Airworthiness Directives; AeroSpace Technologies of Australia Pty Ltd. Models N22B, N22S, and N24A Airplanes, 61636-61639 [E6-17425]
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61636
Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25928; Directorate
Identifier 2006–CE–53–AD; Amendment 39–
14797; AD 2006–21–12]
RIN 2120–AA64
Airworthiness Directives; AeroSpace
Technologies of Australia Pty Ltd.
Models N22B, N22S, and N24A
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for comments
PWALKER on PRODPC60 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) to
supersede AD 2003–22–13, which
applies to all AeroSpace Technologies
of Australia Pty Ltd. (ASTA) Models
N22B and N24A airplanes. AD 2003–
22–13 currently requires you to visually
inspect the ailerons for damage and
replace if necessary; adjust the engine
power levers aural warning
microswitches; set flap extension and
flap down operation limitations; and
fabricate and install cockpit flap
extension and flap down operation
restriction placards. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by the airworthiness authority for
Australia. The FAA inadvertently
omitted Model N22S airplanes from the
applicability of AD 2003–22–13.
Therefore, this AD retains the actions
exactly as required in AD 2003–22–13
and adds Model N22S airplanes to the
Applicability section. We are issuing
this AD to prevent failure of the aileron
due to undetected pre-existing aileron
damage and airplane operation outside
of the approved limits. Aileron failure
could lead to reduced or loss of control
of the airplane.
DATES: This AD becomes effective on
November 8, 2006.
As of November 8, 2006, the Director
of the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
We must receive any comments on
this AD by November 20, 2006.
ADDRESSES: Use one of the following to
comment on this 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
and follow the instructions for sending
your comments electronically.
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20:58 Oct 18, 2006
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• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• 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.
To get the service information
identified in this AD, contact Nomad
Operations, Aerospace Support
Division, Boeing Australia, PO Box 767,
Brisbane, QLD 4000 Australia;
telephone 61 7 3306 3366; fax 61 7 3306
3111.
To view the comments to this AD, go
to https://dms.dot.gov. The docket
number is FAA–2006–25928;
Directorate Identifier 2006–CE–53–AD.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Safety Authority
(CASA), which is the airworthiness
authority for Australia, reported several
incidents of ailerons incurring damage
during flight. Extensive tests and
analysis revealed the cause of the
damage to the ailerons resulted from
operation outside approved limits and
undetected pre-existing damage.
The CASA lowered the operational
limits of the affected airplanes in order
to prevent damage from occurring.
Additional reports of aileron flutter
were received even when operating
within these lower approved limits. As
a precautionary measure, the CASA
further restricted flight operations by
issuing Australian AD Number AD/
GAF–N22/69, Amendment 4, dated
February 27, 2003.
This situation prompted us to issue
AD 2003–22–13, Amendment 39–13361
(68 FR 64270, November 13, 2003). AD
2003–22–13 currently requires the
following on all ASTA Models N22B
and N24A airplanes:
—Visually inspecting the ailerons for
damage and replacing if necessary;
—Adjusting the engine power levers
aural warning microswitches;
—Setting flap extension and flap down
operation limitations; and
—Fabricating and installing cockpit flap
extension and flap down operation
restriction placards.
Since we issued AD 2003–22–13, the
CASA issued Australian AD Number
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AD/GAF–N22/69, Amendment 5, issued
September 14, 2006, effective on
October 26, 2006. That AD clarifies that
N22 series and Model N24S airplanes
with float/amphibian configuration are
included in the Applicability section of
their AD.
Upon reviewing Amendment 5 of the
CASA AD to ensure N22 series and
Model N24S airplanes with float/
amphibian configuration were included
in the Applicability section of AD 2003–
22–13, we realized that we
inadvertently omitted Model N22S
airplanes from the Applicability section.
Models N22B and N24A airplanes
with float/amphibian configuration
were affected by AD 2003–22–13
because we included all serial numbers
in the Applicability section.
This condition, if not corrected, could
result in aileron failure. Such failure
could lead to reduced or loss of control
of the airplane.
Relevant Service Information
We reviewed Nomad Alert Service
Bulletin ANMD–57–18, Rev 1, dated
August 14, 2006. The service
information describes procedures for:
—Adjusting the engine power levers
aural warning microswitches;
—Setting flap extension and flap down
operation limitations; and
—Fabricating and installing cockpit flap
extension and flap down operation
restriction placards.
FAA’s Determination and Requirements
of This AD
These ASTA Models N22B, N22S, and
N24A airplanes are manufactured in
Australia and are 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.
Under this bilateral airworthiness
agreement, the CASA has kept us
informed of the situation described
above. We are issuing this AD because
we evaluated all the information and
determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design. This AD supersedes AD
2003–22–13 with a new AD that retains
the actions exactly as required in AD
2003–22–13, adds Model N22S
airplanes to the Applicability section,
and clarifies applicability to airplanes
with float/amphibian configuration.
In preparing this rule, we contacted
type clubs and aircraft operators to get
technical information and information
on operational and economic impacts.
We did not receive any information
through these contacts. If received, we
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Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations
would have included a discussion of
any information that may have
influenced this action in the rulemaking
docket.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, 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 an
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments regarding this
AD. Send your comments to an address
listed under the ADDRESSES section.
Include the docket number ‘‘FAA–
2006–25928; Directorate Identifier
2006–CE–53–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the AD. We will consider all
comments received by the closing date
and may amend the 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 we receive
concerning 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 AD.
61637
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
Regulatory Findings
We have 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 that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that
contains the AD, the regulatory
evaluation, any comments received, and
other information on the Internet at
https://dms.dot.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone (800) 647–
5227) is located at the street address
stated in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2003–22–13, Amendment 39–13361 (68
FR 64270, November 13, 2003) and
adding the following new AD:
I
2006–21–12 AeroSpace Technologies of
Australia Pty Ltd.: Amendment 39–
14797; Docket No. FAA–2006–25928;
Directorate Identifier 2006–CE–53–AD.
Effective Date
(a) This AD becomes effective on
November 8, 2006.
Affected ADs
(b) Supersedes AD 2003–22–13,
Amendment 39–13361.
Applicability
(c) This AD affects Models N22B, N22S,
and N24A airplanes, all serial numbers
including airplanes with float/amphibian
configuration, that are certificated in any
category.
Unsafe Condition
(d) This AD is the result of mandatory
continuing airworthiness information (MCAI)
issued by the airworthiness authority for
Australia. We are issuing this AD to prevent
failure of the aileron due to undetected preexisting aileron damage and airplane
operation outside of the approved limits.
Aileron failure could lead to reduced or loss
of control of the airplane.
Compliance
(e) To address this problem, you must do
the following:
Compliance
Procedures
(1) Visually inspect the left-hand and right-hand
ailerons for damage (i.e., distortion, bending,
impact marks). Repair or replace any damaged aileron found.
PWALKER on PRODPC60 with RULES
Actions
(i) For Models N22B and N24A airplanes (airplanes previously affected by AD 2003–22–
13): Inspect within the next 50 hours timein-service (TIS) after December 23, 2003
(the effective date of AD 2003–22–13), unless already done.
(ii) For Model N22S airplanes (airplanes not
previously affected by AD 2003–22–13): Inspect within the next 10 hours TIS or 30
days, whichever occurs first, after the effective date of this AD, unless already done.
Following the applicable maintenance manual.
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Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations
Actions
Compliance
(2) Adjust the engine power lever actuated
landing gear ‘‘up’’ aural warning microswitches and then perform a ground test. If
deficiencies are detected during the ground
test, make the necessary adjustments.
PWALKER on PRODPC60 with RULES
(3) For Model N22B airplanes:
(i) Fabricate placards that incorporate the
following words (using at least 1⁄8-inch
letters) and install these placards on the
instrument panel within the pilot’s clear
view:
(A) ‘‘RECOMMENDED APPROACH
FLAPS 10 OR 20 DEG AT 90
KIAS’’;
(B) ‘‘USE 10° OR 20° FLAP FOR
TAKE-OFF
AND
LANDING—
WARNING—DO NOT EXCEED 20°
FLAP
EXTENSION
DURING
FLIGHT, LANDING GEAR UP
WARNING WILL INITIATE FOR A
TORQUE PRESSURE OF LESS
THAN 30 PSI’’; and
(ii) Incorporate the following information
into the Limitations section of the Airplane Flight Manual (AFM):
(A) Limit the maximum flap extension
to 20 degrees; and
(B) Limit flaps down operations for
landing to 10° or 20° flap.
(4) For Model N22S airplanes:
(i) Fabricate a placard that incorporates the
following words (using at least 1⁄8-inch
letters) and install this placard on the instrument panel within the pilot’s clear
view: ‘‘USE 10° FLAP FOR TAKE-OFF
AND LANDING—WARNING—DO NOT
EXCEED 10° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP
WARNING WILL INITIATE FOR A
TORQUE PRESSURE OF LESS THAN
30 PSI’’; and
(ii) Incorporate the following information
into the Limitations section of the AFM:
(A) Limit the maximum flap extension
to 10 degrees; and
(B) Limit flaps down operations for
landing to 10° flap.
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Procedures
(iii) For all affected airplanes: Repair or replace before further flight after the inspection.
(i) For Models N22B and N24A airplanes (airplanes previously affected by AD 2003–22–
13): Within the next 50 hours TIS after December 23, 2003 (the effective date of AD
2003–22–13), unless already done following
Nomad Alert Service Bulletin ANMD–57–18,
dated December 19, 2002.
(ii) For Model N22S airplanes (airplanes not
previously affected by AD 2003–22–13):
Within the next 10 hours TIS or 30 days,
whichever occurs first, after the effective
date of this AD, unless already done.
Within the next 50 hours TIS after December
23, 2003 (the effective date of AD 2003–
22–13), unless already done following
Nomad Alert Service Bulletin ANMD–57–18,
dated December 19, 2002.
Within the next 10 hours TIS or 30 days,
whichever occurs first, after the effective
date of this AD, unless already done.
PO 00000
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Following Nomad Alert Service Bulletin
ANMD–57–18, Rev 1, dated August 14,
2006, and the applicable maintenance manual.
Following Nomad Alert Service Bulletin
ANMD–57–18, Rev 1, dated August 14,
2006. To show compliance with paragraphs
(e)(3)(ii)(A) and (e)(3)(ii)(B) of this AD, a
copy of this AD may be inserted into the
Limitations section of the AFM. The owner/
operator holding at least a private pilot certificate as authorized by section 43.7 of the
Federal Aviation Regulations (14 CFR 43.7)
may do the AFM insertion and the placard
requirements of paragraphs (e)(3)(i)(A) and
(e)(3)(i)(B) of this AD. Make an entry into
the aircraft records showing compliance
with these portions of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
Following Nomad Alert Service Bulletin
ANMD–57–18, Rev 1, dated August 14,
2006. To show compliance with paragraphs
(e)(4)(ii)(A) and (e)(4)(ii)(B) of this AD, a
copy of this AD may be inserted into the
Limitations section of the AFM. The owner/
operator holding at least a private pilot certificate as authorized by section 43.7 of the
Federal Aviation Regulations (14 CFR 43.7)
may do the AFM insertion and the placard
requirement of paragraph (e)(4)(i) of this
AD. Make an entry into the aircraft records
showing compliance with these portions of
the AD following section 43.9 of the Federal
Aviation Regulations (14 CFR 43.9).
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Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations
61639
Actions
Compliance
Procedures
(5) For Model N24A airplanes:
(i) Fabricate a placard that incorporates the
following words (using at least 1⁄8-inch
letters) and install this placard on the instrument panel within the pilot’s clear
view: ‘‘USE 10° FLAP FOR TAKE-OFF
AND LANDING—WARNING—DO NOT
EXCEED 10° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP
WARNING WILL INITIATE FOR A
TORQUE PRESSURE OF LESS THAN
30 PSI’’; and
(ii) Incorporate the following information
into the Limitations section of the AFM:
(A) Limit the maximum flap extension
to 10 degrees; and
(B) Limit flaps down operations for
landing to 10° flap.
Within the next 50 hours TIS after December
23, 2003 (the effective date of AD 2003–
22–13), unless already done following
Nomad Alert Service Bulletin ANMD–57–18,
dated December 19, 2002.
Following Nomad Alert Service Bulletin
ANMD–57–18, Rev 1, dated August 14,
2006. To show compliance with paragraphs
(e)(5)(ii)(A) and (e)(5)(ii)(B) of this AD, a
copy of this AD may be inserted into the
Limitations section of the AFM. The owner/
operator holding at least a private pilot certificate as authorized by section 43.7 of the
Federal Aviation Regulations (14 CFR 43.7)
may do the AFM insertion and the placard
requirement of paragraph (e)(5)(i) of this
AD. Make an entry into the aircraft records
showing compliance with these portions of
the AD following section 43.9 of the Federal
Aviation Regulations (14 CFR 43.9).
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Standards Staff, FAA,
ATTN: Doug Rudolph, Aerospace Engineer,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19.
(g) AMOCs approved for AD 2003–22–13
are not approved for this AD.
Related Information
(h) This AD relates to Australian AD/GAF–
N22/69, Amendment 5, dated September 14,
2006, which references Nomad Alert Service
Bulletin ANMD–57–18, Rev 1, dated August
14, 2006.
PWALKER on PRODPC60 with RULES
Material Incorporated by Reference
(i) You must use Nomad Alert Service
Bulletin ANMD–57–18, Rev 1, dated August
14, 2006, 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 Nomad Operations,
Aerospace Support Division, Boeing
Australia, PO Box 767, Brisbane, QLD 4000
Australia; telephone 61 7 3306 3366; fax 61
7 3306 3111.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Kansas City, Missouri
64106; or 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
October 13, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–17425 Filed 10–18–06; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26083; Directorate
Identifier 2006–NM–185–AD; Amendment
39–14793; AD 2006–21–08]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200, A340–200, and A340–300
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200, A340–200,
and A340–300 airplanes. This AD
requires the installation of heatshields
in the belly fairing of the center
fuselage. This AD results from fuel
system reviews conducted by the
manufacturer. We are issuing this AD to
prevent exposing any fuel leaked from
the center fuel tank to the hot
temperature areas of the air
conditioning packs, which could result
in a fire and consequent fuel tank
explosion.
DATES: This AD becomes effective
November 3, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of November 3, 2006.
We must receive comments on this
AD by December 18, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
PO 00000
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Sfmt 4700
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.
• 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.
Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France,
for service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
we issued a regulation titled ‘‘Transport
Airplane Fuel Tank System Design
Review, Flammability Reduction and
Maintenance and Inspection
Requirements’’ (66 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements, this
rule included Special Federal Aviation
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]]>Agencies
[Federal Register Volume 71, Number 202 (Thursday, October 19, 2006)]
[Rules and Regulations]
[Pages 61636-61639]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-17425]
[[Page 61636]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25928; Directorate Identifier 2006-CE-53-AD;
Amendment 39-14797; AD 2006-21-12]
RIN 2120-AA64
Airworthiness Directives; AeroSpace Technologies of Australia Pty
Ltd. Models N22B, N22S, and N24A Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) to
supersede AD 2003-22-13, which applies to all AeroSpace Technologies of
Australia Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 2003-22-13
currently requires you to visually inspect the ailerons for damage and
replace if necessary; adjust the engine power levers aural warning
microswitches; set flap extension and flap down operation limitations;
and fabricate and install cockpit flap extension and flap down
operation restriction placards. This AD results from mandatory
continuing airworthiness information (MCAI) issued by the airworthiness
authority for Australia. The FAA inadvertently omitted Model N22S
airplanes from the applicability of AD 2003-22-13. Therefore, this AD
retains the actions exactly as required in AD 2003-22-13 and adds Model
N22S airplanes to the Applicability section. We are issuing this AD to
prevent failure of the aileron due to undetected pre-existing aileron
damage and airplane operation outside of the approved limits. Aileron
failure could lead to reduced or loss of control of the airplane.
DATES: This AD becomes effective on November 8, 2006.
As of November 8, 2006, the Director of the Federal Register
approved the incorporation by reference of certain publications listed
in the regulation.
We must receive any comments on this AD by November 20, 2006.
ADDRESSES: Use one of the following to comment on this 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 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 20590-0001.
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.
To get the service information identified in this AD, contact Nomad
Operations, Aerospace Support Division, Boeing Australia, PO Box 767,
Brisbane, QLD 4000 Australia; telephone 61 7 3306 3366; fax 61 7 3306
3111.
To view the comments to this AD, go to https://dms.dot.gov. The
docket number is FAA-2006-25928; Directorate Identifier 2006-CE-53-AD.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
The Civil Aviation Safety Authority (CASA), which is the
airworthiness authority for Australia, reported several incidents of
ailerons incurring damage during flight. Extensive tests and analysis
revealed the cause of the damage to the ailerons resulted from
operation outside approved limits and undetected pre-existing damage.
The CASA lowered the operational limits of the affected airplanes
in order to prevent damage from occurring. Additional reports of
aileron flutter were received even when operating within these lower
approved limits. As a precautionary measure, the CASA further
restricted flight operations by issuing Australian AD Number AD/GAF-
N22/69, Amendment 4, dated February 27, 2003.
This situation prompted us to issue AD 2003-22-13, Amendment 39-
13361 (68 FR 64270, November 13, 2003). AD 2003-22-13 currently
requires the following on all ASTA Models N22B and N24A airplanes:
--Visually inspecting the ailerons for damage and replacing if
necessary;
--Adjusting the engine power levers aural warning microswitches;
--Setting flap extension and flap down operation limitations; and
--Fabricating and installing cockpit flap extension and flap down
operation restriction placards.
Since we issued AD 2003-22-13, the CASA issued Australian AD Number
AD/GAF-N22/69, Amendment 5, issued September 14, 2006, effective on
October 26, 2006. That AD clarifies that N22 series and Model N24S
airplanes with float/amphibian configuration are included in the
Applicability section of their AD.
Upon reviewing Amendment 5 of the CASA AD to ensure N22 series and
Model N24S airplanes with float/amphibian configuration were included
in the Applicability section of AD 2003-22-13, we realized that we
inadvertently omitted Model N22S airplanes from the Applicability
section.
Models N22B and N24A airplanes with float/amphibian configuration
were affected by AD 2003-22-13 because we included all serial numbers
in the Applicability section.
This condition, if not corrected, could result in aileron failure.
Such failure could lead to reduced or loss of control of the airplane.
Relevant Service Information
We reviewed Nomad Alert Service Bulletin ANMD-57-18, Rev 1, dated
August 14, 2006. The service information describes procedures for:
--Adjusting the engine power levers aural warning microswitches;
--Setting flap extension and flap down operation limitations; and
--Fabricating and installing cockpit flap extension and flap down
operation restriction placards.
FAA's Determination and Requirements of This AD
These ASTA Models N22B, N22S, and N24A airplanes are manufactured
in Australia and are 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.
Under this bilateral airworthiness agreement, the CASA has kept us
informed of the situation described above. We are issuing this AD
because we evaluated all the information and determined the unsafe
condition described previously is likely to exist or develop on other
products of the same type design. This AD supersedes AD 2003-22-13 with
a new AD that retains the actions exactly as required in AD 2003-22-13,
adds Model N22S airplanes to the Applicability section, and clarifies
applicability to airplanes with float/amphibian configuration.
In preparing this rule, we contacted type clubs and aircraft
operators to get technical information and information on operational
and economic impacts. We did not receive any information through these
contacts. If received, we
[[Page 61637]]
would have included a discussion of any information that may have
influenced this action in the rulemaking docket.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, 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 an opportunity for
public comment. We invite you to send any written relevant data, views,
or arguments regarding this AD. Send your comments to an address listed
under the ADDRESSES section. Include the docket number ``FAA-2006-
25928; Directorate Identifier 2006-CE-53-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the 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 we
receive concerning 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 AD.
Regulatory Findings
We have 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 that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket that contains the AD, the regulatory
evaluation, any comments received, and other information on the
Internet at https://dms.dot.gov; or in person at the Docket Management
Facility between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The Docket Office (telephone (800) 647-5227) is
located at the street address stated in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA proposes to amend 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 removing Airworthiness Directive (AD)
2003-22-13, Amendment 39-13361 (68 FR 64270, November 13, 2003) and
adding the following new AD:
2006-21-12 AeroSpace Technologies of Australia Pty Ltd.: Amendment
39-14797; Docket No. FAA-2006-25928; Directorate Identifier 2006-CE-
53-AD.
Effective Date
(a) This AD becomes effective on November 8, 2006.
Affected ADs
(b) Supersedes AD 2003-22-13, Amendment 39-13361.
Applicability
(c) This AD affects Models N22B, N22S, and N24A airplanes, all
serial numbers including airplanes with float/amphibian
configuration, that are certificated in any category.
Unsafe Condition
(d) This AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Australia. We are issuing this AD to prevent failure of the aileron
due to undetected pre-existing aileron damage and airplane operation
outside of the approved limits. Aileron failure could lead to
reduced or loss of control of the airplane.
Compliance
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Visually inspect the (i) For Models N22B Following the
left-hand and right-hand and N24A airplanes applicable
ailerons for damage (i.e., (airplanes maintenance manual.
distortion, bending, impact previously affected
marks). Repair or replace by AD 2003-22-13):
any damaged aileron found. Inspect within the
next 50 hours time-
in-service (TIS)
after December 23,
2003 (the effective
date of AD 2003-22-
13), unless already
done.
(ii) For Model N22S
airplanes
(airplanes not
previously affected
by AD 2003-22-13):
Inspect within the
next 10 hours TIS
or 30 days,
whichever occurs
first, after the
effective date of
this AD, unless
already done.
[[Page 61638]]
(iii) For all
affected airplanes:
Repair or replace
before further
flight after the
inspection.
(2) Adjust the engine power (i) For Models N22B Following Nomad
lever actuated landing gear and N24A airplanes Alert Service
``up'' aural warning (airplanes Bulletin ANMD-57-
microswitches and then previously affected 18, Rev 1, dated
perform a ground test. If by AD 2003-22-13): August 14, 2006,
deficiencies are detected Within the next 50 and the applicable
during the ground test, hours TIS after maintenance manual.
make the necessary December 23, 2003
adjustments. (the effective date
of AD 2003-22-13),
unless already done
following Nomad
Alert Service
Bulletin ANMD-57-
18, dated December
19, 2002.
(ii) For Model N22S
airplanes
(airplanes not
previously affected
by AD 2003-22-13):
Within the next 10
hours TIS or 30
days, whichever
occurs first, after
the effective date
of this AD, unless
already done.
(3) For Model N22B Within the next 50 Following Nomad
airplanes: hours TIS after Alert Service
(i) Fabricate placards that December 23, 2003 Bulletin ANMD-57-
incorporate the following (the effective date 18, Rev 1, dated
words (using at least \1/8\- of AD 2003-22-13), August 14, 2006. To
inch letters) and install unless already done show compliance
these placards on the following Nomad with paragraphs
instrument panel within the Alert Service (e)(3)(ii)(A) and
pilot's clear view: Bulletin ANMD-57- (e)(3)(ii)(B) of
(A) ``RECOMMENDED APPROACH 18, dated December this AD, a copy of
FLAPS 10 OR 20 DEG AT 90 19, 2002. this AD may be
KIAS''; inserted into the
(B) ``USE 10[deg] OR 20[deg] Limitations section
FLAP FOR TAKE-OFF AND of the AFM. The
LANDING--WARNING--DO NOT owner/operator
EXCEED 20[deg] FLAP holding at least a
EXTENSION DURING FLIGHT, private pilot
LANDING GEAR UP WARNING certificate as
WILL INITIATE FOR A TORQUE authorized by
PRESSURE OF LESS THAN 30 section 43.7 of the
PSI''; and Federal Aviation
(ii) Incorporate the Regulations (14 CFR
following information into 43.7) may do the
the Limitations section of AFM insertion and
the Airplane Flight Manual the placard
(AFM): requirements of
(A) Limit the maximum flap paragraphs
extension to 20 degrees; (e)(3)(i)(A) and
and (e)(3)(i)(B) of
(B) Limit flaps down this AD. Make an
operations for landing to entry into the
10[deg] or 20[deg] flap. aircraft records
showing compliance
with these portions
of the AD following
section 43.9 of the
Federal Aviation
Regulations (14 CFR
43.9).
(4) For Model N22S Within the next 10 Following Nomad
airplanes: hours TIS or 30 Alert Service
(i) Fabricate a placard that days, whichever Bulletin ANMD-57-
incorporates the following occurs first, after 18, Rev 1, dated
words (using at least \1/8\- the effective date August 14, 2006. To
inch letters) and install of this AD, unless show compliance
this placard on the already done. with paragraphs
instrument panel within the (e)(4)(ii)(A) and
pilot's clear view: ``USE (e)(4)(ii)(B) of
10[deg] FLAP FOR TAKE-OFF this AD, a copy of
AND LANDING--WARNING--DO this AD may be
NOT EXCEED 10[deg] FLAP inserted into the
EXTENSION DURING FLIGHT, Limitations section
LANDING GEAR UP WARNING of the AFM. The
WILL INITIATE FOR A TORQUE owner/operator
PRESSURE OF LESS THAN 30 holding at least a
PSI''; and private pilot
(ii) Incorporate the certificate as
following information into authorized by
the Limitations section of section 43.7 of the
the AFM: Federal Aviation
(A) Limit the maximum flap Regulations (14 CFR
extension to 10 degrees; 43.7) may do the
and AFM insertion and
(B) Limit flaps down the placard
operations for landing to requirement of
10[deg] flap. paragraph (e)(4)(i)
of this AD. Make an
entry into the
aircraft records
showing compliance
with these portions
of the AD following
section 43.9 of the
Federal Aviation
Regulations (14 CFR
43.9).
[[Page 61639]]
(5) For Model N24A Within the next 50 Following Nomad
airplanes: hours TIS after Alert Service
(i) Fabricate a placard that December 23, 2003 Bulletin ANMD-57-
incorporates the following (the effective date 18, Rev 1, dated
words (using at least \1/8\- of AD 2003-22-13), August 14, 2006. To
inch letters) and install unless already done show compliance
this placard on the following Nomad with paragraphs
instrument panel within the Alert Service (e)(5)(ii)(A) and
pilot's clear view: ``USE Bulletin ANMD-57- (e)(5)(ii)(B) of
10[deg] FLAP FOR TAKE-OFF 18, dated December this AD, a copy of
AND LANDING--WARNING--DO 19, 2002. this AD may be
NOT EXCEED 10[deg] FLAP inserted into the
EXTENSION DURING FLIGHT, Limitations section
LANDING GEAR UP WARNING of the AFM. The
WILL INITIATE FOR A TORQUE owner/operator
PRESSURE OF LESS THAN 30 holding at least a
PSI''; and private pilot
(ii) Incorporate the certificate as
following information into authorized by
the Limitations section of section 43.7 of the
the AFM: Federal Aviation
(A) Limit the maximum flap Regulations (14 CFR
extension to 10 degrees; 43.7) may do the
and AFM insertion and
(B) Limit flaps down the placard
operations for landing to requirement of
10[deg] flap. paragraph (e)(5)(i)
of this AD. Make an
entry into the
aircraft records
showing compliance
with these portions
of the AD following
section 43.9 of the
Federal Aviation
Regulations (14 CFR
43.9).
------------------------------------------------------------------------
Alternative Methods of Compliance (AMOCs)
(f) The Manager, Standards Staff, FAA, ATTN: Doug Rudolph,
Aerospace Engineer, Small Airplane Directorate, 901 Locust, Room
301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax:
(816) 329-4090, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
(g) AMOCs approved for AD 2003-22-13 are not approved for this
AD.
Related Information
(h) This AD relates to Australian AD/GAF-N22/69, Amendment 5,
dated September 14, 2006, which references Nomad Alert Service
Bulletin ANMD-57-18, Rev 1, dated August 14, 2006.
Material Incorporated by Reference
(i) You must use Nomad Alert Service Bulletin ANMD-57-18, Rev 1,
dated August 14, 2006, 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 Nomad
Operations, Aerospace Support Division, Boeing Australia, PO Box
767, Brisbane, QLD 4000 Australia; telephone 61 7 3306 3366; fax 61
7 3306 3111.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or 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 October 13, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-17425 Filed 10-18-06; 8:45 am]
BILLING CODE 4910-13-P
