[Federal Register Volume 70, Number 98 (Monday, May 23, 2005)]
[Rules and Regulations]
[Pages 29437-29440]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-9976]
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Rules and Regulations
Federal Register
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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 http://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:
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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:
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Actions Compliance Procedures
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(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: http://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 http://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]
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