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.
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 certain ASTA Models N22B and N24A. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on April 29, 2003 (68 FR 22636). The NPRM proposed to require you to repetitively inspect, using either dye penetrant or magnetic particle methods and measurements, 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.
Was the public invited to comment? The FAA encouraged interested persons to participate in the making of this amendment. We did not receive any comments on the proposed rule or on our determination of the cost to the public.
FAA's Determination
What is FAA's final determination on this issue? After careful review of all available information related to the subject presented above, we have determined that air safety and the public interest require the adoption of the rule as proposed except for minor editorial corrections. We have determined that these minor corrections:
--Provide the intent that was proposed in the NPRM for correcting the unsafe condition; and
--do not add any additional burden uponthe public than was already proposed in the NPRM.
How does the revision to 14 CFR part 39 affect this 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 relates 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 does this AD impact? We estimate that this AD affects 10 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 accomplish the initial inspection:
Labor cost
Parts cost
Total cost per airplane
Total cost on U.S. operators
12 workhours x $60 per hour = $720
Not Applicable
$720
10 x $720 = $7,200.
We estimate thefollowing costs to accomplish any necessary repetitive inspections:
Labor cost
Parts cost
Total cost per airplane
2 workhours x $60 per hour = $120
Not Applicable
$120
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:
Labor cost
Parts cost
Total cost per airplane
12 workhours x $60 per hour = $720.
$930
$720 + $930 = $1,650
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:
Labor cost
Parts cost
Total cost per airplane
12 workhours x $60 per hour = $720
$930
$720 + $930 = $1,650.
Regulatory Impact
Does this AD impact various entities? The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.
Does this 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) 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 final evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the RulesDocket at the location provided under the caption ADDRESSES.
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:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
39.13 [Amended]
2. FAA amends 39.13 by removing Airworthiness Directive (AD) 82- 12-06, Amendment 39-4399, and by adding a new AD to read as follows: