Discussion
What events have caused this AD? The Federal Office for Civil Aviation (FOCA), which is the airworthiness authority for Switzerland, recently notified FAA that an unsafe condition may exist on Pilatus Models PC-12 and PC-12/45 airplanes. The FOCA reports that certain shock absorber attachment bolts (part number 532.10.12.110) in the main landing gear assemblies could fail during operation. Investigations revealed that an improper cadmium plating process applied to the high strength steel part causes the problem. This can cause hydrogen embrittlement.
The only bolts affected are those installed on main landing gear assemblies with a serial number that starts with AM.
What is the potential impact if FAA took no action? Failure of the main landing gear could lead to main landing gear collapse during operation with consequent loss of airplane control.
Has FAA taken any action to this point? We issued a proposal to amend part 39of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Pilatus Models PC-12 and PC-12/45 airplanes.
This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on January 9, 2004 (69 FR 1551). The NPRM proposed to require you to determine whether certain main landing gear shock absorber attachment bolts have been replaced and, if not replaced, would require you to replace shock absorber attachment bolts on main landing gear assemblies that have a serial number beginning with AM.
Comments
Was the public invited to comment? We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA's response to each comment:
Comment Issue No. 1: Limit the Effectivity of the AD
What is the commenter's concern? Two commenters want the effectivity of the AD limited to Pilatus Models PC-12 and PC-12/45 airplanes with serial numbers 101 through 482 (as listed in Pilatus SB PC12 Service Bulletin No: 32-015, dated September 12, 2003). The commenters state that the suspected bolts have been installed on a limited number of landing gears. Further, it is very unlikely that bolts have been swapped between airplanes. The proposed effectivity to all serial numbers will place an undue burden on owners and operators.
The commenters conclude that limiting the effectivity to airplanes with serial numbers 101 through 482 is enough to assure the airworthiness of Pilatus Models PC-12 and PC-12/45 airplanes.
What is FAA's response to the concern? We believe that the practice of swapping bolts is rare, however, it is still possible. To help alleviate this possibility, we are including the action of a logbook check in the AD.
We also believe that the swapping of the main landing gear assemblies is possible so limiting the airplane serial numbers is not enough to assure the airworthiness of Pilatus Models PC-12 and PC-12/45 airplan
We are not changing the final rule AD action as a result of theses comments.
Comment Issue No. 2: Limit Effectivity on the Shock-Absorber Attachment Bolts
What is the commenter's concern? Two commenters note that main landing gear assemblies with new bolts (part number (P/N) 532.10.12.110) marked "AT" or "VLG" are good bolts and do not require replacement.
The commenters request limiting the effectivity of the AD to those P/N 532.10.12.110 bolts not marked "AT" or "VLG."
What is FAA's response to the concern? We agree that the main landing gear assemblies with new bolts (part number (P/N) 532.10.12.110) marked "AT" or "VLG" are good bolts and do not require replacement.
We are changing the final rule AD action accordingly to reflect the commenters' request.
Comment Issue No. 3: AD Is Not Needed
What is the commenter's concern? One commenter suggests that the aviation industry has influence over FAA. Further, FAA neglects the public's concerns.
We infer that the commenters want us to withdraw the NPRM.
What is FAA's response to the concern? Through the NPRM process, FAA provides the public opportunity to comment on and influence the AD action.
Since the commenter gave no specific reasons to withdraw or change the proposed rule, we are not changing the final rule AD action as a result of these comments.
Comment Issue No. 4: Limit Effectivity on the Main Landing Gear Assemblies
What is the commenter's concern? One commenter requests that FAA limit the effectivity on the main landing gear assemblies to those assemblies with the serial numbers that start "AM001" through "AM053" since Pilatus has identified these were assembled with the defective bolts. The commenter notes that limiting the effectivity will lessen the impact on owners/operators.
What is FAA's response to the concern? The FAA agrees that the AD should limit the effectivity on the main landing gear assemblies.
We are changing the final rule AD action accordingly.
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 the changes discussed above and minor editorial corrections. We have determined that these changes and 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 includedin 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 260 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the affected airplanes? The manufacturer will provide parts free of charge and will pay for the estimated 3 workhours required to do the inspection and replacement of the shock absorber attachment bolts.
Compliance Time of This AD
What will be the compliance time of this AD? The compliance time of this AD is within the next 30 calendar days after the effective date of this AD.
Why is this compliance time presented in calendar time instead of hours time-in-service (TIS)? The unsafe condition exists or could develop on airplanes equipped with the affected parts regardless of airplane operation. For example, the unsafe condition has the same chance of occurring on an airplane with 50 hours TIS as it does on one with 5,000 hours TIS. Therefore, we are presenting the compliance time of this AD in calendar time instead of hours TIS.
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
under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD 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 "AD Docket No. 2003-CE-55-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
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: