Discussion
Has FAA Taken Any Action to This Point?
Fatigue cracks found on the engine mount assemblies of certain Socata Models MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 150T, and Rallye 150ST airplanes caused us to issue AD 2002-05-04, Amendment 39-12672 (67 FR 10831, March 11, 2002). This AD requires the following on affected airplane models and serial numbers that are certificated in any category and do not have a part number 892-51-0-035-0 engine mount assembly (or FAA-approved equivalent part number) installed:
Repetitively inspecting any engine mount assembly that is not part number 892-51-0-035-0 (or FAA-approved equivalent part number) for cracks;
Repairing cracks that do not exceed a certain length;
Replacing the engine mount when the cracks exceed a certain length and cracks are found on an engine mount that already has two repairs; and
Terminating repetitive inspections after installing a partnumber 892-51-0-035-0 engine mount assembly, (or FAA-approved equivalent part number).
AD 2002-05-04 superseded AD 77-15-06, Amendment 39-2975, which required accomplishing the following:
Inspecting the engine mount assembly for cracks at repetitive intervals;
Repairing any cracks found; and
Modifying the brackets on airplanes with right angle engine mounts.
AD 2002-05-04 incorporated new manufacturer service information to address the unsafe condition, added additional airplane models to the applicability; and changed the initial compliance time for all airplanes.
Accomplishment of these actions is required in accordance with Socata Service Bulletin SB 156-71, dated May 2001.
What Has Happened Since AD 2002-05-04 to Initiate This Action?
The Direction Genenrale de l'Aviation Civile (DGAC), which is the airworthiness authority for France, recently notified FAA of the need to change AD 2002-05-04. The DGAC reports that affected airplanes equipped withan engine mount assembly part number 892-51-0-035-0 are also affected by fatigue cracking and should be included in the applicability section of AD 2002-05-04. Installing part number 892-51-0-035-0 is no longer considered a terminating action for the repetitive inspections and should be removed from all affected airplanes.
What Is the Potential Impact if FAA Took No Action?
This condition, if not detected and corrected, could cause the engine mount assembly to fail. Such failure could result in loss of control 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 Socata Models MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 150T, and Rallye 150ST airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on December 24, 2002 (67 FR 78394). The NPRM proposed to supersede AD 2002-05-04 with a new AD that would:
Retain the repetitive inspection and repair requirements of AD 2002-05-04;
Remove the terminating action;
Change the applicability section; and
Require replacement of all part number 892-51-0-035-0 engine mount assemblies with an FAA-approved equivalent part number.
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 theunsafe condition; and
Do not add any additional burden upon the public than was already proposed in the NPRM.
Cost Impact
How Many Airplanes Does This AD Impact?
We estimate that this AD affects 81 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 each inspections:
Labor cost
Parts cost
Total cost per airplane
Total cost on U.S. operators
1 workhour x $60 = $60
No parts required
$60
$60 x 81 = $4,860.
We estimate the following costs to accomplish any necessary repairs 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 repair:
Labor cost
Parts cost
Total cost per airplane
3 workhours x $60 = $180
No parts required
$180.
We estimate the following costs to accomplish the replacement. We have no way of determining the number of airplanesthat may need such replacement:
Labor cost
Parts cost
Total cost per airplane
20 workhours x $60 = $1,200
Approximately $3,360
$1,200 + 3,360 = $4,560.
What Is the Difference Between the Cost Impact of This AD and the Cost Impact of AD 2002-05-04?
The differences between this AD and AD 2002-05-04 are the correction to the applicability section, removal of the terminating action, and the addition of replacing all part number 892-51-0-035-0 engine mount assemblies. We have determined that this AD action does increase the cost impact over that required by AD 2002-05-04.
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 removing Airworthiness Directive (AD) 2002-05-04, Amendment 39-12672 (67 FR 10831, March 11, 2002), and by adding a new AD to read as follows: