[Federal Register: April 29, 2003 (Volume 68, Number 82)]
[Proposed Rules]
[Page 22636-22639]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr29ap03-27]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-CE-04-AD]
RIN 2120-AA64
Airworthiness Directives; AeroSpace Technologies of Australia Pty
Ltd. Models N22B and N24A Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede Airworthiness Directive
(AD) 82-12-06, which applies to certain AeroSpace Technologies of
Australia Pty Ltd. (ASTA) Models N22B and N24A airplanes. AD 82-12-06
currently requires repetitive visual inspections of all rudder control
lever shaft assemblies for cracks and discrepancies, and, if cracks or
discrepancies are found, it requires replacement with new or
serviceable rudder control shafts, and a check of the fit of all rod
end bearings in lever shafts. AD 82-12-06 also allows you to inspect
all lever shafts by magnetic particle inspection or dye penetrant
methods as terminating action for the repetitive visual inspections.
This proposed AD is the result of recent reports of failures of the
upper control lever torque shaft due to fatigue loading on the affected
airplanes, including those that included the terminating actions. This
proposed AD would require more detailed repetitive inspections (than
there are in AD 82-12-06) of the upper and lower rudder pedal torque
shafts and a one-time inspection for discrepancies in the thickness of
the lever shaft side plates with appropriate follow-up action. The
actions specified by this proposed 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.
DATES: The FAA must receive any comments on this rule on or before June
9, 2003.
ADDRESSES: Submit comments to FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2003-CE-04-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. You may view any
comments at this location between 8 a.m. and 4 p.m., Monday through
Friday, except Federal holidays. You may also send comments
electronically to the following address: 9-ACE-7_Docket@faa.gov.
Comments sent electronically must contain ``Docket No. 2003-CE-04-AD''
in the subject line. If you send comments electronically as attached
electronic files, the files must be formatted in
[[Page 22637]]
Microsoft Word 97 for Windows or ASCII text.
You may get service information that applies to this proposed AD
from Nomad Operations, Aerospace Support Division, Boeing Australia, PO
Box 767, Brisbane, QLD 4000 Australia; telephone 61 7 3306 3366;
facsimile 61 7 3306 3111. You may also view this information at the
Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Ron Atmur, Aerospace Engineer, FAA,
Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California 90712; telephone (562) 627-5224; facsimile (562)
627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
How do I comment on this proposed AD? The FAA invites comments on
this proposed rule. You may submit whatever written data, views, or
arguments you choose. You need to include the proposed rule's docket
number and submit your comments to the address specified under the
caption ADDRESSES. We will consider all comments received on or before
the closing date. We may amend this proposed rule in light of comments
received. Factual information that supports your ideas and suggestions
is extremely helpful in evaluating the effectiveness of this proposed
AD action and determining whether we need to take additional rulemaking
action.
Are there any specific portions of this proposed AD I should pay
attention to? The FAA specifically invites comments on the overall
regulatory, economic, environmental, and energy aspects of this
proposed rule that might suggest a need to modify the rule. You may
view all comments we receive before and after the closing date of the
rule in the Rules Docket. We will file a report in the Rules Docket
that summarizes each contact we have with the public that concerns the
substantive parts of this proposed AD.
How can I be sure FAA receives my comment? If you want FAA to
acknowledge the receipt of your mailed comments, you must include a
self-addressed, stamped postcard. On the postcard, write ``Comments to
Docket No. 2003-CE-04-AD.'' We will date stamp and mail the postcard
back to you.
Discussion
Has FAA taken any action to this point? 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 currently requires the following on
certain ASTA Models N22B and N24A airplanes:
--Repetitively inspecting visually all rudder control lever shafts
for cracking;
--If cracks are found, before further flight, 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.
What has happened since AD 82-12-06 to initiate this proposed
action? The Civil Aviation Safety Authority (CASA), which is the
airworthiness authority for Australia, recently notified FAA of the
need to change AD 82-12-06. The CASA reports failures of the rudder
control lever shaft. All the failures have occurred during ground
operations and nosewheel steering/rudder loads are now considered the
primary cause of the failure.
Some of the failures occurred on airplanes where the terminating
action of AD 82-12-06 was incorporated.
Is there service information that applies to this subject? ASTA has
issued Nomad Alert Service Bulletin ANMD-27-51, dated September 13,
2002.
What are the provisions of this service bulletin? The service
bulletin includes procedures for:
--Repetitively inspecting, using either dye penetrant or magnetic
particle methods and measurements, rudder control lever shafts 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 action did the CASA take? The CASA classified this service
bulletin as mandatory and issued Australian AD GAF-N22/44, dated
November 14, 2002, in order to ensure the continued airworthiness of
these airplanes in Australia.
Was this in accordance with the bilateral airworthiness agreement?
These airplane models 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.
Pursuant to this bilateral airworthiness agreement, the CASA has
kept FAA informed of the situation described above.
The FAA's Determination and an Explanation of the Provisions of This
Proposed AD
What has FAA decided? The FAA has examined the findings of the
CASA; reviewed all available information, including the service
information referenced above; and determined that:
--The unsafe condition referenced in this document exists or could
develop on Models N22B and N24A airplanes of the same type design that
are on the U.S. registry;
--The actions specified in the previously-referenced service
information should be accomplished on the affected airplanes including
those that have the terminating action of AD 82-12-06 incorporated; and
--AD action should be taken in order to correct this unsafe
condition.
What would this proposed AD require? This proposed AD would
supersede AD 82-12-06 with a new AD that would require the actions
specified in the above-referenced service information.
How does the revision to 14 CFR part 39 affect this proposed AD? On
July 10, 2002, FAA published a new version of 14 CFR part 39 (67 FR
47997, July 22, 2002), which governs FAA's AD system. This regulation
now includes material that relate to special flight permits,
alternative methods of compliance, and altered products. 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.
Cost Impact
How many airplanes would this proposed AD impact? We estimate that
this proposed AD affects 10 airplanes in the U.S. registry.
What would be the cost impact of this proposed AD on owners/
operators of the affected airplanes? We estimate the following costs to
accomplish this proposed initial inspection:
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Total cost
Labor cost Parts cost Per Airplane Total cost in U.S. operators
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12 workhours x $60 per hour = $720... Not Applicable................................... $720 10 x $720 = $7,200.
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[[Page 22638]]
We estimate the following costs to accomplish any necessary
repetitive inspections:
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Labor cost Parts cost Total cost per airplane
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2 workhours x $60 per hour = Not Applicable.............................. $120.
$120.
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We estimate the following costs to accomplish any necessary lever
shaft replacements that would be required based on the results of the
proposed inspections. We have no way of determining the number of
airplanes that may need such replacement:
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Labor cost Parts cost Total cost per airplane
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12 workhours x $60 per hour = $720....... $930 $720 + $930 = $1650.
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We estimate the following costs to accomplish any necessary lever
shaft side plate replacements that would be required based on the
results of the proposed inspection. We have no way of determining the
number of airplanes that may need such replacement:
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Labor cost Parts cost Total cost per airplane
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12 workhours x $60 per hour = $720....... $930 $720 + $930 = $1650.
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Regulatory Impact
Would this proposed AD impact various entities? The regulations
proposed herein would not have a substantial direct effect on the
States, on the relationship between the national government and the
States, or on the distribution of power and responsibilities among the
various levels of government. Therefore, it is determined that this
proposed rule would not have federalism implications under Executive
Order 13132.
Would this proposed AD involve a significant rule or regulatory
action? For the reasons discussed above, I certify that this action (1)
is not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated,
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. A copy of the draft regulatory evaluation
prepared for this action has been placed in the Rules Docket. A copy of
it may be obtained by contacting the Rules Docket at the location
provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
82-12-06, Amendment 39-4399, and by adding a new AD to read as follows:
Aerospace Technologies of Australia PTY LTD.: Docket No. 2003-CE-04-
AD; Supersedes AD 82-12-06, Amendment 39-4399.
(a) What airplanes are affected by this AD? This AD affects
Models N22B and N24A airplanes, all serial numbers, that are
certificated in any category.
(b) Who must comply with this AD? Anyone who wishes to operate
any of airplanes identified in paragraph (a) of this AD must comply
with this AD.
(c) What problem does this AD address? The actions specified by
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.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
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Actions Compliance Procedures
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(1) Inspect the rudder Within the next 100 In accordance with
control lever shafts, part hours time-in- Nomad Alert Service
numbers (P/N) 2/N-45-1102, service (TIS) after Bulletin ANMD-27-
1/N-45-1103, and 1/N-45- the effective date 51, dated September
1104 (or FAA-approved of this AD, unless 13, 2002, and the
equivalent part numbers) already applicable
for cracks use dye accomplished. maintenance manual.
penetrant while the shaft
is installed; or either dye
penetrant inspection or
magnetic particle methods
if the shaft is removed.
(2) Inspect all lever shaft Within the next 100 In accordance with
side plates on P/Ns 2/N-45- hours TIS after the Nomad Alert Service
1102, 1/N-45-1103, and 1/N- effective date of Bulletin ANMD-27-
45-1104 (or FAA-approved this AD, unless 51, dated September
equivalent part numbers) by already 13, 2002, and the
measuring the thickness for accomplished. applicable
discrepancies. maintenance manual.
[[Page 22639]]
(3) Visually inspect all Repetitively inspect In accordance with
rudder control lever shafts at intervals not to Nomad Alert Service
P/Ns 2/N-45-1102, 1/N-45- exceed 100 hours Bulletin ANMD-27-
1103, and 1/N-45-1104 (or TIS after the 51, dated September
FAA-approved equivalent inspection required 13, 2002, and the
part numbers) for cracks. in paragraph (d)(1) applicable
of this AD. maintenance manual.
(4) If damage is found Prior to further In accordance with
during any inspection flight after any Nomad Alert Service
required by this AD: inspection required bulletin ANMD-27-
(i) for lever shafts found by this AD. 51, dated September
with crack damage, replace 13, 2002, and the
with new or serviceable applicable
items. maintenance manual.
(ii) For discrepancies in
the thickness of lever
shaft side plates, obtain a
repair scheme from the
manufacturer through FAA at
the address specified in
paragraph (e) of this AD
and incorporate this repair
scheme.
(iii) Repairable and
nonrepairable damage is
defined in the service
information.
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(e) Can I comply with this AD in any other way?
(1) To use an alternative method of compliance or adjust the
compliance time, follow the procedures in 14 CFR 39.13. Send these
requests to the Manager, Los Angeles Aircraft Certification Office.
For information on any already approved alternative methods of
compliance, contact Ron Atmur, Aerospace Engineer, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
California 90712; telephone (562) 627-5224; facsimile (562) 627-
5210.
(2) Alternative methods of compliance approved in accordance
with AD 82-12-06, which is superseded by this AD, are not approved
as alternative methods of compliance with this AD.
(f) How do I get copies of the documents referenced in this AD?
You may obtain copies of the documents referenced in this AD from
Nomad Operations, Aerospace Support Division, Boeing Australia, PO
Box 767, Brisbane, QLD 4000 Australia; telephone 617 3306 3366;
facsimile 61 7 3306 3111. You may examine these documents at FAA,
Central Region, Office of the Regional Counsel, 901 Locust, Room
506, Kansas City, Missouri 64106.
(g) Does this AD action affect any existing AD actions? This
amendment supersedes AD 82-12-06, Amendment 39-4399.
Note: The subject of this AD is addressed in Australian AD GAF-
N22/44, dated November 14, 2002.
Issued in Kansas City, Missouri, on April 21, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-10516 Filed 4-28-03; 8:45 am]
BILLING CODE 4910-13-P