Airworthiness Directives; Airbus Model A321 Series Airplanes, 16167-16170 [05-6243]
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Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules
Installation of System Preventing Excessive
Lowering of Power Levers in Flight
(g) Within 2 years after March 1, 2000,
install a system that would prevent
positioning the power levers below the flight
idle stop during flight, in accordance with a
method approved by the Manager, New York
Aircraft Certification Office (ACO), FAA.
Following accomplishment of that
installation, the placard required by
paragraph (f) of this AD may be removed.
(h) In the event that the system required by
paragraph (g) of this AD malfunctions, or if
the use of an override (if installed) is
necessary, the airplane may be operated for
three days to a location where required
maintenance/repair can be performed,
provided the system required by paragraph
(g) of this AD has been properly deactivated
and placarded for flightcrew awareness, in
accordance with the FAA-approved Master
Minimum Equipment List (MMEL).
New Requirements
Bulletin 8–76–24: Within 50 flight hours after
the effective date of this AD, perform an
operational check of the beta lockout system
in accordance with the applicable de
Havilland, Inc., Dash 8 task card listed in
Table 1 of this AD. Thereafter repeat the
operational check at intervals specified in the
applicable de Havilland, Inc., temporary
revision (TR) listed in Table 2 of this AD.
Operational Checks of the Beta Lockout
System
(i) For airplanes that have been modified
in accordance with Bombardier Service
TABLE 1.—TASK CARDS
DHC–8 Model
de Havilland, Inc., task card
–101, –102, –103, and –106 airplanes .........
–201 and –202 airplanes ..............................
–301, –311, and –315 airplanes ...................
Dash 8 Series 100 Maintenance Task Card 6120/10 .................................
Dash 8 Series 200 Maintenance Task Card 6120/10 .................................
Dash 8 Series 300 Maintenance Task Card 6120/10 .................................
Revision of Airworthiness Limitations
(AWL) Section
(j) Within 30 days after the effective date
of this AD, revise the AWL section of the
applicable Instructions for Continued
Airworthiness by incorporating the contents
of the applicable de Havilland, Inc., TR listed
in Table 2 of this AD into the AWL section
Date
November 21, 2003.
November 21, 2003.
November 21, 2003.
of the applicable Bombardier DHC–8
Maintenance Program Support Manual
(PSM).
TABLE 2.—TRS
DHC–8 Model
de Havilland, Inc., TR
Dated
For PSM
–101, –102, –103, and –106 airplanes ..........................................
–201 and –202 airplanes ...............................................................
–301, –311, and –315 airplanes ....................................................
AWL–86 ....................................
AWL 2–26 .................................
AWL 3–93 .................................
March 17, 2003 .........................
March 17, 2003 .........................
March 17, 2003 .........................
1–8–7
1–82–7
1–83–7
(k) When the information in the applicable
de Havilland, Inc., TR identified in Table 2
of this AD has been included in the general
revisions of the applicable PSM identified in
Table 2 of this AD, the general revisions may
be inserted in the PSM, and the applicable
TR may be removed from the AWL section
of the Instruction for Continued
Airworthiness.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, New York ACO has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) AMOCS approved previously in
accordance with AD 2000–02–13 are
acceptable for the corresponding
requirements of this AD.
Related Information
(m) None.
Issued in Renton, Washington, on March
17, 2005.
Jeffery E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–6241 Filed 3–29–05; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20755; Directorate
Identifier 2004–NM–244–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A321 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Airbus
Model A321 series airplanes. The
existing AD currently requires revising
the Limitations section of the airplane
flight manual to include an instruction
to use Flap 3 for landing when
performing an approach in conditions of
moderate to severe icing, significant
crosswind (i.e., crosswinds greater than
20 knots, gust included), or moderate to
severe turbulence. This proposed AD
would require replacing existing
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elevator and aileron computers (ELAC)
with ELACs having either L83 or L91
software, as applicable, which would
terminate the requirements of the
existing AD. This proposed AD would
also require a related concurrent action.
In addition, this proposed AD would
revise the applicability by removing
airplanes with these ELAC software
standards incorporated in production.
This proposed AD is prompted by
issuance of mandatory continuing
airworthiness information by a civil
airworthiness authority. We are
proposing this AD to prevent roll
oscillations during approach and
landing in certain icing, crosswind, and
turbulent conditions, which could result
in reduced controllability of the
airplane.
We must receive comments on
this proposed AD by April 29, 2005.
DATES:
Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
ADDRESSES:
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Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20755; the directorate identifier for this
docket is 2004–NM–244–AD.
FOR FURTHER INFORMATION CONTACT: Tim
Dulin, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2141;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20755; Directorate Identifier
2004–NM–244–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of our docket
web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You can
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
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19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can examine the AD docket on
the Internet at https://dms.dot.gov, or in
person at the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
Discussion
On January 28, 2004, we issued AD
2004–03–02, amendment 39–13446 (69
FR 5007, February 3, 2004), for all
Airbus Model A321 series airplanes.
That AD requires revising the
Limitations section of the airplane flight
manual to include an instruction to use
Flap 3 for landing when performing an
approach in conditions of moderate to
severe icing, significant crosswind (i.e.,
crosswinds greater than 20 knots, gust
included), or moderate to severe
turbulence. That AD was prompted by
reports indicating that pilots of two
separate Model A321 series airplanes
encountered lateral handling
difficulties, which led to roll
oscillations. We issued that AD to
prevent roll oscillations during
approach and landing in certain icing,
crosswind, and turbulent conditions,
which could result in reduced
controllability of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2004–03–02, the
´ ´
Direction Generale de l’Aviation Civile
(DGAC), which is the airworthiness
authority for France, issued French
airworthiness directive F–2004–147,
dated August 18, 2004. The French
airworthiness directive mandates the
installation of elevator aileron
computers (ELAC) having L83 or L91
software, as applicable, and cancels the
revision to the Limitations section of the
airplane flight manual. The French
airworthiness directive also revises the
applicability by removing airplanes on
which Airbus Modification 34043 was
installed in production.
Relevant Service Information
Airbus has issued Service Bulletins
A320–27–1151, including Appendix 01,
dated March 9, 2004; and A320–27–
1152, including Appendix 01, dated
June 4, 2004. Service Bulletin A320–27–
1151 describes procedures for replacing
existing ELACs with ELACs having L83
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software, and Service Bulletin A320–
27–1152 describes procedures for
replacing existing ELACs with ELACs
having L91 software. Accomplishing the
actions specified in the service
information is intended to adequately
address the unsafe condition. The
DGAC mandated the service information
and issued French airworthiness
directive F–2004–147, dated August 18,
2004, to ensure the continued
airworthiness of these airplanes in
France.
Airbus Service Bulletin A320–27–
1151 refers to Thales Service Bulletin
394512–27–026, dated March 5, 2004, as
an additional source of service
information for installing ELAC L83
software. Airbus Service Bulletin A320–
27–1152 refers to Thales Service
Bulletin 394512B–27–010, dated May
24, 2004, as an additional source of
service information for installing ELAC
L91 software.
Concurrent Service Bulletin
Airbus Service Bulletins A320–27–
1151 and A320–27–1152 recommend
prior or concurrent accomplishment of
Airbus Service Bulletin A320–27–1135,
Revision 02, dated April 18, 2002.
Airbus Service Bulletin A320–27–1135,
Revision 02, describes procedures for
installing ELACs having L81 software.
Airbus Service Bulletin A320–27–1135,
Revision 02, refers to Thales Service
Bulletins 394512–27–022, Revision 01,
dated June 4, 2004; and 394512B–27–
002, Revision 01, dated July 16, 2002; as
additional sources of service
information for installing L81 software
in the ELACs.
FAA’s Determination and Requirements
of the Proposed AD
This airplane model is manufactured
in France and is type certificated for
operation in the United States under the
provisions of § 21.29 of the Federal
Aviation Regulations (14 CFR 21.29)
and the applicable bilateral
airworthiness agreement. According to
this bilateral airworthiness agreement,
the DGAC has kept the FAA informed
of the situation described above. We
have examined the DGAC’s findings,
evaluated all pertinent information, and
determined that AD action is necessary
for airplanes of this type design that are
certificated for operation in the United
States. This proposed AD would
supersede AD 2004–03–02. This
proposed AD would continue to require
revising the airplane flight manual to
specify procedures for landing under
certain conditions of icing, significant
crosswind, or moderate to severe
turbulence, until the new requirements
of this AD have been accomplished.
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Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Proposed Rules
This proposed AD would also require
replacing existing ELAC computers with
ELAC computers having L83 or L91
software, as applicable, which would
terminate the requirements of the
existing AD. This proposed AD would
also require a related concurrent action.
In addition, this proposed AD would
revise the applicability by removing
airplanes with these ELAC software
standards incorporated during
production. The actions would be
required to be accomplished in
accordance with the service information
described previously.
Clarification of Terminology
Concurrent Airbus Service Bulletin
A320–27–1135 refers to ‘‘ELAC standard
L81.’’ This AD uses the term ‘‘L81
software.’’
Change to Existing AD
This proposed AD would retain all
requirements of AD 2004–03–02. Since
AD 2004–03–02 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
Action
Average
labor rate per
hour
Work hour
Parts
identifier has changed in this proposed
AD, as listed in the following table:
REVISED PARAGRAPH IDENTIFIER
Requirement in AD
2004–03–02
paragraph (a) ............
Corresponding
requirement in this
proposed AD
paragraph (f).
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
Number of
U.S.-registered airplanes
Cost per
airplane
Fleet cost
Estimated Costs
AFM revision (required by AD 2004–03–02) ......
Installation of ELAC having L83 or L91 software
(new proposed action).
1
1
$65
65
None ............
No charge ....
$65
65
29
29
$1,885
1,885
65
29
1,885
Estimated Concurrent Service Bulletin Costs
Installation of ELAC having L81 software ...........
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
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1
65
No charge ....
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–13446 (69 FR
5007, February 3, 2004) and adding the
following new airworthiness directive
(AD):
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Airbus: Docket No. FAA–2005–20755;
Directorate Identifier 2004–NM–244–AD.
Comments Due Date
(a) The Federal Aviation Administration
must receive comments on this AD action by
April 29, 2005.
Affected ADs
(b) This AD supersedes AD 2004–03–02,
amendment 39–13446 (69 FR 5007, February
3, 2004).
Applicability
(c) This AD applies to Airbus Model A321
series airplanes, certificated in any category,
except those with Airbus Modification 34043
installed in production.
Unsafe Condition
(d) This AD was prompted by issuance of
mandatory continuing airworthiness
information by a civil airworthiness
authority. We are issuing this AD to prevent
roll oscillations during approach and landing
in certain icing, crosswind, and turbulent
conditions, which could result in reduced
controllability of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2004–
03–02
Airplane Flight Manual Revision
(f) Within 10 days after February 18, 2004
(the effective date of AD 2004–03–02), revise
the Limitations section of the airplane flight
manual (AFM) to include the following
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statement. This may be done by inserting a
copy of this AD in the AFM.
‘‘A321 APPROACH AND LANDING (ROLL
CONTROL) When moderate to severe icing
conditions, or significant cross wind (i.e.,
crosswinds greater than 20 knots, gust
included), or moderate to severe turbulence
are anticipated:
Use FLAP 3 for landing.’’
Note 1: When a statement identical to that
in paragraph (f) of this AD has been included
in the general revisions of the AFM, the
general revisions may be inserted into the
AFM, and the copy of this AD may be
removed from the AFM.
New Requirements of This AD
Installation of Elevator Aileron Computers
(ELAC) Having L83 or L91 Software
(g) Within 16 months after the effective
date of this AD: Replace existing ELACs with
ELACs having L83 software, by
accomplishing all of the actions specified in
the Accomplishment Instructions of Airbus
Service Bulletin A320–27–1151, including
Appendix 01, dated March 9, 2004; or with
ELACs having L91 software, by
accomplishing all of the actions specified in
the Accomplishment Instructions of Airbus
Service Bulletin A320–27–1152, including
Appendix 01, dated June 4, 2004; as
applicable. After accomplishing the ELAC
replacements, remove the AFM revision
required by paragraph (f) of this AD.
Accomplishing the requirements of this
paragraph terminates the requirements of
paragraph (f) of this AD.
Note 2: Airbus Service Bulletin A320–27–
1151 refers to Thales Service Bulletin
394512–27–026, dated March 5, 2004, as an
additional source of service information for
installing ELAC L83 software. Airbus Service
Bulletin A320–27–1152 refers to Thales
Service Bulletin 394512B–27–010, dated May
24, 2004, as an additional source of service
information for installing ELAC L91 software.
Concurrent Service Bulletin
(h) Prior to doing the requirements of
paragraph (g) of this AD: Install ELACs
having L81 software in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1135, Revision 02,
dated April 18, 2002.
Previously Accomplished Actions in
Concurrent Service Bulletin
(i) Installation of ELACs having L81
software in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1135, dated June
29, 2001; or Service Bulletin A320–27–1135,
Revision 01, dated August 31, 2001; is
acceptable for compliance with the
requirements of paragraph (h) of this AD.
Part Installation
(j) As of the effective date of this AD, no
person may install on any airplane an ELAC,
part number 3945122506, 3945123506,
3945128102, or 3945128103.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, International Branch,
Transport Airplane Directorate, FAA, has the
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authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Alternative methods of compliance,
approved previously in accordance with AD
2004–03–02, are approved as alternative
methods of compliance with the
corresponding requirements of this AD.
Related Information
(l) French airworthiness directive F–2004–
147, dated August 18, 2004, also addresses
the subject of this AD.
Issued in Renton, Washington, on March
22, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–6243 Filed 3–29–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20727; Directorate
Identifier 2004–NM–148–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400, –401, and –402
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier Model DHC–8–400,
–401, and –402 airplanes. This proposed
AD would require repetitive inspections
to detect discrepancies of the
attachment fittings of the outboard flap
front spar at flap track Number 4 and
Number 5 locations, and corrective
actions if necessary. This proposed AD
also would require eventual
replacement of the attachment fittings as
terminating action for the repetitive
inspections. This proposed AD is
prompted by the discovery of several
airplanes that have loose flap front spar
attachment fittings at flap track Number
4 and Number 5 locations. We are
proposing this AD to prevent the
attachment fittings from becoming
detached, and consequent loss of
control of the airplane.
DATES: We must receive comments on
this proposed AD by April 29, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
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instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• By fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Bombardier,
Inc., Bombardier Regional Aircraft
Division, 123 Garratt Boulevard,
Downsview, Ontario M3K 1Y5, Canada.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20727; the directorate identifier for this
docket is 2004–NM–148–AD.
FOR FURTHER INFORMATION CONTACT:
David A. Lawson, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, suite 410, Westbury, New York
11590; telephone (516) 228–7327; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written
relevant data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20727; Directorate Identifier
2004–NM–148–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments submitted by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of our docket
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
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]]>Agencies
[Federal Register Volume 70, Number 60 (Wednesday, March 30, 2005)]
[Proposed Rules]
[Pages 16167-16170]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6243]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20755; Directorate Identifier 2004-NM-244-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A321 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Airbus Model A321 series airplanes.
The existing AD currently requires revising the Limitations section of
the airplane flight manual to include an instruction to use Flap 3 for
landing when performing an approach in conditions of moderate to severe
icing, significant crosswind (i.e., crosswinds greater than 20 knots,
gust included), or moderate to severe turbulence. This proposed AD
would require replacing existing elevator and aileron computers (ELAC)
with ELACs having either L83 or L91 software, as applicable, which
would terminate the requirements of the existing AD. This proposed AD
would also require a related concurrent action. In addition, this
proposed AD would revise the applicability by removing airplanes with
these ELAC software standards incorporated in production. This proposed
AD is prompted by issuance of mandatory continuing airworthiness
information by a civil airworthiness authority. We are proposing this
AD to prevent roll oscillations during approach and landing in certain
icing, crosswind, and turbulent conditions, which could result in
reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by April 29, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov
[[Page 16168]]
and follow the instructions for sending your comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-20755; the directorate identifier for this docket is
2004-NM-244-AD.
FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2141; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20755;
Directorate Identifier 2004-NM-244-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
On January 28, 2004, we issued AD 2004-03-02, amendment 39-13446
(69 FR 5007, February 3, 2004), for all Airbus Model A321 series
airplanes. That AD requires revising the Limitations section of the
airplane flight manual to include an instruction to use Flap 3 for
landing when performing an approach in conditions of moderate to severe
icing, significant crosswind (i.e., crosswinds greater than 20 knots,
gust included), or moderate to severe turbulence. That AD was prompted
by reports indicating that pilots of two separate Model A321 series
airplanes encountered lateral handling difficulties, which led to roll
oscillations. We issued that AD to prevent roll oscillations during
approach and landing in certain icing, crosswind, and turbulent
conditions, which could result in reduced controllability of the
airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2004-03-02, the Direction G[eacute]n[eacute]rale
de l'Aviation Civile (DGAC), which is the airworthiness authority for
France, issued French airworthiness directive F-2004-147, dated August
18, 2004. The French airworthiness directive mandates the installation
of elevator aileron computers (ELAC) having L83 or L91 software, as
applicable, and cancels the revision to the Limitations section of the
airplane flight manual. The French airworthiness directive also revises
the applicability by removing airplanes on which Airbus Modification
34043 was installed in production.
Relevant Service Information
Airbus has issued Service Bulletins A320-27-1151, including
Appendix 01, dated March 9, 2004; and A320-27-1152, including Appendix
01, dated June 4, 2004. Service Bulletin A320-27-1151 describes
procedures for replacing existing ELACs with ELACs having L83 software,
and Service Bulletin A320-27-1152 describes procedures for replacing
existing ELACs with ELACs having L91 software. Accomplishing the
actions specified in the service information is intended to adequately
address the unsafe condition. The DGAC mandated the service information
and issued French airworthiness directive F-2004-147, dated August 18,
2004, to ensure the continued airworthiness of these airplanes in
France.
Airbus Service Bulletin A320-27-1151 refers to Thales Service
Bulletin 394512-27-026, dated March 5, 2004, as an additional source of
service information for installing ELAC L83 software. Airbus Service
Bulletin A320-27-1152 refers to Thales Service Bulletin 394512B-27-010,
dated May 24, 2004, as an additional source of service information for
installing ELAC L91 software.
Concurrent Service Bulletin
Airbus Service Bulletins A320-27-1151 and A320-27-1152 recommend
prior or concurrent accomplishment of Airbus Service Bulletin A320-27-
1135, Revision 02, dated April 18, 2002. Airbus Service Bulletin A320-
27-1135, Revision 02, describes procedures for installing ELACs having
L81 software. Airbus Service Bulletin A320-27-1135, Revision 02, refers
to Thales Service Bulletins 394512-27-022, Revision 01, dated June 4,
2004; and 394512B-27-002, Revision 01, dated July 16, 2002; as
additional sources of service information for installing L81 software
in the ELACs.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. According to this
bilateral airworthiness agreement, the DGAC has kept the FAA informed
of the situation described above. We have examined the DGAC's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States. This proposed AD would supersede AD
2004-03-02. This proposed AD would continue to require revising the
airplane flight manual to specify procedures for landing under certain
conditions of icing, significant crosswind, or moderate to severe
turbulence, until the new requirements of this AD have been
accomplished.
[[Page 16169]]
This proposed AD would also require replacing existing ELAC computers
with ELAC computers having L83 or L91 software, as applicable, which
would terminate the requirements of the existing AD. This proposed AD
would also require a related concurrent action. In addition, this
proposed AD would revise the applicability by removing airplanes with
these ELAC software standards incorporated during production. The
actions would be required to be accomplished in accordance with the
service information described previously.
Clarification of Terminology
Concurrent Airbus Service Bulletin A320-27-1135 refers to ``ELAC
standard L81.'' This AD uses the term ``L81 software.''
Change to Existing AD
This proposed AD would retain all requirements of AD 2004-03-02.
Since AD 2004-03-02 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifier has changed in this proposed AD, as listed in the
following table:
Revised Paragraph Identifier
------------------------------------------------------------------------
Corresponding requirement
Requirement in AD 2004-03-02 in this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
------------------------------------------------------------------------
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average Cost per U.S.-
Action Work hour labor rate Parts airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM revision (required by AD 2004-03-02)...... 1 $65 None.............................. $65 29 $1,885
Installation of ELAC having L83 or L91 1 65 No charge......................... 65 29 1,885
software (new proposed action).
-----------------------------------------------
Estimated Concurrent Service Bulletin Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Installation of ELAC having L81 software...... 1 65 No charge......................... 65 29 1,885
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing amendment 39-13446 (69 FR
5007, February 3, 2004) and adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2005-20755; Directorate Identifier 2004-NM-
244-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by April 29, 2005.
Affected ADs
(b) This AD supersedes AD 2004-03-02, amendment 39-13446 (69 FR
5007, February 3, 2004).
Applicability
(c) This AD applies to Airbus Model A321 series airplanes,
certificated in any category, except those with Airbus Modification
34043 installed in production.
Unsafe Condition
(d) This AD was prompted by issuance of mandatory continuing
airworthiness information by a civil airworthiness authority. We are
issuing this AD to prevent roll oscillations during approach and
landing in certain icing, crosswind, and turbulent conditions, which
could result in reduced controllability of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2004-03-02
Airplane Flight Manual Revision
(f) Within 10 days after February 18, 2004 (the effective date
of AD 2004-03-02), revise the Limitations section of the airplane
flight manual (AFM) to include the following
[[Page 16170]]
statement. This may be done by inserting a copy of this AD in the
AFM.
``A321 APPROACH AND LANDING (ROLL CONTROL) When moderate to
severe icing conditions, or significant cross wind (i.e., crosswinds
greater than 20 knots, gust included), or moderate to severe
turbulence are anticipated:
Use FLAP 3 for landing.''
Note 1: When a statement identical to that in paragraph (f) of
this AD has been included in the general revisions of the AFM, the
general revisions may be inserted into the AFM, and the copy of this
AD may be removed from the AFM.
New Requirements of This AD
Installation of Elevator Aileron Computers (ELAC) Having L83 or L91
Software
(g) Within 16 months after the effective date of this AD:
Replace existing ELACs with ELACs having L83 software, by
accomplishing all of the actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1151, including
Appendix 01, dated March 9, 2004; or with ELACs having L91 software,
by accomplishing all of the actions specified in the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1152, including
Appendix 01, dated June 4, 2004; as applicable. After accomplishing
the ELAC replacements, remove the AFM revision required by paragraph
(f) of this AD. Accomplishing the requirements of this paragraph
terminates the requirements of paragraph (f) of this AD.
Note 2: Airbus Service Bulletin A320-27-1151 refers to Thales
Service Bulletin 394512-27-026, dated March 5, 2004, as an
additional source of service information for installing ELAC L83
software. Airbus Service Bulletin A320-27-1152 refers to Thales
Service Bulletin 394512B-27-010, dated May 24, 2004, as an
additional source of service information for installing ELAC L91
software.
Concurrent Service Bulletin
(h) Prior to doing the requirements of paragraph (g) of this AD:
Install ELACs having L81 software in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1135,
Revision 02, dated April 18, 2002.
Previously Accomplished Actions in Concurrent Service Bulletin
(i) Installation of ELACs having L81 software in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-27-
1135, dated June 29, 2001; or Service Bulletin A320-27-1135,
Revision 01, dated August 31, 2001; is acceptable for compliance
with the requirements of paragraph (h) of this AD.
Part Installation
(j) As of the effective date of this AD, no person may install
on any airplane an ELAC, part number 3945122506, 3945123506,
3945128102, or 3945128103.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, International Branch, Transport Airplane
Directorate, FAA, has the authority to approve AMOCs for this AD, if
requested in accordance with the procedures found in 14 CFR 39.19.
(2) Alternative methods of compliance, approved previously in
accordance with AD 2004-03-02, are approved as alternative methods
of compliance with the corresponding requirements of this AD.
Related Information
(l) French airworthiness directive F-2004-147, dated August 18,
2004, also addresses the subject of this AD.
Issued in Renton, Washington, on March 22, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-6243 Filed 3-29-05; 8:45 am]
BILLING CODE 4910-13-P
