Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes) and A310 Series Airplanes, 59008-59011 [2011-24203]
Download as PDF
59008
Federal Register / Vol. 76, No. 185 / Friday, September 23, 2011 / Rules and Regulations
Least efficient basic model—(model numbers(s))
Nominal full-load efficiency
Motor horsepower/standard kilowatt equivalent
Open motors
(number of poles)
Enclosed motors
(number of poles)
8
[FR Doc. 2011–24500 Filed 9–22–11; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0647; Directorate
Identifier 2010–NM–193–AD; Amendment
39–16812; AD 2011–20–03]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B4–600, B4–600R, and F4–600R
Series Airplanes, and Model C4–605R
Variant F Airplanes (Collectively Called
A300–600 Series Airplanes) and A310
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
erowe on DSK2VPTVN1PROD with RULES
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:
Surface defects were visually detected on
the rudder of an A319 and an A321 in-service
aeroplane. Investigation has determined that
the defects reported on both rudders
corresponded to areas that had been
reworked in production. The investigation
confirmed that the defects were as a result of
de-bonding between the skin and honeycomb
core. Such reworks were also performed on
some rudders fitted on A310 and A300–600
aeroplanes.
An extended de-bonding, if not detected
and corrected, may degrade the structural
integrity of the rudder. The loss of the rudder
leads to degradation of the handling qualities
and reduces the controllability of the
aeroplane.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
VerDate Mar<15>2010
14:40 Sep 22, 2011
Jkt 223001
4
2
8
6
4
2
lll
lll
lll
lll
lll
lll
lll
lll
lll
Etc ....................................................................................................
6
lll
lll
lll
lll
lll
lll
lll
DATES: This AD becomes effective
October 28, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 28, 2011.
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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; 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 June 29, 2011 (76 FR 38069).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
Surface defects were visually detected on
the rudder of an A319 and an A321 in-service
aeroplane. Investigation has determined that
the defects reported on both rudders
corresponded to areas that had been
reworked in production. The investigation
confirmed that the defects were as a result of
de-bonding between the skin and honeycomb
core. Such reworks were also performed on
some rudders fitted on A310 and A300–600
aeroplanes.
An extended de-bonding, if not detected
and corrected, may degrade the structural
integrity of the rudder. The loss of the rudder
leads to degradation of the handling qualities
and reduces the controllability of the
aeroplane.
To address this unsafe condition, EASA
issued AD 2010–0002 [which corresponds to
FAA AD 2010–16–13, Amendment 39–16390
(75 FR 49370, August 13, 2010)], superseding
[EASA] AD 2009–0166, to require
inspections of specific areas and, depending
on findings, the application of corrective
actions for those rudders where production
reworks have been identified.
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Frm 00006
Fmt 4700
Sfmt 4700
This new [EASA] AD addresses the rudder
population that has also been reworked in
production but not included in the
applicability of EASA AD 2010–0002.
The required actions, for certain
rudders, include vacuum loss
inspections and elasticity laminate
checker inspections for defects
including de-bonding between the skin
and honeycomb core of the rudder. The
corrective action is contacting the FAA
or EASA for repair instructions if any
defects are found. For certain other
rudders, the required actions include
replacing the rudder with a serviceable
rudder. We are considering similar
rulemaking action on Model A319 and
A321 airplanes. 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 (76
FR 38069, June 29, 2011) 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
215 products of U.S. registry. We also
estimate that it will take about 4 work-
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Federal Register / Vol. 76, No. 185 / Friday, September 23, 2011 / Rules and Regulations
hours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of the AD on U.S. operators to be
$73,100, or $340 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
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.
erowe on DSK2VPTVN1PROD with RULES
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 (76 FR 38069, June
29, 2011), the regulatory evaluation, any
comments received, and other
information. The street address for the
VerDate Mar<15>2010
14:40 Sep 22, 2011
Jkt 223001
Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
TABLE 2—RUDDER INFORMATION—
Continued
Rudder part No.
Affected
rudder
serial No.
A554–71710–004–00 ...................
A554–71710–004–00 ...................
A554–71710–004–00 ...................
A554–71730–000–00–0000 .........
A554–71730–000–00–0000 .........
A554–71730–000–00–0000 .........
A554–71730–000–00–0000 .........
A554–71730–000–00–0000 .........
TS–2071
TS–2072
TS–2073
TS–2082
TS–2084
TS–2085
TS–2086
TS–2087
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
TABLE 3—RUDDER INFORMATION
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:
■
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 28, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300
B4–601, B4–603, B4–620, B4–622, B4–605R,
B4–622R, F4–605R, F4–622R, and C4–605R
Variant F airplanes; and Model A310–203,
–204, –221, –222, –304, –322, –324, and –325
airplanes; certificated in any category;
equipped with carbon fiber reinforced plastic
rudders having any part number and serial
number listed in table 1, 2, 3, or 4 of this AD.
TABLE 1—RUDDER INFORMATION
A554–71710–000–00
A554–71710–000–00
A554–71710–000–00
A554–71710–002–00
A554–71710–004–00
...................
...................
...................
...................
...................
Affected
rudder
serial No.
TS–2010
TS–2027
TS–2030
TS–2043
TS–2048
TABLE 2—RUDDER INFORMATION
Rudder part No.
Affected
rudder
serial No.
MSN-scrapped ..............................
A554–71710–000–00 ...................
A554–71710–000–00 ...................
A554–71710–002–00 ...................
A554–71710–004–00 ...................
A554–71710–004–00 ...................
TS–1362
TS–2006
TS–2008
TS–2033
TS–2054
TS–2061
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
Affected
rudder
serial No.
Rudder part No.
A554–71500–016–30
A554–71710–004–00
A554–71710–004–00
A554–71710–004–00
2011–20–03 Airbus: Amendment 39–16812.
Docket No. FAA–2011–0647; Directorate
Identifier 2010–NM–193–AD.
Rudder part No.
59009
...................
...................
...................
...................
HF–1254
TS–2049
TS–2055
TS–2059
TABLE 4—RUDDER INFORMATION
Affected
rudder
serial No.
Rudder part No.
A554–71500–016–91
A554–71500–014–00
A554–71500–016–00
A554–71500–016–00
A554–71500–026–00
...................
...................
...................
...................
...................
HF–1044
HF–1116
HF–1183
HF–1184
TS–1402
Subject
(d) Air Transport Association (ATA) of
America Code 55: Stabilizers.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Surface defects were visually detected on
the rudder of an A319 and an A321 in-service
aeroplane. Investigation has determined that
the defects reported on both rudders
corresponded to areas that had been
reworked in production. The investigation
confirmed that the defects were as a result of
de-bonding between the skin and honeycomb
core. Such reworks were also performed on
some rudders fitted on A310 and A300–600
aeroplanes.
An extended de-bonding, if not detected
and corrected, may degrade the structural
integrity of the rudder. The loss of the rudder
leads to degradation of the handling qualities
and reduces the controllability of the
aeroplane.
*
*
*
*
*
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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23SER1
erowe on DSK2VPTVN1PROD with RULES
59010
Federal Register / Vol. 76, No. 185 / Friday, September 23, 2011 / Rules and Regulations
Inspections and Corrective Actions for
Rudders Identified in Tables 1, 2, and 3
(g) For rudders identified in table 1 or table
2 of this AD: Do the actions specified in
paragraph (g)(1) or (g)(2) of this AD, as
applicable, and paragraphs (g)(3) and (g)(4) of
this AD, at the time specified. Do the actions
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A310–55–2049 (for Model A310
series airplanes) or A300–55–6048 (for Model
A300–600 series airplanes), both dated
March 16, 2010.
(1) For rudders identified in table 1 of this
AD: Within 8 months after the effective date
of this AD, perform a vacuum loss inspection
in the ‘‘area 1’’ location defined in Airbus
Mandatory Service Bulletin A310–55–2049
or A300–55–6048, both dated March 16,
2010, as applicable, to detect defects,
including de-bonding.
(2) For rudders identified in table 2 of this
AD: Within 24 months after the effective date
of this AD, perform a vacuum loss inspection
in the ‘‘area 1’’ location defined in Airbus
Mandatory Service Bulletin A310–55–2049
or A300–55–6048, both dated March 16,
2010, as applicable, to detect defects,
including de-bonding.
(3) Within 24 months after the effective
date of this AD: Do an elasticity laminate
checker inspection to detect defects,
including de-bonding, in the trailing edge
location.
(4) Repeat the inspection required by
paragraph (g)(3) of this AD two times at
intervals not to exceed 4,500 flight cycles,
but not fewer than 4,000 flight cycles from
the most recent inspection.
(h) For rudders identified in table 3 of this
AD: Do the actions specified in paragraphs
(h)(1) and (h)(2) of this AD at the time
specified. Do the actions in accordance with
the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–55–2049
(for Model A310 series airplanes) or A300–
55–6048 (for Model A300–600 series
airplanes), both dated March 16, 2010.
(1) Within 4,500 flight cycles after the
effective date of this AD, but not fewer than
4,000 flight cycles from the most recent
elasticity laminate checker inspection: Do an
elasticity laminate checker inspection to
detect defects, including de-bonding, in the
trailing edge location.
(2) Repeat the inspection required by
paragraph (h)(1) of this AD one time within
4,500 flight cycles, but not fewer than 4,000
flight cycles from the last inspection.
(i) If any defect is found during any
inspection required by paragraphs (g) and (h)
of this AD, before further flight, repair in
accordance with a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or
its delegated agent).
(j) If no defect is found during the
inspections required by paragraphs (g)(1) and
(g)(2) of this AD, before further flight, restore
the vacuum loss holes with the temporary
restoration with self adhesive tape,
temporary restoration with resin, or
permanent restoration with resin and surface
protection. Do the applicable actions
specified in paragraph (j)(1) or (j)(2) of this
AD.
VerDate Mar<15>2010
14:40 Sep 22, 2011
Jkt 223001
(1) For airplanes on which a temporary
restoration with self-adhesive disks or tapes
is done, within 4 months after doing the
restoration, do a detailed inspection for loose
or missing self-adhesive disks or tapes and
repeat the inspection thereafter at intervals
not to exceed 4 months until the permanent
restoration is done, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310–55–2049
(for Model A310 series airplanes) or A300–
55–6048 (for Model A300–600 series
airplanes), both dated March 16, 2010. If any
loose or missing self-adhesive disks or tapes
are found during any inspection required by
this AD, before further flight, close the holes,
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A310–55–2049 or A300–55–6048,
both dated March 16, 2010, as applicable. Do
the permanent restoration within 4,500 flight
cycles after doing the temporary restoration,
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A310–55–2049 or A300–55–6048,
both dated March 16, 2010, as applicable.
(2) For airplanes on which a temporary
restoration with resin is done: Within 4,500
flight cycles after doing the temporary
restoration do the permanent restoration, in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A310–55–2049 (for Model A310
series airplanes) or A300–55–6048 (for Model
A300–600 series airplanes), both dated
March 16, 2010.
Reporting
(k) At the applicable time specified in
paragraph (k)(1) or (k)(2) of this AD: Report
the results of each inspection required by
paragraphs (g) and (h) of this AD, including
no findings, to Airbus, as specified in Airbus
Mandatory Service Bulletin A310–55–2049
(for Model A310 series airplanes) or A300–
55–6048 (for Model A300–600 series
airplanes), both dated March 16, 2010.
(1) Inspections done before the effective
date of this AD: Within 30 days after the
effective date of this AD.
(2) Inspections done on or after the
effective date of this AD: Within 30 days after
accomplishment of the inspection.
Replacement for Rudders Identified in
Table 4
(l) For rudders identified in table 4 of this
AD: Within 8 months after the effective date
of this AD, replace the affected rudder with
a serviceable unit, in accordance with a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, or the EASA (or
its delegated agent).
Parts Installation
(m) As of the effective date of this AD, no
person may install any rudder identified in
table 1, 2, or 3 of this AD on any airplane,
unless the rudder has been inspected and all
applicable corrective actions have been done
in accordance with paragraphs (g), (h), and (i)
of this AD, as applicable.
(n) As of the effective date of this AD, no
person may install any rudder identified in
table 4 of this AD on any airplane.
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(o) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 227–2125; fax (425)
227–1149. Information may be e-mailed to:
9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(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: A Federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Related Information
(p) Refer to MCAI EASA Airworthiness
Directive 2010–0144, dated July 16, 2010;
and Airbus Mandatory Service Bulletins
A310–55–2049 and A300–55–6048, both
dated March 16, 2010; for related
information.
Material Incorporated by Reference
(q) You must use Airbus Mandatory
Service Bulletin A310–55–2049, dated March
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Federal Register / Vol. 76, No. 185 / Friday, September 23, 2011 / Rules and Regulations
16, 2010; or Airbus Mandatory Service
Bulletin A300–55–6048, dated March 16,
2010; as applicable; to do the actions
required by this AD, 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—EAW
(Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; e-mail account.airworth-eas@
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.
(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.
Issued in Renton, Washington on
September 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2011–24203 Filed 9–22–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2011–0569; Directorate
Identifier 2010–NM–240–AD; Amendment
39–16811; AD 2011–20–02]
RIN 2120–AA64
Airworthiness Directives; BAE
Systems (Operations) Limited Model
BAe 146 and Avro 146–RJ Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
erowe on DSK2VPTVN1PROD with RULES
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:
VerDate Mar<15>2010
14:40 Sep 22, 2011
Jkt 223001
BAE Systems have received reports of inservice failure of the Main Landing Gear
(MLG) shock absorber lower attachment pin.
*
*
*
*
*
This condition, if not detected and
corrected, could lead to a MLG collapse on
the ground or during landing and
consequently damage to the aeroplane or
injury to the occupants.
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
October 28, 2011.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 28, 2011.
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:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1175; 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 June 22, 2011 (76 FR 36398).
That NPRM proposed to correct an
unsafe condition for the specified
products. The MCAI states:
BAE Systems have received reports of inservice failure of the Main Landing Gear
(MLG) shock absorber lower attachment pin.
Investigation has shown that the pin
failures were due to corrosion.
This condition, if not detected and
corrected, could lead to a MLG collapse on
the ground or during landing and
consequently damage to the aeroplane or
injury to the occupants.
For the reasons described above, this AD
requires repetitive [general visual]
inspections [for damage (cracking, corrosion,
and exposed material)] of the MLG shock
absorber lower attachment pins and
replacement, depending on findings.
The replacement, if damage is found,
consists of installing serviceable pins.
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
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
59011
received no comments on the NPRM (76
FR 36398, June 22, 2011) 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
about 1 product of U.S. registry. We also
estimate that it will take about 2 workhours per product to comply with the
basic requirements of this AD. The
average labor rate is $85 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $170 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 2 work-hours and require parts
costing $14,000, for a cost of $14,170
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
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.
E:\FR\FM\23SER1.SGM
23SER1
Agencies
[Federal Register Volume 76, Number 185 (Friday, September 23, 2011)]
[Rules and Regulations]
[Pages 59008-59011]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-24203]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0647; Directorate Identifier 2010-NM-193-AD;
Amendment 39-16812; AD 2011-20-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes
(Collectively Called A300-600 Series Airplanes) and A310 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:
Surface defects were visually detected on the rudder of an A319
and an A321 in-service aeroplane. Investigation has determined that
the defects reported on both rudders corresponded to areas that had
been reworked in production. The investigation confirmed that the
defects were as a result of de-bonding between the skin and
honeycomb core. Such reworks were also performed on some rudders
fitted on A310 and A300-600 aeroplanes.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective October 28, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 28,
2011.
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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; 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 June 29, 2011 (76 FR
38069). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
Surface defects were visually detected on the rudder of an A319
and an A321 in-service aeroplane. Investigation has determined that
the defects reported on both rudders corresponded to areas that had
been reworked in production. The investigation confirmed that the
defects were as a result of de-bonding between the skin and
honeycomb core. Such reworks were also performed on some rudders
fitted on A310 and A300-600 aeroplanes.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
To address this unsafe condition, EASA issued AD 2010-0002
[which corresponds to FAA AD 2010-16-13, Amendment 39-16390 (75 FR
49370, August 13, 2010)], superseding [EASA] AD 2009-0166, to
require inspections of specific areas and, depending on findings,
the application of corrective actions for those rudders where
production reworks have been identified.
This new [EASA] AD addresses the rudder population that has also
been reworked in production but not included in the applicability of
EASA AD 2010-0002.
The required actions, for certain rudders, include vacuum loss
inspections and elasticity laminate checker inspections for defects
including de-bonding between the skin and honeycomb core of the rudder.
The corrective action is contacting the FAA or EASA for repair
instructions if any defects are found. For certain other rudders, the
required actions include replacing the rudder with a serviceable
rudder. We are considering similar rulemaking action on Model A319 and
A321 airplanes. 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 (76 FR 38069, June 29,
2011) 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 215 products of U.S. registry.
We also estimate that it will take about 4 work-
[[Page 59009]]
hours per product to comply with the basic requirements of this AD. The
average labor rate is $85 per work-hour. Based on these figures, we
estimate the cost of the AD on U.S. operators to be $73,100, or $340
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 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 (76 FR 38069, June 29, 2011),
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, 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:
2011-20-03 Airbus: Amendment 39-16812. Docket No. FAA-2011-0647;
Directorate Identifier 2010-NM-193-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
28, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620,
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F
airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes; certificated in any category; equipped with
carbon fiber reinforced plastic rudders having any part number and
serial number listed in table 1, 2, 3, or 4 of this AD.
Table 1--Rudder Information
------------------------------------------------------------------------
Rudder part No. Affected rudder serial No.
------------------------------------------------------------------------
A554-71710-000-00.......................... TS-2010
A554-71710-000-00.......................... TS-2027
A554-71710-000-00.......................... TS-2030
A554-71710-002-00.......................... TS-2043
A554-71710-004-00.......................... TS-2048
------------------------------------------------------------------------
Table 2--Rudder Information
------------------------------------------------------------------------
Rudder part No. Affected rudder serial No.
------------------------------------------------------------------------
MSN-scrapped............................... TS-1362
A554-71710-000-00.......................... TS-2006
A554-71710-000-00.......................... TS-2008
A554-71710-002-00.......................... TS-2033
A554-71710-004-00.......................... TS-2054
A554-71710-004-00.......................... TS-2061
A554-71710-004-00.......................... TS-2071
A554-71710-004-00.......................... TS-2072
A554-71710-004-00.......................... TS-2073
A554-71730-000-00-0000..................... TS-2082
A554-71730-000-00-0000..................... TS-2084
A554-71730-000-00-0000..................... TS-2085
A554-71730-000-00-0000..................... TS-2086
A554-71730-000-00-0000..................... TS-2087
------------------------------------------------------------------------
Table 3--Rudder Information
------------------------------------------------------------------------
Rudder part No. Affected rudder serial No.
------------------------------------------------------------------------
A554-71500-016-30.......................... HF-1254
A554-71710-004-00.......................... TS-2049
A554-71710-004-00.......................... TS-2055
A554-71710-004-00.......................... TS-2059
------------------------------------------------------------------------
Table 4--Rudder Information
------------------------------------------------------------------------
Rudder part No. Affected rudder serial No.
------------------------------------------------------------------------
A554-71500-016-91.......................... HF-1044
A554-71500-014-00.......................... HF-1116
A554-71500-016-00.......................... HF-1183
A554-71500-016-00.......................... HF-1184
A554-71500-026-00.......................... TS-1402
------------------------------------------------------------------------
Subject
(d) Air Transport Association (ATA) of America Code 55:
Stabilizers.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Surface defects were visually detected on the rudder of an A319
and an A321 in-service aeroplane. Investigation has determined that
the defects reported on both rudders corresponded to areas that had
been reworked in production. The investigation confirmed that the
defects were as a result of de-bonding between the skin and
honeycomb core. Such reworks were also performed on some rudders
fitted on A310 and A300-600 aeroplanes.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
* * * * *
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
[[Page 59010]]
Inspections and Corrective Actions for Rudders Identified in Tables 1,
2, and 3
(g) For rudders identified in table 1 or table 2 of this AD: Do
the actions specified in paragraph (g)(1) or (g)(2) of this AD, as
applicable, and paragraphs (g)(3) and (g)(4) of this AD, at the time
specified. Do the actions in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-55-2049 (for
Model A310 series airplanes) or A300-55-6048 (for Model A300-600
series airplanes), both dated March 16, 2010.
(1) For rudders identified in table 1 of this AD: Within 8
months after the effective date of this AD, perform a vacuum loss
inspection in the ``area 1'' location defined in Airbus Mandatory
Service Bulletin A310-55-2049 or A300-55-6048, both dated March 16,
2010, as applicable, to detect defects, including de-bonding.
(2) For rudders identified in table 2 of this AD: Within 24
months after the effective date of this AD, perform a vacuum loss
inspection in the ``area 1'' location defined in Airbus Mandatory
Service Bulletin A310-55-2049 or A300-55-6048, both dated March 16,
2010, as applicable, to detect defects, including de-bonding.
(3) Within 24 months after the effective date of this AD: Do an
elasticity laminate checker inspection to detect defects, including
de-bonding, in the trailing edge location.
(4) Repeat the inspection required by paragraph (g)(3) of this
AD two times at intervals not to exceed 4,500 flight cycles, but not
fewer than 4,000 flight cycles from the most recent inspection.
(h) For rudders identified in table 3 of this AD: Do the actions
specified in paragraphs (h)(1) and (h)(2) of this AD at the time
specified. Do the actions in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-55-2049 (for
Model A310 series airplanes) or A300-55-6048 (for Model A300-600
series airplanes), both dated March 16, 2010.
(1) Within 4,500 flight cycles after the effective date of this
AD, but not fewer than 4,000 flight cycles from the most recent
elasticity laminate checker inspection: Do an elasticity laminate
checker inspection to detect defects, including de-bonding, in the
trailing edge location.
(2) Repeat the inspection required by paragraph (h)(1) of this
AD one time within 4,500 flight cycles, but not fewer than 4,000
flight cycles from the last inspection.
(i) If any defect is found during any inspection required by
paragraphs (g) and (h) of this AD, before further flight, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or its delegated agent).
(j) If no defect is found during the inspections required by
paragraphs (g)(1) and (g)(2) of this AD, before further flight,
restore the vacuum loss holes with the temporary restoration with
self adhesive tape, temporary restoration with resin, or permanent
restoration with resin and surface protection. Do the applicable
actions specified in paragraph (j)(1) or (j)(2) of this AD.
(1) For airplanes on which a temporary restoration with self-
adhesive disks or tapes is done, within 4 months after doing the
restoration, do a detailed inspection for loose or missing self-
adhesive disks or tapes and repeat the inspection thereafter at
intervals not to exceed 4 months until the permanent restoration is
done, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A310-55-2049 (for Model A310 series
airplanes) or A300-55-6048 (for Model A300-600 series airplanes),
both dated March 16, 2010. If any loose or missing self-adhesive
disks or tapes are found during any inspection required by this AD,
before further flight, close the holes, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-55-2049 or A300-55-6048, both dated March 16, 2010, as
applicable. Do the permanent restoration within 4,500 flight cycles
after doing the temporary restoration, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-55-2049 or A300-55-6048, both dated March 16, 2010, as
applicable.
(2) For airplanes on which a temporary restoration with resin is
done: Within 4,500 flight cycles after doing the temporary
restoration do the permanent restoration, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-55-2049 (for Model A310 series airplanes) or A300-55-6048 (for
Model A300-600 series airplanes), both dated March 16, 2010.
Reporting
(k) At the applicable time specified in paragraph (k)(1) or
(k)(2) of this AD: Report the results of each inspection required by
paragraphs (g) and (h) of this AD, including no findings, to Airbus,
as specified in Airbus Mandatory Service Bulletin A310-55-2049 (for
Model A310 series airplanes) or A300-55-6048 (for Model A300-600
series airplanes), both dated March 16, 2010.
(1) Inspections done before the effective date of this AD:
Within 30 days after the effective date of this AD.
(2) Inspections done on or after the effective date of this AD:
Within 30 days after accomplishment of the inspection.
Replacement for Rudders Identified in Table 4
(l) For rudders identified in table 4 of this AD: Within 8
months after the effective date of this AD, replace the affected
rudder with a serviceable unit, in accordance with a method approved
by the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA, or the EASA (or its delegated agent).
Parts Installation
(m) As of the effective date of this AD, no person may install
any rudder identified in table 1, 2, or 3 of this AD on any
airplane, unless the rudder has been inspected and all applicable
corrective actions have been done in accordance with paragraphs (g),
(h), and (i) of this AD, as applicable.
(n) As of the effective date of this AD, no person may install
any rudder identified in table 4 of this AD on any airplane.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(o) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, FAA, has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19. In accordance with 14 CFR 39.19, send your request to your
principal inspector or local Flight Standards District Office, as
appropriate. If sending information directly to the International
Branch, send it to ATTN: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 227-2125; fax (425) 227-1149. Information may be e-mailed to:
9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC,
notify your appropriate principal inspector, or lacking a principal
inspector, the manager of the local flight standards district
office/certificate holding district office. The AMOC approval letter
must specifically reference this AD.
(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: A Federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.,
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
Related Information
(p) Refer to MCAI EASA Airworthiness Directive 2010-0144, dated
July 16, 2010; and Airbus Mandatory Service Bulletins A310-55-2049
and A300-55-6048, both dated March 16, 2010; for related
information.
Material Incorporated by Reference
(q) You must use Airbus Mandatory Service Bulletin A310-55-2049,
dated March
[[Page 59011]]
16, 2010; or Airbus Mandatory Service Bulletin A300-55-6048, dated
March 16, 2010; as applicable; to do the actions required by this
AD, 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--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; e-mail account.airworth-eas@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.
(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.
Issued in Renton, Washington on September 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-24203 Filed 9-22-11; 8:45 am]
BILLING CODE 4910-13-P