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Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations
course of business or by the means identified in ADDRESSES.
Differences Between This AD and the MCAI
The MCAI only requires inspection of the tension rods if the IFFAs are modified because they have been found to have the incorrect shape. Due to the length of time between manufacture and the issuance of this AD, operators could have installed an affected tension rod onto an airplane that was not manufactured with the defective part.
Therefore, this AD requires inspection for chafing damage on the tension rods on all Model PC12/47E airplanes that have an affected tension rod installed.
Costs of Compliance The FAA estimates that this AD will affect 18 products of U.S. registry. The FAA also estimates that it will take about 2.5 work-hours per product to comply with the requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $1,600 per product.
Based on these figures, the FAA
estimates the cost of this AD on U.S.
operators will be $32,634 or $1,813 per product.
The FAA has included all costs in this cost estimate. According to the manufacturer, however, all or some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected operators.
Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more detail the scope of the Agencys authority.
The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA
with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce.
This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings This AD will not have federalism implications under Executive Order
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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.
For the reasons discussed above, I
certify that this AD:
1 Is not a significant regulatory action under Executive Order 12866, 2 Will not affect intrastate aviation in Alaska, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by adding the following new airworthiness directive:

20210204 Pilatus Aircraft Ltd.:
Amendment 3921387; Docket No.
FAA20200813; Product Identifier 2019CE040AD.
a Effective Date This airworthiness directive AD is effective March 30, 2021.
b Affected ADs None.
c Applicability This AD applies to Pilatus Aircraft Ltd.
Model PC12/47E airplanes, all serial numbers S/Ns, certificated in any category.
d Subject Joint Aircraft System Component JASC
Code 2700: Flight Controls.
e Reason This AD was prompted by mandatory continuing airworthiness information MCAI
originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI
describes the unsafe condition as inboard
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flap fairings aft IFFAs having an incorrect shape. The FAA is issuing this AD to prevent chafing between the IFFA and the front inboard tension rod, and consequent corrosion of the bare rod aluminum tube and reduced aluminum thickness. This condition, if not corrected, could lead to failure of the inboard flap drive arm, asymmetric flap extension, and reduced control of the airplane.
f Actions and Compliance 1 For airplanes with a S/N 1576 and higher, unless already done, within 100
hours time-in-service TIS after the effective date of this AD or within 6 months after the effective date of this AD, whichever occurs first, inspect the left-hand LH and righthand RH IFFAs for correct shape and clearance with the LH and RH tension rods by following step 3.B.1 and Figures 2 and 3 of the Accomplishment Instructions Aircraft in Pilatus PC12 Service Bulletin No:
27026, dated July 10, 2019 Pilatus SB 27
026.
i If the shape of the LH or RH IFFA is incorrect or if the clearance between the IFFA and the tension rod is less than 5 mm 0.2 inch, before further flight, modify the IFFA and inspect the tension rods for chafing by following section 3.C. of the Accomplishment InstructionsAircraft in Pilatus SB 27026.
ii If the shape of the LH and RH IFFAs is correct and the clearance between the IFFA
and the tension rod is at least 5 mm 0.2
inch, before further flight, inspect the front inboard LH and RH tension rods for chafing by following step 3.C.12a of the Accomplishment InstructionsAircraft in Pilatus SB 27026. If the LH or RH tension rod has any chafing, before further flight, replace the tension rod by following step 3.C.12b of the Accomplishment InstructionsAircraft in Pilatus SB 27026.
2 For airplanes with a S/N 1001 through S/N 1575, inclusive, that have a tension rod part number P/N 527.52.12.135 installed, unless already done, within 100 hours TIS
after the effective date of this AD or within 6 months after the effective date of this AD, whichever occurs first, inspect the front inboard LH and RH tension rods for chafing by following step 3.C.12a of the Accomplishment InstructionsAircraft in Pilatus SB 27026. If the LH or RH tension rod has any chafing, before further flight, replace the tension rod by following step 3.C.12b of the Accomplishment InstructionsAircraft in Pilatus SB 27026.
3 For all Model PC12/47E airplanes, as of the effective date of this AD, do not install on any airplane an LH IFFA P/N
557.52.12.223, RH IFFA P/N 557.52.12.224, or tension rod P/N 527.52.12.135 unless the part has been inspected and all corrective actions have been taken as required by this AD.
g Alternative Methods of Compliance AMOCs
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23FER1