airplane at all positions in order to determine the number of
affected hydraulic circuits in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-27A3154,
Revision 01; or Airbus Mandatory Service Bulletin A340-27A4154,
Revision 01; both dated July 25, 2008; as applicable. If there is no
spoiler servo-control installed with a part number identified in
Table 1 of this AD, no further action is required by this paragraph.
(ii) If there is any spoiler servo-control installed with a part
number identified in Table 1 of this AD, do all applicable actions
required by paragraph (f)(2), (f)(3), or (f)(4) of this AD, as
applicable.
Table 1--Spoiler Servo-Control Part Numbers
------------------------------------------------------------------------
Position 1 Positions 2 through 6
------------------------------------------------------------------------
MZ4339390-01X............................. MZ4306000-01X
MZ4339390-02X............................. MZ4306000-02X
MZ4339390-10X............................. MZ4306000-10X
------------------------------------------------------------------------
(2) If three affected hydraulic circuits are identified during
the inspection required by paragraph (f)(1) of this AD, do the
actions required by paragraphs (f)(2)(i), (f)(2)(ii), and
(f)(2)(iii) of this AD, at the time specified.
(i) Before the accumulation of 10,400 total flight cycles since
first flight of the airplane, or within 3 months after accomplishing
the requirements of paragraph (f)(1)(i) of this AD, whichever occurs
later: Modify the affected spoiler servo-controls on one hydraulic
circuit in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A330-27-3110, Revision 03, dated September 3, 2008;
or Airbus Service Bulletin A340-27-4115, Revision 01, dated March 2,
2007; as applicable.
(ii) Before the accumulation of 10,800 total flight cycles since
first flight of the airplane, or within 6 months after accomplishing
the requirements in paragraph (f)(1)(i) of this AD, whichever occurs
later: Modify the affected spoiler servo-controls on the second
hydraulic circuit in accordance with the
[[Page 46316]]
Accomplishment Instructions of Airbus Service Bulletin A330-27-3110,
Revision 03, dated September 3, 2008; or Airbus Service Bulletin
A340-27-4115, Revision 01, dated March 2, 2007; as applicable.
(iii) Within 18 months after the effective date of this AD:
Modify the remaining affected spoiler servo-controls in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-27-3110, Revision 03, dated September 3, 2008; or Airbus
Service Bulletin A340-27-4115, Revision 01, dated March 2, 2007; as
applicable.
(3) If two affected hydraulic circuits are identified during the
inspection required by paragraph (f)(1) of this AD, do the actions
required by paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, at the
time specified.
(i) Before the accumulation of 10,800 total flight cycles since
first flight of the airplane, or within 6 months after accomplishing
the requirements specified in paragraph (f)(1)(i) of this AD,
whichever occurs later: Modify the affected spoiler servo-controls
on one hydraulic circuit in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-27-3110, Revision 03,
dated September 3, 2008; or Airbus Service Bulletin A340-27-4115,
Revision 01, dated March 2, 2007; as applicable.
(ii) Within 18 months after the effective date of this AD:
Modify the remaining affected spoiler servo-controls in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-27-3110, Revision 03, dated September 3, 2008; or Airbus
Service Bulletin A340-27-4115, Revision 01, dated March 2, 2007; as
applicable.
(4) If one affected hydraulic circuit is identified during the
inspection required by paragraph (f)(1) of this AD: Within 18 months
after the effective date of this AD, modify the affected spoiler
servo-controls in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A330-27-3110, Revision 03, dated September
3, 2008; or Airbus Service Bulletin A340-27-4115, Revision 01, dated
March 2, 2007; as applicable.
(5) For airplanes that have accumulated less than or equal to
8,500 total flight cycles since first flight of the airplane as of
the effective date of this AD: Do the actions required by paragraphs
(f)(5)(i) and (f)(5)(ii) of this AD, as applicable.
(i) Within 9 months after the effective date of this AD: Do the
actions specified in paragraph (f)(1)(i) of this AD. If there is no
spoiler servo-control installed with a part number identified in
Table 1 of this AD, no further action is required by this paragraph.
(ii) If there is any spoiler servo-control installed with a part
number identified in Table 1 of this AD: Within 18 months after the
effective date of this AD, modify all the affected spoiler servo-
controls in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A330-27-3110, Revision 03, dated September
3, 2008; or Airbus Service Bulletin A340-27-4115, Revision 01, dated
March 2, 2007; as applicable.
(6) As of the effective date of this AD, no person may install
any spoiler servo-control with a part number identified in Table 1
of this AD on any airplane as a replacement part, unless the part
has been modified in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A330-27-3110, Revision 03, dated
September 3, 2008; or Airbus Service Bulletin A340-27-4115, Revision
01, dated March 2, 2007; as applicable.
(7) Actions accomplished before the effective date of this AD in
accordance with the service bulletins specified in Table 2 of this
AD are considered acceptable for compliance with the corresponding
requirements of this AD.
Table 2--Credit Service Information
----------------------------------------------------------------------------------------------------------------
Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A330-27-3110.... Original................... November 28, 2003.
Airbus Service Bulletin A330-27-3110.... 01......................... March 26, 2004.
Airbus Service Bulletin A330-27-3110.... 02......................... March 2, 2007.
Airbus Service Bulletin A340-27-4115.... Original................... November 28, 2003.
----------------------------------------------------------------------------------------------------------------
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. Send information to ATTN:
Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to EASA Airworthiness Directive 2008-0160, dated
August 22, 2008, and the service bulletins specified in Table 3 of
this AD, for related information.
Table 3--Related Service Information
----------------------------------------------------------------------------------------------------------------
Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A330- 01 July 25, 2008.
27A3154.
Airbus Mandatory Service Bulletin A340- 01 July 25, 2008.
27A4154.
Airbus Service Bulletin A330-27-3110......... 03 September 3, 2008.
Airbus Service Bulletin A340-27-4115......... 01 March 2, 2007.
----------------------------------------------------------------------------------------------------------------
Material Incorporated by Reference
(i) You must use the service information contained in Table 4 of
this AD to do the actions required by this AD, as applicable, unless
the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 45 80, e-mail
[[Page 46317]]
airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Table 4--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A330- 01 July 25, 2008.
27A3154, excluding Appendix 1.
Airbus Mandatory Service Bulletin A340- 01 July 25, 2008.
27A4154, excluding Appendix 1.
Airbus Service Bulletin A330-27-3110......... 03 September 3, 2008.
Airbus Service Bulletin A340-27-4115......... 01 March 2, 2007.
----------------------------------------------------------------------------------------------------------------
Issued in Renton, Washington, on August 26, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-21408 Filed 9-8-09; 8:45 am]
BILLING CODE 4910-13-P
