Airworthiness Directives; Airbus Model A318, A319, A320 and A321 Series Airplanes, 18118-18121 [E9-8982]
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Federal Register / Vol. 74, No. 75 / Tuesday, April 21, 2009 / Rules and Regulations
Subject
requirements and has assigned OMB Control
Number 2120–0056.
(d) Air Transport Association of America
(ATA) Code 30: Ice and Rain Protection.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
This Airworthiness Directive (AD) is
prompted by some occurrences where the
Deice Pressure Regulator has vented too
much hot air into the forward compartment
damaging the oxygen cylinder ON/OFF cable,
the Ram-Air Scoop cable and the
Environmental Control System (ECS) firewall
shut-off valve cable.
If incorrectly adjusted, or defective, the
Deice Pressure Regulator can vent hot air into
the forward compartment. This situation can
cause overheating and failures of components
located inside the forward compartment,
which could result in potential loss of several
functions essential for safe flight.
For the reason described above, this AD
mandates the installation of a flange and
scoop in the aircraft skin to vent the hot air
from the Deice Pressure Regulator overboard.
Actions and Compliance
(f) Unless already done, within the next 3
months after May 26, 2009 (the effective date
of this AD), install an overboard vent for the
airfoil deice system pressure regulator
(Modification Kit Number 500.50.12.332)
following the Accomplishment Instructions
in PILATUS AIRCRAFT LTD. PC12 Service
Bulletin No. 30–011, dated July 9, 2008.
FAA AD Differences
mstockstill on PROD1PC66 with RULES
Note: 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, Standards Office,
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: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64016;
telephone: (816) 329–4059; fax: (816) 329–
4090. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(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
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
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Jkt 217001
Related Information
(h) Refer to MCAI European Aviation
Safety Agency (EASA) AD No. 2009–0007,
dated January 13, 2009; and PILATUS
AIRCRAFT LTD. PC12 Service Bulletin No.
30–011, dated July 9, 2008, for related
information.
Material Incorporated by Reference
(i) You must use PILATUS AIRCRAFT
LTD. PC12 Service Bulletin No. 30–011,
dated July 9, 2008, 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 PILATUS AIRCRAFT LTD.,
Customer Service Manager, CH–6371
STANS, Switzerland; telephone: +41 (0)41
619 62 08; fax: +41 (0)41 619 73 11; Internet:
https://www.pilatus-aircraft.com/, or e-mail:
SupportPC12@pilatus-aircraft.com.
(3) You may review copies of the service
information incorporated by reference for
this AD at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas
City, Missouri 64106. For information on the
availability of this material at the Central
Region, call (816) 329–3768.
(4) You may also review copies of the
service information incorporated by reference
for this AD 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 Kansas City, Missouri, on April
9, 2009.
John Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–8687 Filed 4–20–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
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:
During a routine inspection on an Airbus
A321 aircraft, the operator discovered that a
bearing of the flap track No. 1 pendulum
assembly had migrated out of position. * * *
This condition, if not corrected, could lead
to separation of the bearing/flap track
assembly, resulting in the detachment of the
affected flap surface from the wing and
consequent loss of control of the aircraft.
*
*
*
*
*
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective May
6, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of May 6, 2009.
We must receive comments on this
AD by May 21, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0360; Directorate
Identifier 2009–NM–039–AD; Amendment
39–15887; AD 2009–09–01]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A318, A319, A320 and A321 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
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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 this AD, 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.
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
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Federal Register / Vol. 74, No. 75 / Tuesday, April 21, 2009 / Rules and Regulations
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–2141; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA) which is the Technical Agent of
the Member States of the European
Community, has issued EASA
Airworthiness Directive 2009–0025,
dated February 10, 2009 [Corrected
February 11, 2009] (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
During a routine inspection on an Airbus
A321 aircraft, the operator discovered that a
bearing of the flap track No. 1 pendulum
assembly had migrated out of position. The
investigation has confirmed that the
pendulum bearing migration was probably
due to the methods used during in-service
replacement of the bearing during
maintenance, whereby the necessary special
tools, fixtures and equipment were not used.
This condition, if not corrected, could lead
to separation of the bearing/flap track
assembly, resulting in the detachment of the
affected flap surface from the wing and
consequent loss of control of the aircraft.
For the reasons described above, this AD
requires a one-time inspection of the affected
flap track No.1 pendulum assembly for
bearing migration and, in case any bearing is
found to have migrated, the replacement of
the affected flap track pendulum assembly.
Note: Based on this in-service experience,
showing the potential safety effect of not
following the TC Holder’s accomplishment
instructions, Airbus has removed the
instructions to replace the bearing in the
pendulum assembly from the A320 Family
aircraft maintenance documentation.
Component Maintenance Manual (CMM)
references are 27–54–43 for the A318, A319
and A320, and 27–54–42 for the A321.
If no migration is found during the onetime inspection for migration, the
required actions include an inspection
for correct swaging of the spherical
bearing in the No.1 flap track pendulum
assembly. If the bearing is found
incorrectly swaged, the corrective
actions include contacting Airbus for
repair instructions and doing the repair.
You may obtain further information by
examining the MCAI in the AD docket.
mstockstill on PROD1PC66 with RULES
Relevant Service Information
Airbus has issued Service Bulletin
A320–57–1144, including Appendix 01,
Revision 01, dated June 18, 2007; and
Service Bulletin A320–57A1146,
including Appendix 01, dated
September 21, 2007. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
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17:57 Apr 20, 2009
Jkt 217001
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Differences Between the 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 FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because of the possible separation
of the bearing and flap track assembly,
resulting in the detachment of the
affected flap surface from the wing and
consequent loss of control of the
airplane. Therefore, we determined that
notice and opportunity for public
comment before issuing this AD are
impracticable and that good cause exists
for making this amendment effective in
fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2009–0360;
Directorate Identifier 2009–NM–039–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
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18119
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Federal Register / Vol. 74, No. 75 / Tuesday, April 21, 2009 / Rules and Regulations
dated September 21, 2007 (for Model A318,
A319 and A320 series airplanes); or in
accordance with Airbus Service Bulletin
A320–57A1144, dated February 6, 2007, or
A320–57–1144, Revision 01, dated June 18,
2007 (for Model A321 series airplanes), and
on which it can be positively determined
from a records review that thereafter no
pendulum bearing replacement or re-swaging
was performed.
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
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:
■
2009–09–01 Airbus: Amendment 39–15887.
Docket No. FAA–2009–0360; Directorate
Identifier 2009–NM–039–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective May 6, 2009.
mstockstill on PROD1PC66 with RULES
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318–
111, A318–112, A318–121, A318–122, A319–
111, A319–112, A319–113, A319–114, A319–
115, A319–131, A319–132, A319–133, A320–
111, A320–211, A320–212, A320–214, A320–
231, A320–232, A320–233, A321–111, A321–
112, A321–131, A321–211, A321–212, A321–
213, A321–231, and A321–232 airplanes;
certificated in any category; except airplanes
identified in paragraph (c)(1), (c)(2), (c)(3), or
(c)(4) of this AD.
(1) Any airplane for which the date of
issuance of the original French or German
airworthiness certificate or the date of
issuance of the original French or German
export certificate of airworthiness, is after
February 24, 2009 (the effective date of
European Aviation Safety Agency (EASA)
Airworthiness Directive 2009–0025
[Corrected: February 11, 2009]).
(2) Any airplane for which it can be
positively determined from records review
that the bearing of any pendulum assembly
has not been replaced or re-swaged since the
date of issuance of the original French or
German airworthiness certificate or the date
of issuance of the original French or German
export certificate of airworthiness.
(3) Any airplane inspected prior to the
effective date of this AD in accordance with
Airbus Service Bulletin A320–57A1146,
dated September 21, 2007 (for Model A318,
A319 and A320 series airplanes); or in
accordance with Airbus Service Bulletin
A320–57A1144, dated February 6, 2007, or
A320–57–1144, Revision 01, dated June 18,
2007 (for Model A321 series airplanes), and
on which it can be positively determined
from a records review that thereafter no
replacement with a pendulum assembly
whose bearing has been replaced or reswaged since new manufacture was
performed.
(4) Any airplane inspected prior to the
effective date of this AD in accordance with
Airbus Service Bulletin A320–57A1146,
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17:57 Apr 20, 2009
Jkt 217001
Subject
(d) Air Transport Association (ATA) of
America Code 57: Wings.
Reason
(e) The mandatory continued airworthiness
information (MCAI) states:
During a routine inspection on an Airbus
A321 aircraft, the operator discovered that a
bearing of the flap track No.1 pendulum
assembly had migrated out of position. The
investigation has confirmed that the
pendulum bearing migration was probably
due to the methods used during in-service
replacement of the bearing during
maintenance, whereby the necessary special
tools, fixtures and equipment were not used.
This condition, if not corrected, could lead
to separation of the bearing/flap track
assembly, resulting in the detachment of the
affected flap surface from the wing and
consequent loss of control of the aircraft.
For the reasons described above, this AD
requires a one-time inspection of the affected
flap track No.1 pendulum assembly for
bearing migration and, in case any bearing is
found to have migrated, the replacement of
the affected flap track pendulum assembly.
Note: Based on this in-service experience,
showing the potential safety effect of not
following the TC Holder’s accomplishment
instructions, Airbus has removed the
instructions to replace the bearing in the
pendulum assembly from the A320 Family
aircraft maintenance documentation.
Component Maintenance Manual (CMM)
references are 27–54–43 for the A318, A319
and A320, and 27–54–42 for the A321.
If no migration is found during the one-time
inspection for migration, the required actions
include an inspection for correct swaging of
the spherical bearing in the No.1 flap track
pendulum assembly. If the bearing is found
incorrectly swaged, the corrective actions
include contacting Airbus for repair
instructions and doing the repair. You may
obtain further information by examining the
MCAI in the AD docket.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Within 600 flight hours after the
effective date of this AD, inspect for
migration, and correct swaging as applicable,
of the pendulum assembly of flap track
number 1 in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57A1146, dated
September 21, 2007 (for Model A318, A319
and A320 series airplanes); or in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–57–1144,
Revision 01, dated June 18, 2007 (for Model
A321 series airplanes).
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(i) If the bearing of the pendulum assembly
of flap track number 1 is found to have
migrated, before further flight, replace the
affected pendulum assembly with a new
pendulum assembly, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57A1146, dated
September 21, 2007 (for Model A318, A319
and A320 series airplanes); or in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–57–1144,
Revision 01, dated June 18, 2007 (for Model
A321 series airplanes).
(ii) If the bearing of the pendulum
assembly of flap track number 1 is incorrectly
swaged, before further flight, contact Airbus
for repair instructions and accomplish the
repair.
(2) After the effective date of this AD, no
person shall replace the bearing in the
pendulum assembly of the flap track or
install a pendulum assembly, unless:
(i) The pendulum assembly is of new
manufacture, or
(ii) It can be positively determined from a
records review that the bearing of the
pendulum assembly has not been replaced or
re-swaged since new.
(3) Accomplishment of the actions required
by paragraph (f)(1), (f)(2), and (f)(3) of this
AD, before the effective date of this AD in
accordance with Airbus Service Bulletin
A320–57A1144, dated February 6, 2007, is
acceptable for compliance with the
corresponding requirements of paragraph (f)
of this AD for Airbus Model A321 series
airplanes.
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: Tim Dulin,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2141; 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,
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21APR1
Federal Register / Vol. 74, No. 75 / Tuesday, April 21, 2009 / Rules and Regulations
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 MCAI European Aviation
Safety Agency Airworthiness Directive 2009–
0025, dated February 10, 2009; Airbus
Service Bulletin A320–57–1144, Revision 01,
dated June 18, 2007; and Airbus Service
Bulletin A320–57A1146, dated September
21, 2007, for related information.
Material Incorporated by Reference
(i) You must use Airbus Service Bulletin
A320–57A1146, including Appendix 01,
dated September 21, 2007; or Airbus Service
Bulletin A320–57–1144, including Appendix
01, Revision 01, dated June 18, 2007; 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, Airworthiness
Office—EAS, 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 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.
Issued in Renton, Washington, on April 8,
2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–8982 Filed 4–20–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0361; Directorate
Identifier 2009–NM–046–AD; Amendment
39–15888; AD 2009–09–02]
mstockstill on PROD1PC66 with RULES
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
VerDate Nov<24>2008
17:57 Apr 20, 2009
Jkt 217001
ACTION: Final rule; request for
comments.
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:
Several reports have been received on
failures of the aft hinge of the main landing
gear (MLG) forward stabilizer brace.
Laboratory examinations have found that the
fatigue cracks were initiated from the dowel
pin hole at the aft hinge lug of the MLG
forward stabilizer brace where the stop
bracket is attached. Failure of the stabilizer
brace could result in the collapse of the main
landing gear.
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective May
6, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of May 6, 2009.
We must receive comments on this
AD by May 21, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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 this AD, 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.
FOR FURTHER INFORMATION CONTACT: Jon
Hjelm, Aerospace Engineer, Airframe
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
18121
and Propulsion Branch, ANE–171, FAA,
New York Aircraft Certification Office,
1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone
(516) 228–7323; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Emergency Airworthiness Directive CF–
2009–11, dated March 13, 2009 (referred
to after this as ‘‘the MCAI’’), to correct
an unsafe condition for the specified
products. The MCAI states:
Several reports have been received on
failures of the aft hinge of the main landing
gear (MLG) forward stabilizer brace.
Laboratory examinations have found that the
fatigue cracks were initiated from the dowel
pin hole at the aft hinge lug of the MLG
forward stabilizer brace where the stop
bracket is attached. Failure of the stabilizer
brace could result in the collapse of the main
landing gear.
Required actions include inspections for
damage (including excessive wear,
corrosion, foreign object damage, and
cracking) of the MLG forward stabilizer
brace assemblies and applicable
corrective actions. The inspections
include the following inspections:
• A visual inspection for evidence of
excessive wear on the outside diameter
of apex pins part number 46418–1.
• A visual inspection for damage
(including cracking, corrosion, and
foreign object damage) of the face of the
forward stabilizer brace lugs, stop
bracket retention hole apex bushings,
and stop bracket.
• An inspection to detect 0.050-inchlong exposed surface cracks around the
stop bracket mounting face and
retention pin hole areas, using either of
the following nondestructive inspection
methods: (1) An eddy current
inspection, or (2) a visual inspection
using liquid penetrant under 10X
magnification.
The applicable corrective actions
include the following:
• Contacting Goodrich for repair
instructions and doing the repair.
• Replacing the stop bracket.
• Reworking the forward stabilizer
brace assembly.
• Replacing the forward stabilizer
brace assembly.
The required actions also include, for
certain airplanes, repetitive detailed
visual inspection for cracking of both
MLG forward stabilizer braces,
including liquid penetrant inspections
for cracking if necessary, and repair of
the cracking if necessary. The required
actions also include, for certain
airplanes, a detailed visual inspection
E:\FR\FM\21APR1.SGM
21APR1
]]>Agencies
[Federal Register Volume 74, Number 75 (Tuesday, April 21, 2009)]
[Rules and Regulations]
[Pages 18118-18121]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-8982]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0360; Directorate Identifier 2009-NM-039-AD;
Amendment 39-15887; AD 2009-09-01]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A318, A319, A320 and A321
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
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:
During a routine inspection on an Airbus A321 aircraft, the
operator discovered that a bearing of the flap track No. 1 pendulum
assembly had migrated out of position. * * * This condition, if not
corrected, could lead to separation of the bearing/flap track
assembly, resulting in the detachment of the affected flap surface
from the wing and consequent loss of control of the aircraft.
* * * * *
This AD requires actions that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective May 6, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of May 6, 2009.
We must receive comments on this AD by May 21, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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 this AD, 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.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
[[Page 18119]]
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency (EASA) which is the Technical
Agent of the Member States of the European Community, has issued EASA
Airworthiness Directive 2009-0025, dated February 10, 2009 [Corrected
February 11, 2009] (referred to after this as ``the MCAI''), to correct
an unsafe condition for the specified products. The MCAI states:
During a routine inspection on an Airbus A321 aircraft, the
operator discovered that a bearing of the flap track No. 1 pendulum
assembly had migrated out of position. The investigation has
confirmed that the pendulum bearing migration was probably due to
the methods used during in-service replacement of the bearing during
maintenance, whereby the necessary special tools, fixtures and
equipment were not used. This condition, if not corrected, could
lead to separation of the bearing/flap track assembly, resulting in
the detachment of the affected flap surface from the wing and
consequent loss of control of the aircraft.
For the reasons described above, this AD requires a one-time
inspection of the affected flap track No.1 pendulum assembly for
bearing migration and, in case any bearing is found to have
migrated, the replacement of the affected flap track pendulum
assembly.
Note: Based on this in-service experience, showing the potential
safety effect of not following the TC Holder's accomplishment
instructions, Airbus has removed the instructions to replace the
bearing in the pendulum assembly from the A320 Family aircraft
maintenance documentation. Component Maintenance Manual (CMM)
references are 27-54-43 for the A318, A319 and A320, and 27-54-42
for the A321.
If no migration is found during the one-time inspection for migration,
the required actions include an inspection for correct swaging of the
spherical bearing in the No.1 flap track pendulum assembly. If the
bearing is found incorrectly swaged, the corrective actions include
contacting Airbus for repair instructions and doing the repair. You may
obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletin A320-57-1144, including Appendix
01, Revision 01, dated June 18, 2007; and Service Bulletin A320-
57A1146, including Appendix 01, dated September 21, 2007. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between the 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 FAA policies. Any such differences are
highlighted in a NOTE within the AD.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because of
the possible separation of the bearing and flap track assembly,
resulting in the detachment of the affected flap surface from the wing
and consequent loss of control of the airplane. Therefore, we
determined that notice and opportunity for public comment before
issuing this AD are impracticable and that good cause exists for making
this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2009-0360; Directorate
Identifier 2009-NM-039-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 18120]]
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:
2009-09-01 Airbus: Amendment 39-15887. Docket No. FAA-2009-0360;
Directorate Identifier 2009-NM-039-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 6,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A318-111, A318-112, A318-
121, A318-122, A319-111, A319-112, A319-113, A319-114, A319-115,
A319-131, A319-132, A319-133, A320-111, A320-211, A320-212, A320-
214, A320-231, A320-232, A320-233, A321-111, A321-112, A321-131,
A321-211, A321-212, A321-213, A321-231, and A321-232 airplanes;
certificated in any category; except airplanes identified in
paragraph (c)(1), (c)(2), (c)(3), or (c)(4) of this AD.
(1) Any airplane for which the date of issuance of the original
French or German airworthiness certificate or the date of issuance
of the original French or German export certificate of
airworthiness, is after February 24, 2009 (the effective date of
European Aviation Safety Agency (EASA) Airworthiness Directive 2009-
0025 [Corrected: February 11, 2009]).
(2) Any airplane for which it can be positively determined from
records review that the bearing of any pendulum assembly has not
been replaced or re-swaged since the date of issuance of the
original French or German airworthiness certificate or the date of
issuance of the original French or German export certificate of
airworthiness.
(3) Any airplane inspected prior to the effective date of this
AD in accordance with Airbus Service Bulletin A320-57A1146, dated
September 21, 2007 (for Model A318, A319 and A320 series airplanes);
or in accordance with Airbus Service Bulletin A320-57A1144, dated
February 6, 2007, or A320-57-1144, Revision 01, dated June 18, 2007
(for Model A321 series airplanes), and on which it can be positively
determined from a records review that thereafter no replacement with
a pendulum assembly whose bearing has been replaced or re-swaged
since new manufacture was performed.
(4) Any airplane inspected prior to the effective date of this
AD in accordance with Airbus Service Bulletin A320-57A1146, dated
September 21, 2007 (for Model A318, A319 and A320 series airplanes);
or in accordance with Airbus Service Bulletin A320-57A1144, dated
February 6, 2007, or A320-57-1144, Revision 01, dated June 18, 2007
(for Model A321 series airplanes), and on which it can be positively
determined from a records review that thereafter no pendulum bearing
replacement or re-swaging was performed.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continued airworthiness information (MCAI)
states:
During a routine inspection on an Airbus A321 aircraft, the
operator discovered that a bearing of the flap track No.1 pendulum
assembly had migrated out of position. The investigation has
confirmed that the pendulum bearing migration was probably due to
the methods used during in-service replacement of the bearing during
maintenance, whereby the necessary special tools, fixtures and
equipment were not used. This condition, if not corrected, could
lead to separation of the bearing/flap track assembly, resulting in
the detachment of the affected flap surface from the wing and
consequent loss of control of the aircraft.
For the reasons described above, this AD requires a one-time
inspection of the affected flap track No.1 pendulum assembly for
bearing migration and, in case any bearing is found to have
migrated, the replacement of the affected flap track pendulum
assembly.
Note: Based on this in-service experience, showing the potential
safety effect of not following the TC Holder's accomplishment
instructions, Airbus has removed the instructions to replace the
bearing in the pendulum assembly from the A320 Family aircraft
maintenance documentation. Component Maintenance Manual (CMM)
references are 27-54-43 for the A318, A319 and A320, and 27-54-42
for the A321.
If no migration is found during the one-time inspection for
migration, the required actions include an inspection for correct
swaging of the spherical bearing in the No.1 flap track pendulum
assembly. If the bearing is found incorrectly swaged, the corrective
actions include contacting Airbus for repair instructions and doing
the repair. You may obtain further information by examining the MCAI
in the AD docket.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) Within 600 flight hours after the effective date of this AD,
inspect for migration, and correct swaging as applicable, of the
pendulum assembly of flap track number 1 in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57A1146,
dated September 21, 2007 (for Model A318, A319 and A320 series
airplanes); or in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-57-1144, Revision 01, dated June 18,
2007 (for Model A321 series airplanes).
(i) If the bearing of the pendulum assembly of flap track number
1 is found to have migrated, before further flight, replace the
affected pendulum assembly with a new pendulum assembly, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-57A1146, dated September 21, 2007 (for Model A318,
A319 and A320 series airplanes); or in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-57-1144,
Revision 01, dated June 18, 2007 (for Model A321 series airplanes).
(ii) If the bearing of the pendulum assembly of flap track
number 1 is incorrectly swaged, before further flight, contact
Airbus for repair instructions and accomplish the repair.
(2) After the effective date of this AD, no person shall replace
the bearing in the pendulum assembly of the flap track or install a
pendulum assembly, unless:
(i) The pendulum assembly is of new manufacture, or
(ii) It can be positively determined from a records review that
the bearing of the pendulum assembly has not been replaced or re-
swaged since new.
(3) Accomplishment of the actions required by paragraph (f)(1),
(f)(2), and (f)(3) of this AD, before the effective date of this AD
in accordance with Airbus Service Bulletin A320-57A1144, dated
February 6, 2007, is acceptable for compliance with the
corresponding requirements of paragraph (f) of this AD for Airbus
Model A321 series airplanes.
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: Tim
Dulin, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2141; 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,
[[Page 18121]]
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 MCAI European Aviation Safety Agency Airworthiness
Directive 2009-0025, dated February 10, 2009; Airbus Service
Bulletin A320-57-1144, Revision 01, dated June 18, 2007; and Airbus
Service Bulletin A320-57A1146, dated September 21, 2007, for related
information.
Material Incorporated by Reference
(i) You must use Airbus Service Bulletin A320-57A1146, including
Appendix 01, dated September 21, 2007; or Airbus Service Bulletin
A320-57-1144, including Appendix 01, Revision 01, dated June 18,
2007; 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, Airworthiness Office--EAS, 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 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.
Issued in Renton, Washington, on April 8, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-8982 Filed 4-20-09; 8:45 am]
BILLING CODE 4910-13-P
