Discussion
What Events Have Caused This AD?
The Civil Aviation Safety Authority (CASA), which is the airworthiness authority for Australia, notified FAA that an unsafe condition may exist on certain Eagle Model 150B airplanes. The CASA reports an occurrence where frayed rudder cables were found on an Eagle Model 150B airplane. Further investigation reveals that the diameter of the rudder cable pulleys is too small and cables rub against these pulleys.
What Are the Consequences If the Condition Is Not Corrected?
Continued airplane operation with damaged cables could result in rudder cable system failure with possible loss of airplane control.
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 Eagle Model 150B airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on January 2, 2001 (66 FR 59). The NPRM proposed to require you to:
--Inspect the rudder cables for fraying, broken strands, etc. (referred to as damage), and replace any damaged cables; and
--Replace the rudder cable pulleys with larger diameter pulleys to eliminate the possibility of further damage.
Was the Public Invited To Comment?
Interested persons were afforded an opportunity to participate in the making of this amendment. We have given due consideration to the comment received.
Comment Disposition
What Is the Commenter's Concern?
Eagle Aircraft Pty. Ltd requests that FAA withdraw the AD because pulley replacement kits to correct the unsafe condition have been shipped to the United States and all affected airplanes models may already be in compliance with this AD.
What Is FAA's Response To the Concern?
We do not concur. Although there may be airplanes on the U.S. Register that have already incorporated the kit installation, the AD isstill justified. Issuing an AD is the only way to assure that:
--The installation of the pulley replacement kit is incorporated on any U.S.-registered airplane;
--The actions are accomplished on any airplane that is imported from another country and placed on the U.S. Register; and
--The installation continues to be incorporated on all U.S. registered airplanes.
We have not changed the AD as a result of this comment.
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 determined that these minor corrections:
--Will not change the meaning of the AD; and
--Will not add any additional burden upon the public than was already proposed.
Cost Impact
How Many Airplanes Does This AD Impact?
We estimate that this AD affects 5 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 inspection of the rudder cable and replacement of the rudder cable pulley:
Labor cost
Parts cost
Total cost per airplane
Total cost
on U.S. operators
5 workhours x $60
$286
$586
$2,930
Replacement cables, if necessary, will cost $305 per airplane. We have no way of determining the number of rudder cables that will be found damaged during the inspection.
Compliance Time of this AD
What Is the Compliance Time of This AD?
The compliance time of this AD will be to accomplish the inspection and rudder cable pulley replacement "within the next 100 hours time- in-service (TIS) after the effective date of this AD" and to accomplish any necessary cable replacement "prior to further flight after the inspection."
Why Are the Compliance Times of the Australian AD Different From the Compliance Times in This AD?
The Australian AD requires (on Eagle Model 150B airplanes registered in Australia) the inspection within the next 5 hours of service and requires the pulley replacement within 100 hours of operation. These are the compliance times specified in the service information.
We do not have justification to require the inspection within 5 hours of service. We use compliance times such as this when we have identified an urgent safety of flight situation. We believe that 100 hours TIS will give the owners/operators of the affected airplanes enough time to have the inspection and replacement accomplished without compromising the safety of the airplanes.
By accomplishing both the inspection and replacement at the same time, the owners/operators of the affected airplanes only have their airplanes out of service once instead of twice.
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 Rules Docket 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.
Sec. 39.13 [Amended]
2. FAA amends Sec. 39.13 by adding a new AD to read as follows: