Airworthiness Directives; AeroSpace Technologies of Australia Pty Ltd. Models N22B, N22S, and N24A Airplanes, 29437-29440 [05-9976]
Download as PDF
<![CDATA[
29437
Rules and Regulations
Federal Register
Vol. 70, No. 98
Monday, May 23, 2005
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20439; Directorate
Identifier 2005–CE–04–AD; Amendment 39–
14102; AD 2005–10–24]
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.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) to
supersede AD 2003–14–20, which
applies to all AeroSpace Technologies
of Australia Pty Ltd. (ASTA) Models
N22B and N24A airplanes. AD 2003–
14–20 requires you to repetitively
inspect, using either dye penetrant or
magnetic particle methods, the rudder
control lever shafts for cracks; inspect
(one-time) all lever shaft side plates by
measuring the thickness; and if cracks
or discrepancies in thickness are found,
replace unserviceable parts with new or
serviceable parts. Since AD 2003–14–20
was issued, we determined that the AD
should also affect Model N22S
airplanes. The manufacturer has also
revised the service information to
include a rudder control lever shaft part
number (P/N) that was not part of AD
2003–14–20. Consequently, this AD
retains the actions of AD 2003–14–20,
adds Model N22S airplanes to the
applicability, and adds rudder control
lever shaft P/N 1/N–45–1102 to the
inspection requirements. We are issuing
this AD to detect and correct cracks in
the rudder control lever torque shafts
and discrepancies in the thickness of
the lever shaft side plates, which could
result in failure of the rudder control
VerDate jul<14>2003
14:30 May 20, 2005
Jkt 205001
lever torque shaft. Such failure could
lead to reduced controllability of the
airplane.
This AD becomes effective on
June 30, 2005.
As of June 30, 2005, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
ADDRESSES: To get the service
information identified in this AD,
contact Nomad Operations, Aerospace
Support Division, Boeing Australia, PO
Box 767, Brisbane, QLD 4001 Australia;
telephone 61 7 3306 3366; facsimile 61
7 3306 3111.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2005–20439; Directorate Identifier
2005–CE–04–AD.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
Small Airplane Directorate, ACE–112,
901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; facsimile: (816) 329–4090.
SUPPLEMENTARY INFORMATION:
DATES:
Discussion
What events have caused this AD?
Reports of cracking and other
discrepancies on rudder control lever
shaft assemblies on certain ASTA
Models N22B and N24A airplanes
caused us to issue AD 82–12–06,
Amendment 39–4399. AD 82–12–06
required the following:
—Repetitively inspecting visually all
rudder control lever shafts for
cracking;
—If cracks are found, replacing with
new or serviceable rudder control
shafts;
—Checking for clearance of the fit of all
rod end bearings in lever shafts; and
—Discontinuing the repetitive visual
inspections when lever shafts are
inspected either by magnetic particle
inspection or dye penetrant methods
The Civil Aviation Safety Authority
(CASA), which is the airworthiness
authority for Australia notified FAA of
the need to change AD 82–12–06. The
CASA reported failures of the rudder
control lever shaft. All the failures
occurred during ground operations.
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
Nosewheel steering/rudder loads are
considered the primary cause of the
failures.
Some of the failures occurred on
airplanes where the terminating action
of AD 82–12–06 had been incorporated.
This caused us to issue AD 2003–14–20,
Amendment 39–13239 (68 FR 42954,
July 21, 2003).
AD 2003–14–20 currently requires the
following on all ASTA Model N22B and
N24A airplanes:
—Repetitively inspecting, using either
dye penetrant or magnetic particle
methods and measurements, certain
rudder control lever shafts, part
numbers (P/N) 2/N–45–1102, 1/N–45–
1103, and 1/N–45–1104 (or FAAapproved equivalent part numbers),
for cracks;
—Inspecting (one-time) all lever shaft
side plates by measuring the
thickness; and
—If cracks or discrepancies in thickness
are found, replacing unserviceable
parts with new or serviceable parts.
What has happened since AD 2003–
14–20 to initiate this action? Since AD
2003–14–20 was issued, we determined
that Model N22S airplanes should be
included in the applicability.
The manufacturer has also revised the
service information to include a rudder
control lever shaft P/N that was not part
of AD 2003–14–20.
What is the potential impact if FAA
took no action? This condition, if not
detected and corrected, could result in
failure of the rudder control lever torque
shaft. Such failure could lead to reduced
controllability of the airplane.
Has FAA taken any action to this
point? We issued a proposal to amend
part 39 of the Federal Aviation
Regulations (14 CFR part 39) to include
an AD that would apply to all ASTA
Model N22B, N22S, and N24A
airplanes. This proposal was published
in the Federal Register as a notice of
proposed rulemaking (NPRM) on March
16, 2005 (70 FR 12819). The NPRM
proposed to supersede AD 2003–14–20
with a new AD that would retain the
actions of AD 2003–14–20, add Model
N22S airplanes to the applicability, and
add rudder control lever shaft P/N 1/N–
45–1102 to the inspection requirements.
Comments
Was the public invited to comment?
We provided the public the opportunity
to participate in developing this AD. We
E:\FR\FM\23MYR1.SGM
23MYR1
29438
Federal Register / Vol. 70, No. 98 / Monday, May 23, 2005 / Rules and Regulations
received no comments on the proposal
or on the determination of the cost to
the public.
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Conclusion
What is FAA’s final determination on
this issue? We have carefully reviewed
the available data and determined that
air safety and the public interest require
adopting the AD as proposed except for
minor editorial corrections. We have
determined that these minor
corrections:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
Changes to 14 CFR Part 39—Effect on
the AD
How does the revision to 14 CFR part
39 affect this AD? On July 10, 2002, the
FAA published a new version of 14 CFR
part 39 (67 FR 47997, July 22, 2002),
which governs the FAA’s AD system.
This regulation now includes material
that relates to altered products, special
flight permits, and alternative methods
of compliance. This material previously
was included in each individual AD.
Since this material is included in 14
CFR part 39, we will not include it in
future AD actions.
Costs of Compliance
How many airplanes does this AD
impact? We estimate that this AD affects
15 airplanes in the U.S. registry.
What is the cost impact of this AD on
owners/operators of the affected
airplanes? We estimate the following
costs to do the initial inspection:
Labor cost
Parts cost
Total cost
per airplane
12 workhours × $65 per hour = $780 ...................................................................
Not Applicable ...........
Total cost on U.S.
operators
$780
15 × $780 = $11,700.
We estimate the following costs to do
the necessary repetitive inspections:
Labor cost
Parts cost
Total cost per
airplane
2 workhours × $65 per hour = $130 ..................................................................................................
Not Applicable .........
$130.
We estimate the following costs to do
any rudder control lever shaft
replacement that will be required based
on the results of the inspections. We
have no way of determining the number
of airplanes that may need such
replacement:
Labor cost
Parts cost
12 workhours × $65 per hour = $780 ...............................................................................................
$930
We estimate the following costs to do
any lever shaft side plate replacements
that will be required based on the
results of the inspection. We have no
way of determining the number of
Parts cost
12 workhours × $65 per hour = $780 ...............................................................................................
$930
Authority for This Rulemaking
What authority does FAA have for
issuing this rulemaking action? 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.
VerDate jul<14>2003
14:30 May 20, 2005
Jkt 205001
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
Will this AD impact various entities?
We have determined that this AD will
not have federalism implications under
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
$780 + $930 = $1710.
airplanes that may need such
replacement:
Labor cost
What is the difference between the
cost impact of this AD and the cost
impact of AD 2003–14–20? The only
difference between AD 2003–14–20 and
this AD is the addition of Model N22S
airplanes to the applicability section.
There are no additional actions required
in this AD.
Total cost per airplane
Total cost per airplane
$780 + $930 = $1710.
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.
Will this AD involve a significant rule
or regulatory action? 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
E:\FR\FM\23MYR1.SGM
23MYR1
Federal Register / Vol. 70, No. 98 / Monday, May 23, 2005 / Rules and Regulations
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD (and other
information as included in the
Regulatory Evaluation) and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2005–20439;
Directorate Identifier 2005–CE–04–AD’’
in your request.
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 Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
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]
29439
What Other ADs Are Affected By This
Action?
(b) This AD supersedes AD 2003–14–20,
Amendment 39–13239.
What Airplanes Are Affected By This AD?
(c) This AD affects Models N22B, N22S,
and N24A airplanes, all serial numbers, that
are certificated in any category.
2005–10–24 Aerospace Technologies of
Australia Pty Ltd.: Amendment 39–
14102; Docket No. FAA–2005–20439;
Directorate Identifier 2005–CE–04–AD;
Supersedes AD 2003–14–20,
Amendment 39–13239.
What Is The Unsafe Condition Presented in
This AD?
(d) This AD is the result of continuing
airworthiness information (MCAI) issued by
the airworthiness authority for Australia. The
actions specified in this AD are intended to
detect and correct cracks in the rudder
control lever torque shafts and discrepancies
in the thickness of the lever shaft side plates,
which could result in failure of the rudder
control lever torque shaft. Such failure could
lead to reduced controllability of the
airplane.
When Does This AD Become Effective?
What Must I Do To Address This Problem?
(a) This AD becomes effective on June 30,
2005.
(e) To address this problem, you must do
the following:
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2003–14–20, Amendment 39–13239 (68
FR 42954, July 21, 2003), and by adding
a new AD to read as follows:
I
Actions
Compliance
Procedures
(1) Inspect the following:
(i) The rudder control level shafts, part numbers
(P/N) 1/N–45–1102, 2/N–45–1102, 1/N–45–
1103, and 1/N–45–1104 (or FAA-approved
equivalent part numbers) for cracks. Use dye
penetrant inspection while the shaft is installed. Use either dye penetrant or magnetic
particle inspection if the shaft is removed;
and
(ii) All lever shaft side plates on P/Ns 1/N–45–
1102, 2/N–45–1102, 1/N–45–1103, and 1/N–
45–1104 (or FAA-approved equivalent part
numbers) by measuring the thickness for discrepancies.
(2) If no cracks are found in the rudder control
lever shafts during the inspection required in
paragraph (e)(1)(i) of this AD, repetitively inspect rudder control lever shafts P/Ns 1/N–
45–1102, 2/N–45–1102, 1/N–45–1103, ands
1/N–45–1104 (or FAA-approved equivalent
part numbers) for cracks.
(3) If cracks or discrepancies are found during
any inspection required by this AD, do the
following:
(i) For rudder control lever shafts found with
crack damage, replace with new or serviceable parts. After replacement, continue with
the repetitive inspections required in paragraph (e)(2) of this AD.
(ii) If the thickness of the lever shaft side plates
is less than 0.050 inches, replace the lever
shaft side plate with a new plate that measures at least 0.050 inches in thickness.
(4) If at any time certain operating conditions
occur that caused abnormal rudder pedal
loads, inspect the rudder control lever shafts
as specified in paragraph (e)(2) of this AD.
Examples of such conditions are: heavy use
of nosewheel steering over rough ground; excessive steering angle under towl; towing
with rudder gust lock fitted; engine failure on
takeoff; and aircraft left parked outside with
rudder gust lock not fitted.
Initially inspect within the next 50 hours timein-service (TIS) or 30 days after June 30,
2005 (the effective date of this AD), whichever occurs first, unless already done.
Following Nomad Alert Service Bulletin
ANMD–27–51, Rev. 2, dated April 29,
2004, and the applicable maintenance manual.
Repetitively inspect thereafter at intervals not
to exceed 300 hours TIS after the initial inspection required in paragraph (e)(1) of this
AD.
Following Nomad—Series N22 & N24 Inspection Requirements Manual, Temporary Revision 26, Fatigue Critical Areas, dated May
27, 2004.
Before further flight after any inspection required by this AD in which cracks or discrepancies are found..
Following Nomad Alert Service Bulletin
ANMD–27–51, Rev. 2, dated April 29,
2004, and the applicable maintenance manual.
Before further flight ..........................................
Following Nomad—Series N22 & N24 Inspection Requirements Manual, Temporary Revision 26, Fatigue Critical Areas, dated May
27, 2004.
VerDate jul<14>2003
14:30 May 20, 2005
Jkt 205001
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
E:\FR\FM\23MYR1.SGM
23MYR1
29440
Federal Register / Vol. 70, No. 98 / Monday, May 23, 2005 / Rules and Regulations
Actions
Compliance
Procedures
(5) Do not install a new lever shaft side plate
that is less than 0.050 inches in thickness.
As of June 30, 2005 (the effective date of this
AD).
As specified in Nomad Alert Service Bulletin
ANMD–27–51, Rev. 2, dated April 29,
2004; and Nomad—Series N22 & N24 Inspection Requirements Manual, Temporary
Revision 26, Fatigue Critical Areas, dated
May 27, 2004.
May I Request an Alternative Method of
Compliance?
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19.
(1) Unless FAA authorizes otherwise, send
your request to your principal inspector. The
principal inspector may add comments and
will send your request to the Manager,
Standards Office, Small Airplane Directorate,
FAA. For information on any already
approved alternative methods of compliance,
contact Doug Rudolph, Aerospace Engineer,
Small Airplane Directorate, ACE–112, 901
Locust, Rm 301, Kansas City, Missouri,
64106; telephone: (816) 329–4059; facsimile:
(816) 329–4090.
(2) Alternative methods of compliance
approved for AD 2003–14–20 are not
considered approved as alternative methods
of compliance for this AD.
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2005–20439; Directorate Identifier 2005–CE–
04–AD.
Issued in Kansas City, Missouri, on May
13, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–9976 Filed 5–20–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
As of June 30, 2005, the Director of
the Federal Register approved the
incorporation by reference of certain
publications listed in the regulation.
ADDRESSES: To get the service
information identified in this AD,
contact DG Flugzeugbau, Postbox 41 20,
76625 Bruchsal, Germany; telephone, 49
7257 890; fax, 49 7257 8922.
To view the AD docket, go to the
Docket Management Facility; U.S.
Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001 or on the Internet at https://
dms.dot.gov. The docket number is
FAA–2004–19959; Directorate Identifier
2004–CE–46–AD.
FOR FURTHER INFORMATION CONTACT:
Gregory Davison, Aerospace Engineer,
FAA, Small Airplane Directorate, ACE–
112, Room 301, 901 Locust, Kansas City,
Missouri 64106; telephone: 816–329–
4130; facsimile: 816–329–4090.
SUPPLEMENTARY INFORMATION:
Is There Other Information That Relates to
This Subject?
(g) Australian AD GAF–N22/44,
Amendment 2, dated November 2004, also
addresses the subject of this AD.
14 CFR Part 39
Does This AD Incorporate Any Material By
Reference?
(h) You must do the actions required by
this AD following the instructions in
Nomad—Series N22 & N24 Inspection
Requirements Manual, Temporary Revision
26, Fatigue Critical Areas, dated May 27,
2004, and Nomad Alert Service Bulletin
ANMD–27–51, Rev. 2, dated April 29, 2004,
which incorporates the following pages:
RIN 2120–AA64
Discussion
Airworthiness Directives; DG
Flugzeugbau GmbH Model DG–500MB
Sailplanes and Glaser-Dirks
Flugzeugbau GmbH Model DG–800B
Sailplanes
What events have caused this AD?
The Luftfahrt-Bundesamt (LBA), which
is the airworthiness authority for
Germany, recently notified FAA that an
unsafe condition may exist on all DG
Flugzeugbau GmbH Model DG–500MB
sailplanes equipped with a Solo engine
and all Glaser-Dirks Flugzeugbau GmbH
Model DG–800B sailplanes equipped
with a Solo engine. The LBA reports
that a damaged propeller was found on
a Model DG–800B sailplane.
The foam core inside the propeller
separated and caused one blade to be
thicker than the other. The propeller
became overheated after the engine was
retracted. This was possibly due to
limited ventilation. The LBA reports
three occurrences of this condition.
The propeller on Model DG–500MB
sailplanes equipped with a Solo engine
is of a similar design to Model DG–800B
sailplanes equipped with a Solo engine.
What is the potential impact if FAA
took no action? If not detected and
corrected, damage to the propeller,
specifically foam core separation, could
cause the propeller to fail to perform
properly. This failure could lead to
reduced or loss of control of the
sailplane.
Revision
level
Pages
1 and 3 ..........
2 .....................
4 .....................
1 Original
2
2
1
Date
April 29, 2004.
Jan. 29, 2004.
Sept. 13, 2002.
issue.
(1) The Director of the Federal Register
approved the incorporation by reference of
these documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51.
(2) To get a copy of this service
information, contact Nomad Operations,
Aerospace Support Division, Boeing
Australia, PO Box 767, Brisbane, QLD 4001
Australia; telephone 61 7 3306 3366;
facsimile 61 7 3306 3111. To review copies
of this service information, go to the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html or call (202) 741–6030. To
VerDate jul<14>2003
14:30 May 20, 2005
Jkt 205001
[Docket No. FAA–2004–19959; Directorate
Identifier 2004–CE–46–AD; Amendment 39–
14101; AD 2005–10–23]
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA adopts a new
airworthiness directive (AD) for all DG
Flugzeugbau GmbH Model DG–500MB
sailplanes equipped with a Solo engine
and Glaser-Dirks Flugzeugbau GmbH
Model DG–800B sailplanes equipped
with a Solo engine. This AD requires
you to inspect the propeller for damage,
specifically foam core separation, and
replace any damaged propeller. This AD
results from mandatory continuing
airworthiness information (MCAI)
issued by the airworthiness authority for
Germany. We are issuing this AD to
detect and correct damage to the
propeller, which could result in failure
of the propeller to perform properly.
This failure could lead to reduced or
loss of control of the sailplane.
DATES: This AD becomes effective on
June 30, 2005.
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
E:\FR\FM\23MYR1.SGM
23MYR1
]]>Agencies
[Federal Register Volume 70, Number 98 (Monday, May 23, 2005)]
[Rules and Regulations]
[Pages 29437-29440]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-9976]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 70, No. 98 / Monday, May 23, 2005 / Rules and
Regulations
[[Page 29437]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20439; Directorate Identifier 2005-CE-04-AD;
Amendment 39-14102; AD 2005-10-24]
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.
-----------------------------------------------------------------------
SUMMARY: The FAA adopts a new airworthiness directive (AD) to supersede
AD 2003-14-20, which applies to all AeroSpace Technologies of Australia
Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 2003-14-20 requires
you to repetitively inspect, using either dye penetrant or magnetic
particle methods, the rudder control lever shafts for cracks; inspect
(one-time) all lever shaft side plates by measuring the thickness; and
if cracks or discrepancies in thickness are found, replace
unserviceable parts with new or serviceable parts. Since AD 2003-14-20
was issued, we determined that the AD should also affect Model N22S
airplanes. The manufacturer has also revised the service information to
include a rudder control lever shaft part number (P/N) that was not
part of AD 2003-14-20. Consequently, this AD retains the actions of AD
2003-14-20, adds Model N22S airplanes to the applicability, and adds
rudder control lever shaft P/N 1/N-45-1102 to the inspection
requirements. We are issuing this AD to detect and correct cracks in
the rudder control lever torque shafts and discrepancies in the
thickness of the lever shaft side plates, which could result in failure
of the rudder control lever torque shaft. Such failure could lead to
reduced controllability of the airplane.
DATES: This AD becomes effective on June 30, 2005.
As of June 30, 2005, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in the
regulation.
ADDRESSES: To get the service information identified in this AD,
contact Nomad Operations, Aerospace Support Division, Boeing Australia,
PO Box 767, Brisbane, QLD 4001 Australia; telephone 61 7 3306 3366;
facsimile 61 7 3306 3111.
To view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC 20590-001 or on the Internet at https://
dms.dot.gov. The docket number is FAA-2005-20439; Directorate
Identifier 2005-CE-04-AD.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer,
Small Airplane Directorate, ACE-112, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? Reports of cracking and other
discrepancies on rudder control lever shaft assemblies on certain ASTA
Models N22B and N24A airplanes caused us to issue AD 82-12-06,
Amendment 39-4399. AD 82-12-06 required the following:
--Repetitively inspecting visually all rudder control lever shafts for
cracking;
--If cracks are found, replacing with new or serviceable rudder control
shafts;
--Checking for clearance of the fit of all rod end bearings in lever
shafts; and
--Discontinuing the repetitive visual inspections when lever shafts are
inspected either by magnetic particle inspection or dye penetrant
methods
The Civil Aviation Safety Authority (CASA), which is the
airworthiness authority for Australia notified FAA of the need to
change AD 82-12-06. The CASA reported failures of the rudder control
lever shaft. All the failures occurred during ground operations.
Nosewheel steering/rudder loads are considered the primary cause of the
failures.
Some of the failures occurred on airplanes where the terminating
action of AD 82-12-06 had been incorporated. This caused us to issue AD
2003-14-20, Amendment 39-13239 (68 FR 42954, July 21, 2003).
AD 2003-14-20 currently requires the following on all ASTA Model
N22B and N24A airplanes:
--Repetitively inspecting, using either dye penetrant or magnetic
particle methods and measurements, certain rudder control lever shafts,
part numbers (P/N) 2/N-45-1102, 1/N-45-1103, and 1/N-45-1104 (or FAA-
approved equivalent part numbers), for cracks;
--Inspecting (one-time) all lever shaft side plates by measuring the
thickness; and
--If cracks or discrepancies in thickness are found, replacing
unserviceable parts with new or serviceable parts.
What has happened since AD 2003-14-20 to initiate this action?
Since AD 2003-14-20 was issued, we determined that Model N22S airplanes
should be included in the applicability.
The manufacturer has also revised the service information to
include a rudder control lever shaft P/N that was not part of AD 2003-
14-20.
What is the potential impact if FAA took no action? This condition,
if not detected and corrected, could result in failure of the rudder
control lever torque shaft. Such failure could lead to reduced
controllability of the airplane.
Has FAA taken any action to this point? We issued a proposal to
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to
include an AD that would apply to all ASTA Model N22B, N22S, and N24A
airplanes. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on March 16, 2005 (70 FR 12819).
The NPRM proposed to supersede AD 2003-14-20 with a new AD that would
retain the actions of AD 2003-14-20, add Model N22S airplanes to the
applicability, and add rudder control lever shaft P/N 1/N-45-1102 to
the inspection requirements.
Comments
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. We
[[Page 29438]]
received no comments on the proposal or on the determination of the
cost to the public.
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for minor
editorial corrections. We have determined that these minor corrections:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 15 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to do the initial
inspection:
----------------------------------------------------------------------------------------------------------------
Total cost
Labor cost Parts cost per airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
12 workhours x $65 per hour = Not Applicable................ $780 15 x $780 = $11,700.
$780.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do the necessary repetitive
inspections:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
----------------------------------------------------------------------------------------------------------------
2 workhours x $65 per hour = $130............. Not Applicable........................... $130.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any rudder control lever
shaft replacement that will be required based on the results of the
inspections. We have no way of determining the number of airplanes that
may need such replacement:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
----------------------------------------------------------------------------------------------------------------
12 workhours x $65 per hour = $780........... $930 $780 + $930 = $1710.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any lever shaft side plate
replacements that will be required based on the results of the
inspection. We have no way of determining the number of airplanes that
may need such replacement:
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Total cost per airplane
----------------------------------------------------------------------------------------------------------------
12 workhours x $65 per hour = $780........... $930 $780 + $930 = $1710.
----------------------------------------------------------------------------------------------------------------
What is the difference between the cost impact of this AD and the
cost impact of AD 2003-14-20? The only difference between AD 2003-14-20
and this AD is the addition of Model N22S airplanes to the
applicability section. There are no additional actions required in this
AD.
Authority for This Rulemaking
What authority does FAA have for issuing this rulemaking action?
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
Will this AD impact various entities? 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.
Will this AD involve a significant rule or regulatory action? 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
[[Page 29439]]
under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD (and
other information as included in the Regulatory Evaluation) and placed
it in the AD Docket. You may get a copy of this summary by sending a
request to us at the address listed under ADDRESSES. Include ``Docket
No. FAA-2005-20439; Directorate Identifier 2005-CE-04-AD'' in your
request.
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 Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (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)
2003-14-20, Amendment 39-13239 (68 FR 42954, July 21, 2003), and by
adding a new AD to read as follows:
2005-10-24 Aerospace Technologies of Australia Pty Ltd.: Amendment
39-14102; Docket No. FAA-2005-20439; Directorate Identifier 2005-CE-
04-AD; Supersedes AD 2003-14-20, Amendment 39-13239.
When Does This AD Become Effective?
(a) This AD becomes effective on June 30, 2005.
What Other ADs Are Affected By This Action?
(b) This AD supersedes AD 2003-14-20, Amendment 39-13239.
What Airplanes Are Affected By This AD?
(c) This AD affects Models N22B, N22S, and N24A airplanes, all
serial numbers, that are certificated in any category.
What Is The Unsafe Condition Presented in This AD?
(d) This AD is the result of continuing airworthiness
information (MCAI) issued by the airworthiness authority for
Australia. The actions specified in this AD are intended to detect
and correct cracks in the rudder control lever torque shafts and
discrepancies in the thickness of the lever shaft side plates, which
could result in failure of the rudder control lever torque shaft.
Such failure could lead to reduced controllability of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect the following: Initially inspect Following Nomad
(i) The rudder control level within the next 50 Alert Service
shafts, part numbers (P/N) hours time-in- Bulletin ANMD-27-
1/N-45-1102, 2/N-45-1102, 1/ service (TIS) or 30 51, Rev. 2, dated
N-45-1103, and 1/N-45-1104 days after June 30, April 29, 2004, and
(or FAA-approved equivalent 2005 (the effective the applicable
part numbers) for cracks. date of this AD), maintenance manual.
Use dye penetrant whichever occurs
inspection while the shaft first, unless
is installed. Use either already done.
dye penetrant or magnetic
particle inspection if the
shaft is removed; and
(ii) All lever shaft side
plates on P/Ns 1/N-45-1102,
2/N-45-1102, 1/N-45-1103,
and 1/N-45-1104 (or FAA-
approved equivalent part
numbers) by measuring the
thickness for
discrepancies.
(2) If no cracks are found Repetitively inspect Following Nomad--
in the rudder control lever thereafter at Series N22 & N24
shafts during the intervals not to Inspection
inspection required in exceed 300 hours Requirements
paragraph (e)(1)(i) of this TIS after the Manual, Temporary
AD, repetitively inspect initial inspection Revision 26,
rudder control lever shafts required in Fatigue Critical
P/Ns 1/N-45-1102, 2/N-45- paragraph (e)(1) of Areas, dated May
1102, 1/N-45-1103, ands 1/N- this AD. 27, 2004.
45-1104 (or FAA-approved
equivalent part numbers)
for cracks.
(3) If cracks or Before further Following Nomad
discrepancies are found flight after any Alert Service
during any inspection inspection required Bulletin ANMD-27-
required by this AD, do the by this AD in which 51, Rev. 2, dated
following: cracks or April 29, 2004, and
(i) For rudder control lever discrepancies are the applicable
shafts found with crack found.. maintenance manual.
damage, replace with new or
serviceable parts. After
replacement, continue with
the repetitive inspections
required in paragraph
(e)(2) of this AD..
(ii) If the thickness of the
lever shaft side plates is
less than 0.050 inches,
replace the lever shaft
side plate with a new plate
that measures at least
0.050 inches in thickness..
(4) If at any time certain Before further Following Nomad--
operating conditions occur flight. Series N22 & N24
that caused abnormal rudder Inspection
pedal loads, inspect the Requirements
rudder control lever shafts Manual, Temporary
as specified in paragraph Revision 26,
(e)(2) of this AD. Examples Fatigue Critical
of such conditions are: Areas, dated May
heavy use of nosewheel 27, 2004.
steering over rough ground;
excessive steering angle
under towl; towing with
rudder gust lock fitted;
engine failure on takeoff;
and aircraft left parked
outside with rudder gust
lock not fitted.
[[Page 29440]]
(5) Do not install a new As of June 30, 2005 As specified in
lever shaft side plate that (the effective date Nomad Alert Service
is less than 0.050 inches of this AD). Bulletin ANMD-27-
in thickness. 51, Rev. 2, dated
April 29, 2004; and
Nomad--Series N22 &
N24 Inspection
Requirements
Manual, Temporary
Revision 26,
Fatigue Critical
Areas, dated May
27, 2004.
------------------------------------------------------------------------
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19.
(1) Unless FAA authorizes otherwise, send your request to your
principal inspector. The principal inspector may add comments and
will send your request to the Manager, Standards Office, Small
Airplane Directorate, FAA. For information on any already approved
alternative methods of compliance, contact Doug Rudolph, Aerospace
Engineer, Small Airplane Directorate, ACE-112, 901 Locust, Rm 301,
Kansas City, Missouri, 64106; telephone: (816) 329-4059; facsimile:
(816) 329-4090.
(2) Alternative methods of compliance approved for AD 2003-14-20
are not considered approved as alternative methods of compliance for
this AD.
Is There Other Information That Relates to This Subject?
(g) Australian AD GAF-N22/44, Amendment 2, dated November 2004,
also addresses the subject of this AD.
Does This AD Incorporate Any Material By Reference?
(h) You must do the actions required by this AD following the
instructions in Nomad--Series N22 & N24 Inspection Requirements
Manual, Temporary Revision 26, Fatigue Critical Areas, dated May 27,
2004, and Nomad Alert Service Bulletin ANMD-27-51, Rev. 2, dated
April 29, 2004, which incorporates the following pages:
------------------------------------------------------------------------
Revision
Pages level Date
------------------------------------------------------------------------
1 and 3........................... 2 April 29, 2004.
2................................. 2 Jan. 29, 2004.
4................................. \1\ Sept. 13, 2002.
------------------------------------------------------------------------
\1\ Original issue.
(1) The Director of the Federal Register approved the
incorporation by reference of these documents in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) To get a copy of this service information, contact Nomad
Operations, Aerospace Support Division, Boeing Australia, PO Box
767, Brisbane, QLD 4001 Australia; telephone 61 7 3306 3366;
facsimile 61 7 3306 3111. To review copies of this service
information, go to the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html or call (202) 741-6030. To
view the AD docket, go to the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif
Building, Room PL-401, Washington, DC 20590-001 or on the Internet
at https://dms.dot.gov. The docket number is FAA-2005-20439;
Directorate Identifier 2005-CE-04-AD.
Issued in Kansas City, Missouri, on May 13, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-9976 Filed 5-20-05; 8:45 am]
BILLING CODE 4910-13-P
