[Federal Register Volume 85, Number 104 (Friday, May 29, 2020)]
[Proposed Rules]
[Pages 32308-32315]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-11340]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0049; Product Identifier 2017-CE-031-AD]
RIN 2120-AA64


Airworthiness Directives; Textron Aviation Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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SUMMARY: The FAA is revising an earlier proposal for certain Textron 
Aviation Inc. (Textron) Model 172N, 172P, 172Q, 172RG, F172N, F172P, 
FR172K, R172K, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 
182P, 182Q, 182R, T182, F182P, F182Q, F182RG, R182, TR182, 206, P206/
TP206, U206/TU206, 207/T207, 210-5 (205), 210-5A (205A), 210B, 210C, 
210D, 210E, 210F, and T210F airplanes. This action revises the

[[Page 32309]]

notice of proposed rulemaking (NPRM) by modifying the estimated costs 
of the proposed AD, the repetitive inspection intervals, and the credit 
allowed for previous actions; clarifying the inspection instructions 
for airplanes with the service kit installed; correcting the contact 
information for obtaining the service information; and adding a 
reporting requirement to collect the inspection results. The FAA is 
proposing this airworthiness directive (AD) to address the unsafe 
condition on these products. Since these actions would impose an 
additional burden over those in the NPRM based on comments from 
commenters, the FAA is reopening the comment period to allow the public 
the chance to comment on these changes.

DATES: The comment period for the NPRM published in the Federal 
Register on February 1, 2018 (83 FR 4605), is reopened.
    The FAA must receive comments on this SNPRM by July 13, 2020.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this SNPRM, contact Textron 
Aviation Inc., Textron Aviation Customer Service, One Cessna Blvd., 
Wichita, Kansas 67215; telephone: (316) 517-5800; email: 
[email protected]; internet: https://support.cessna.com. You may 
review this referenced service information at the FAA, Airworthiness 
Products Section, Operational Safety Branch, 901 Locust, Kansas City, 
Missouri 64106. For information on the availability of this material at 
the FAA, call (816) 329-4148.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0049; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this SNPRM, any comments received, and other information. The street 
address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, Aerospace Engineer, 
Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209; 
telephone: (316) 946-4155; fax: (316) 946-4107; email: 
[email protected] or [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0049; 
Product Identifier 2017-CE-031-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this SNPRM. The FAA will 
consider all comments received by the closing date and may amend this 
SNPRM because of those comments.
    The FAA will post all comments, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this SNPRM.

Discussion

    The FAA issued an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to certain Textron (type certificate previously held by 
Cessna Aircraft Company) Model 172N, 172P, 172Q, 172RG, F172N, F172P, 
FR172K, R172K, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 
182P, 182Q, 182R, T182, F182P, F182Q, F182RG, R182, TR182, 206, P206/
TP206, U206/TU206, 207/T207, 210-5 (205), 210-5A (205A), 210B, 210C, 
210D, 210E, 210F, and T210F airplanes. The NPRM published in the 
Federal Register on February 1, 2018 (83 FR 4605). The NPRM was 
prompted by a report from an operator of one of the affected Textron 
airplanes that cracks were found in the lower area of the forward cabin 
doorpost bulkhead. The NPRM proposed to require repetitively inspecting 
the lower area of the forward cabin doorposts at the strut attach 
fitting for cracks and repairing any cracks found by modifying the area 
with the applicable service kit.

Comments

    The FAA gave the public the opportunity to comment on the NPRM. The 
following presents the comments received on the NPRM and the FAA's 
response to each comment.

Request To Withdraw the NPRM

    Matt Gunsch stated that cracking at the location identified in the 
NPRM was not observed while performing annual inspections on hundreds 
of Cessna airplanes as a mechanic with an Inspection Authorization. The 
commenter explained that these inspections were on airplanes from the 
Model 172A to the newest restart airplane, with some flown as little as 
25 hours a year to others that were flown l,000 hours a year, all with 
no evidence of cracking at this location. The FAA infers the commenter 
would like to see the NPRM withdrawn.
    The FAA disagrees. The FAA's investigation revealed more than four 
dozen similar cracks on Textron Model 100- and 200-series airplanes. 
The FAA has not changed this proposed AD based on this comment.

Requests To Change the Repetitive Inspection Compliance Intervals

    Mark Stephenson, Ronald Welch, the Aircraft Owners and Pilots 
Association (AOPA), Kermit Bunde, Matt Gunsch, Howard Nelson, and an 
anonymous commenter requested the FAA change the compliance time for 
the repetitive inspection intervals to hours TIS only and remove the 
12-month calendar time inspection requirement. Neal Bachman suggested 
the compliance time be based on take off and landing cycles. Most of 
these commenters stated the cracking identified in the proposed AD was 
attributed to metal fatigue, which is driven by usage, not calendar 
time. Several commenters noted that an annual repetitive inspection 
adds an unnecessary burden for operators of low-use airplanes that may 
accumulate less than 1,000 hours TIS per year. The anonymous commenter 
stated that a repetitive inspection every 12 months was unjustified and 
unsupported because the FAA did not include in the AD docket crack-
propagation math models or show raw data indicating the number of 
airplanes with cracks, their associated TIS, or the crack lengths.
    Craig Morton requested the FAA change the multiple compliance time 
interval from ``whichever occurs first'' to ``whichever occurs later.''
    David Scott requested that the FAA increase the repetitive interval 
depending on airplane configuration.
    The FAA partially agrees. The FAA did not provide the data 
requested by

[[Page 32310]]

the anonymous commenter because the raw data relied upon by the FAA in 
its risk analysis did not include crack lengths. The FAA agrees to 
revise the calendar time requirement because a repetitive inspection 
annually does not account for low use airplanes. The FAA has adjusted 
the proposed repetitive inspection interval from 12 months or 1,000 
hours TIS to 36 calendar months or 1,000 hours TIS. The FAA has 
determined this extended compliance time adequately addresses the 
identified unsafe condition. In addition, this compliance time 
corresponds with the manufacturer's guidance, for certain airplanes, 
that is published in supplemental inspection documents (SIDs) and is 
supported by the fleet history. The FAA disagrees with providing an 
allowance for takeoff and landing cycles because there is insufficient 
data to support inspection intervals based on this aspect of an 
airplane's usage. Also, FAA regulations do not require all operators to 
maintain records of landing and takeoff cycles. The FAA also disagrees 
with the requests to base the inspection solely on flight hours and to 
increase the inspection interval. In developing appropriate compliance 
times for this proposed AD, the FAA considered the urgency associated 
with the subject unsafe condition, the manufacturer's recommended 
compliance times, the availability of parts, and the practical aspect 
of accomplishing the required inspection and any on-condition actions. 
In light of these factors, the FAA determined the proposed compliance 
times are appropriate and address the identified unsafe condition.

Request To Decrease the Initial Inspection Compliance Time

    An anonymous commenter suggested the FAA require the initial 
inspection before 4,000 hours TIS. The commenter stated that cracking 
might occur in airplanes before the 4,000 hours TIS identified in the 
proposed AD.
    The FAA partially agrees. The FAA agrees that unverified reports 
indicate cracking may occur before an airplane accumulates 4,000 hours 
TIS. However, the FAA disagrees with reducing the compliance time for 
the initial inspection at this time because the data available from the 
manufacturer and from the FAA service difficulty reporting system does 
not contain sufficient information to justify it. The FAA has added a 
reporting requirement to the proposed AD to help the FAA collect more 
data to determine if the cracking is occurring at an earlier period. 
The FAA will analyze the reporting results and may take further 
rulemaking action.

Requests To Clarify the Repetitive Inspection Instructions

    Two commenters requested the FAA clarify the repetitive inspection 
instructions for airplanes that have a service kit installed. Adam 
Ondrajka noted it is more difficult to do the inspection after 
installation of the service kit because it covers some of the area 
susceptible to cracking. Hageland Aviation Services, Inc. (Hageland 
Aviation) requested the proposed AD be revised to include verbiage that 
allows the inspection to be performed with the service kit remaining in 
place, and inspecting for any cracking that has propagated past the 
boundaries of the kit. This commenter also stated that the term ``to 
the fullest extent'' in the repetitive inspection instructions for 
airplanes with a service kit installed is unclear and could be 
interpreted to require removal of the kit to complete the inspection.
    The FAA agrees. The FAA has changed the proposed inspection 
language to clarify the service kit should not be removed during the 
inspections and to inspect for cracks extending beyond the modified 
parts.

Requests Regarding the Service Kits

    AOPA requested the FAA allow the installation of the service kit to 
terminate the repetitive inspection requirements of the proposed AD. 
AOPA and Adam Ondrajka noted that installation of the kit is 
terminating action in Cessna Mandatory Service Bulletins SEB 93-5R1 and 
SEB 95-19, and the FAA did not provide justification or reasoning in 
the NPRM for continuing the repetitive inspections after installation 
of the kit.
    Neal Bachman requested the FAA encourage the installation of the 
service kit preemptively to prevent future cracking, and stated that if 
ongoing inspections are required after the service kit is installed 
then the kit is inadequate.
    The FAA partially agrees. Owners may voluntarily install the 
service kit, as neither the NPRM nor this SNPRM would prohibit the 
installation of the service kit prior to observed cracking. The 
structure added by the service kit reinforces the critical area on 
which cracking has been found. However, the manufacturer did not 
provide sufficient evidence that installation of the service kits 
corrects the unsafe condition and therefore warrants discontinuing the 
inspections. In addition, the FAA has received unconfirmed reports of 
cracking extending beyond the repair doubler that is installed as part 
of the kit. At this time, sufficient information is not available to 
determine the cause of the continued cracking. Therefore, the FAA has 
added a reporting requirement to this SNPRM to evaluate the crack 
development.

Comment Regarding Variable Time Limit for Kit Installation

    Mark Stephenson requested the FAA change the compliance time for 
installing the service kit after crack detection to a variable 
compliance time based on the size, number, or severity of the 
identified cracking. The commenter noted that the proposed AD specifies 
installing the service kit before further flight if cracks are found, 
while at the same time specifying a 1,000-hour repeat inspection of the 
area if no cracks are found. The commenter stated that therefore the 
FAA is accepting that flight with cracks is acceptable for periods 
approaching 1,000 hours and concluded the logic for the requirement to 
incorporate the service kit before further flight is flawed.
    The FAA disagrees. There is insufficient data on crack growth rate 
to support flight with known cracks without installation of the service 
kit. Therefore, this proposed AD would not allow variable compliance 
times based on the size, number, or severity of the identified 
cracking. The installation of the service kit reinforces the cracked 
area. The FAA has not changed this SNPRM based on this comment.

Concern for Parts Availability

    Urban Moore, Hageland Aviation, Bruce Thomas, and Paul Gryko 
expressed concern that the proposed AD may ground airplanes after 
cracks are identified because of the unavailability of parts. The 
commenters indicated that waiting times for some of the service kits 
were several months.
    The FAA recognizes the demand for the service kits following the 
issuance of the proposed AD is likely to increase. However, the FAA has 
determined that the proposed actions and compliance times are necessary 
to address the identified unsafe condition. The FAA has not changed 
this proposed AD based on this comment. However, operators may request 
approval of an alternative method of compliance (AMOC) to extend the 
compliance times under the provisions of paragraph (m) of this proposed 
AD. The operator must justify in the request that an extension of the 
compliance time will provide an adequate level of safety.

[[Page 32311]]

Request for Specific Part Numbers

    Urban Moore noted that Textron would not provide the specific part 
numbers for each item included in the service kits.
    The FAA disagrees. The applicable service kits identify the part 
numbers required for the kit installation. The FAA will post in the AD 
docket all service documents incorporated by reference when the FAA 
issues the final rule. Until then, and as specified in the ADDRESSES 
section of the NPRM and this SNPRM, interested parties may contact 
Textron for a copy of the service information identified in this SNPRM. 
A party may also view the service information in person at the FAA's 
offices in Kansas City, Missouri.

Request To Include the Possibility of Extended Cracks

    Textron suggested the FAA change the language in the proposed AD to 
reflect that cracks could extend beyond the doublers installed in 
accordance with the service kits, if an operator installed a service 
kit before the AD was released.
    The FAA agrees. The FAA has added language to paragraphs (g) and 
(h)(2) of this proposed AD to address potential cracking on airplanes 
with the service kits installed.

Request To Make Service Information Available

    Matt Gunsch commented about the difficulty obtaining the service 
bulletins that are the basis of the proposed AD and requested the FAA 
include the referenced service documents in the AD Docket.
    The FAA partially agrees. The FAA will post in the AD docket all 
service documents incorporated by reference when the FAA issues the 
final rule. Until then, and as specified in the ADDRESSES section of 
the NPRM and this SNPRM, interested parties may contact Textron for a 
copy of the service information identified in this SNPRM. A party may 
also view the service information in person at the FAA's offices in 
Kansas City, Missouri.

Request To Update Service Information

    Textron requested the FAA update references to the service bulletin 
and service kit information in the proposed AD to reflect the latest 
revision levels.
    The FAA agrees. The FAA has updated the service information in this 
proposed AD accordingly.

Request To Provide Credit for Airplanes With SK206-42 or SK206-42A 
Installed

    Textron requested the FAA clarify the credit in paragraph (k)(3) of 
the proposed AD for Model 207 and T207 airplanes that have installed a 
service kit in accordance with Cessna Single Engine Service Bulletin 
SEB 93-5, dated March 26, 1993. Specifically, Textron asked whether 
owners/operators are expected to remove the kit and install a new kit.
    The FAA agrees to clarify the credit for Model 207 and T207 
airplanes. The FAA has revised paragraph (k)(3) of the NPRM and 
redesignated it as paragraph (k)(2)(i) in this SNPRM. As now proposed, 
paragraph (k)(2)(i) specifies that the reinforcement detailed in Cessna 
Single Engine Service Kit SK207-19A, dated May 29, 2019, must be done 
to receive credit for previous installations. As specified in Cessna 
Single Engine Service Kit SK207-19A, dated May 29, 2019, the 
reinforcement can be done on airplanes with a previously installed 
SK206-42() kit.

Request To Allow Credit for Previous Actions

    Hageland Aviation, Jason Vink, Stephen Greenwood, Adam Ondrajka, 
AOPA, Textron, and an anonymous commenter requested the FAA allow 
credit for initial inspections and service kit installations in 
accordance with Cessna Service Bulletins SEB 93-5, SEB 93-5 Revision l, 
and SEB 95-19. Hageland Aviation stated that failing to give credit 
could affect intrastate aviation within the state of Alaska. Adam 
Ondrajka stated that paragraphs (k)(1)(v) and (k)(3) of the proposed AD 
include contradictory language for previous repairs completed on Model 
207 and T207 airplanes. Textron and an anonymous commenter requested 
credit for inspections that have been previously completed.
    The FAA partially agrees. Paragraph (f), ``Compliance,'' of both 
the NPRM and this SNPRM states compliance is required ``unless already 
done,'' which allows credit for any AD action completed before the 
effective date of the AD.
    The FAA has revised paragraphs (k)(1) and (2) of this SNPRM to 
provide credit for most airplane models that have installed the service 
kit using Cessna Single Engine Service Bulletin SEB 93-5, dated March 
26, 1993; or Cessna Single Engine Service Bulletin SEB 93-5, Revision 
1, dated September 8, 1995. The FAA has also revised paragraph (k)(3) 
(redesignated as paragraph (k)(2)(i) in this SNPRM) to allow credit for 
Model 207, T207, 207A, and T207A airplanes that have installed the 
service kit if additional reinforcement has also been done.
    The FAA disagrees that the language in paragraphs (k)(1)(v) and 
(k)(3) of the NPRM is contradictory. Paragraph (k)(1)(v) of the NPRM 
applies only to the inspection, while paragraph (k)(3) of the NPRM 
applies to the repair. Similarly, paragraph (k)(1) of this SNPRM 
applies only to the inspection, while paragraph (k)(2) of this SNPRM 
applies to the repair.
    The FAA acknowledges Hageland Aviation's comment that intrastate 
aviation within the state of Alaska will be affected if credit is not 
given. The FAA has revised paragraph (k) of this SNPRM to provide 
credit for most airplane models that have installed the service kit. 
Additionally, paragraph (f), ``Compliance,'' of both the NPRM and the 
SNPRM states compliance is required ``unless already done,'' which 
allows credit for any AD action completed before the effective date of 
the AD. Therefore, the FAA is giving credit for previous actions.

Requests To Change the Costs of Compliance

    AOPA, Urban Moore, Duane Taylor, Ely Cyrus, Hageland Aviation, 
Stephen Greenwood, Neal Bachman, Howard Nelson, an anonymous commenter, 
Paul Gryko, and Richard James requested the FAA update the costs of the 
service kits. These commenters stated the estimated costs in the NPRM 
for the installation of the service kits did not represent the current 
costs of the kits. The commenters also expressed concern that Textron 
was increasing the prices of the service kits.
    The FAA agrees. The FAA has revised the estimated cost of the 
service kits to account for the known costs.
    Urban Moore requested the FAA increase the number of labor hours 
estimated to complete the repair.
    The FAA agrees. The FAA has increased the estimated work-hours to 
install the service kits from 24 work-hours to 36 work-hours.
    An anonymous commenter stated the labor rate of $85 per work-hour 
is out of date.
    The FAA disagrees. The FAA Office of Aviation Policy and Plans 
provides the labor rate of $85 per work-hour to use when estimating the 
labor costs of complying with AD requirements.
    An anonymous commenter stated the estimated cost in the NPRM should 
be doubled to account for the cost to repair the doorposts for both 
wing struts.
    The FAA disagrees. The estimated costs in both the NPRM and this

[[Page 32312]]

SNPRM already account for repairs on both sides of the airplane.

Request To Correct the Language in the Cost of Compliance for Affected 
Products

    An anonymous commenter noted an error in the estimated costs and 
stated that the Cost of Compliance section incorrectly refers to 2,928 
engines instead of the correct number of airplanes.
    The FAA disagrees. The Cost of Compliance section in the NPRM 
estimates that the proposed AD would affect 14,653 airplanes of U.S. 
registry; it does not refer to the number of affected engines. The FAA 
has not changed this proposed AD based on this comment.

Request To Change the Manufacturer Contact Information

    Textron requested the FAA change the internet contact information 
for contacting the manufacturer to https://support.cessna.com.
    The FAA agrees. The FAA has updated the contact information 
accordingly.

Request for Docket Correction

    Stephen Greenwood noted that in the NPRM the docket number is 
incorrectly listed as FAA-2017-0049 instead of FAA-2018-0049. The FAA 
infers that the commenter is requesting that the FAA correct the docket 
number.
    The FAA agrees. The FAA published a proposed rule; correction 
because of the docket number error in the NPRM on February 13, 2018 (83 
FR 6136). This SNPRM references the correct docket number.

Request To Extend the Comment Period

    Howard Nelson stated that after the proposed AD is updated with the 
correct costs for the repair kit, the FAA should extend the comment 
period.
    The FAA agrees. The FAA has updated the estimated cost of the 
repair service kit and has made other changes that increase the burden 
on the operators. Therefore, the FAA is issuing this SNPRM to allow 
further comment on these changes.

Other Differences Between the NPRM and This SNPRM

    Table 1 to paragraph (c) of this SNPRM contains changes to some of 
the model designations listed in the applicability in order to match 
the models as they are listed in the type certificate data sheet. Where 
the NPRM referred to ``P206/TP206,'' ``U206/TU206,'' and ``207/T207,'' 
series of airplanes, this SNPRM identifies the following model 
designations: P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, 
TP206C, TP206D, TP206E, U206, U206A, U206B, U206C, U206D, U206E, U206F, 
U206G, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, 207, 
207A, T207, and T207A.
    The Model ``F182RG'' listed in Table 1 to paragraph (c) of the NPRM 
was based on the model designation specified in the service 
information. Table 1 to paragraph (c) of this SNPRM lists ``Model 
FR182,'' which is the correct model designation as it is listed in the 
type certificate data sheet for that model.
    This SNPRM also clarifies the affected serial numbers listed in 
table 1 to paragraph (c) of the NPRM. Where the table to paragraph (c) 
of this SNPRM identifies an affected serial number range that includes 
all eligible serial numbers for a given model, the FAA has instead 
specified ``All serial numbers'' in this SNPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Cessna Single Engine Service Bulletin SEB 95-19, 
dated December 29, 1995 (SEB 95-19); and Cessna Single Engine Service 
Bulletin SEB 93-5, Revision 2, dated May 29, 2019 (SEB 93-5R2). For the 
applicable model airplanes, the service information contains procedures 
for repetitively inspecting the lower area of the forward cabin 
doorposts for cracks and repairing any cracks found by modifying the 
area with an applicable Cessna service kit.
    The FAA also reviewed Cessna Single Engine Service Kit SK207-19A, 
dated May 29, 2019. The service information contains procedures to 
reinforce the lower forward doorpost bulkhead and wing strut fitting by 
adding a doubler and a channel to each forward cabin doorpost bulkhead.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Other Related Service Information

    The FAA reviewed Cessna Single Engine Service Kit SK172-147, dated 
December 29, 1995. This service kit provides instructions to add a 
channel to each forward cabin doorpost bulkhead. The FAA also reviewed 
Cessna Single Engine Service Kit SK182-115, dated December 29, 1995; 
Cessna Single Engine Service Kit SK206-42D, dated May 29, 2019; and 
Cessna Single Engine Service Kit SK210-156, dated December 29, 1995. 
For the applicable model airplanes, these service kits provide 
instructions to add a doubler and a channel to each forward cabin 
doorpost bulkhead.

FAA's Determination

    The FAA is proposing this AD because the FAA evaluated all the 
relevant information and determined the unsafe condition described 
previously is likely to exist or develop in other products of the same 
type design. Certain changes described above expand the scope of the 
NPRM. As a result, the FAA has determined that it is necessary to 
reopen the comment period to provide additional opportunity for the 
public to comment on this SNPRM.

Proposed Requirements of This SNPRM

    This SNPRM would require repetitively inspecting the lower area of 
the forward cabin doorposts for cracks and repairing any cracks found 
by modifying the area with the applicable Cessna service kit.

Costs of Compliance

    The FAA estimates that this proposed AD would affect 14,653 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
             Action                      Labor cost              Parts cost          product        operators
----------------------------------------------------------------------------------------------------------------
Inspect the lower area of the     1.5 work-hours x $85 per  Not applicable.....         $127.50    $1,868,257.50
 forward cabin doorposts for       hour = $127.50.
 cracks.
Reporting requirement...........  1 work-hour x $85 per     Not applicable.....              85        1,245,505
                                   hour = $85.
----------------------------------------------------------------------------------------------------------------


[[Page 32313]]

    The FAA estimates the following costs to do any necessary repairs 
that would be required based on the results of the proposed inspection. 
Reference the applicable Cessna single engine service bulletin for kit 
applicability. The FAA has no way of determining the number of 
airplanes that might need this repair:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Install Cessna Single-Engine Service Kit     36 work-hours x $85 per hour =               $3,415          $6,475
 SK172-147.                                   $3,060.
Install Cessna Single-Engine Service Kit     36 work-hours x 85 per hour = 3,060           7,490          10,550
 SK182-115.
Install Cessna Single-Engine Service Kit     36 work-hours x 85 per hour = 3,060           3,115           6,175
 SK206-42D.
Install Cessna Single-Engine Service Kit     36 work-hours x 85 per hour = 3,060           4,957           8,017
 SK207-19A.
Install Cessna Single-Engine Service Kit     36 work-hours x 85 per hour = 3,060           7,020          10,080
 SK210-156.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a currently valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to be 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, completing and reviewing the collection of 
information. All responses to this collection of information are 
mandatory. Send comments regarding this burden estimate or any other 
aspect of this collection of information, including suggestions for 
reducing this burden to: Information Collection Clearance Officer, 
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 
76177-1524.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's 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 Agency's 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 airplanes 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

    The FAA determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Textron Aviation Inc.: Docket No. FAA-2018-0049; Product Identifier 
2017-CE-031-AD.

(a) Comments Due Date

    The FAA must receive comments by July 13, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the following Textron Aviation Inc. (type 
certificate previously held by Cessna Aircraft Company) model 
airplanes, certificated in any category:

      Table 1 to Paragraph (c)--Affected Models and Serial Numbers
------------------------------------------------------------------------
            Model                             Serial Nos.
------------------------------------------------------------------------
172N.........................  17272885 through 17274009 inclusive.
172P.........................  All serial numbers.
172Q.........................  17275869, 17275927 through 17275934
                                inclusive, 17275952, 17275959, 17275960,
                                17275962, 17275964, 17275965, 17275967,
                                17275968, 17275969, 17275971, 17275992,
                                17275999, 17276002, 17276005, 17276029,
                                17276032, 17276042, 17276045, 17276051,
                                17276052, 17276054, 17276101, 17276109,
                                17276140, 17276147, 17276188, and
                                17276211.
172RG........................  All serial numbers.
F172N........................  F17201910 through F17202039 inclusive.
F172P........................  All serial numbers.

[[Page 32314]]

 
FR172K.......................  FR17200656 through FR17200675 inclusive.
R172K........................  R1723200 through R1723454 inclusive.
182E.........................  All serial numbers.
182F.........................  All serial numbers.
182G.........................  All serial numbers.
182H.........................  All serial numbers.
182J.........................  All serial numbers.
182K.........................  All serial numbers.
182L.........................  All serial numbers.
182M.........................  All serial numbers.
182N.........................  All serial numbers.
182P.........................  All serial numbers.
182Q.........................  All serial numbers.
182R.........................  All serial numbers.
T182.........................  All serial numbers.
F182P........................  All serial numbers.
F182Q........................  All serial numbers.
FR182........................  All serial numbers.
R182.........................  R18200002 through R18200583 inclusive.
R182 and TR182...............  R18200001 and R18200584 through R18202039
                                inclusive.
206..........................  All serial numbers.
P206, P206A, P206B, P206C,     All serial numbers.
 P206D, P206E, TP206A,
 TP206B, TP206C, TP206D, and
 TP206E.
U206, U206A, U206B, U206C,     All serial numbers.
 U206D, U206E, U206F, U206G,
 TU206A, TU206B, TU206C,
 TU206D, TU206E, TU206F, and
 TU206G.
207, 207A, T207, and T207A...  All serial numbers.
210-5 (205)..................  All serial numbers.
210-5A (205A)................  All serial numbers.
210B.........................  All serial numbers.
210C.........................  All serial numbers.
210D.........................  All serial numbers.
210E.........................  All serial numbers.
210F.........................  All serial numbers.
T210F........................  All serial numbers.
------------------------------------------------------------------------

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report of cracks found in the lower 
area of the forward cabin doorpost bulkhead. The FAA is issuing this 
AD to detect and address cracking of the wing strut attach point. 
The unsafe condition, if not addressed, could result in failure of 
the wing in operation, which could result in loss of control of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Initial Inspections

    (1) For airplanes without a lower forward doorpost bulkhead and 
wing strut fitting reinforcement service kit (service kit) installed 
in accordance with Cessna Single Engine Service Bulletin SEB95-19, 
dated December 29, 1995 (SEB95-19), or Cessna Single Engine Service 
Bulletin SEB93-5, Revision 2, dated May 29, 2019 (SEB93-5R2): At the 
applicable compliance time specified in paragraph (g)(1)(i) or (ii) 
of this AD, do a visual inspection of the lower forward doorpost at 
the strut attach fitting for cracks in accordance with steps 1.A., 
1.B., 1.C., and 1.B. (the step following step 1.C.) of the 
Accomplishment Instructions in SEB95-19; or steps 1.A. and 1.B. of 
the Accomplishment Instructions in SEB93-5R2; as applicable to your 
model airplane.
    (i) For airplanes that have accumulated less than 4,000 hours 
time-in-service (TIS) as of the effective date of this AD: Initially 
inspect prior to the accumulation of 4,000 hours TIS or within the 
next 200 hours TIS after the effective date of this AD, whichever 
occurs later.
    (ii) For airplanes that have accumulated 4,000 or more hours TIS 
as of the effective date of this AD: Initially inspect within 200 
hours TIS after the effective date of this AD or within 12 calendar 
months after the effective date of this AD, whichever occurs first.
    (2) For airplanes with a service kit installed in accordance 
with SEB95-19 or SEB93-5R2: At the later of the times specified in 
paragraphs (g)(2)(i) and (ii) of this AD, do a visual inspection of 
the lower forward doorpost at the strut attach fitting for cracks in 
accordance with steps 1.A., 1.B., 1.C., and 1.B. (the step following 
step 1.C.) of the Accomplishment Instructions in SEB95-19; or steps 
1.A. and 1.B. of the Accomplishment Instructions in SEB93-5R2; as 
applicable to your model airplane. Do not remove the installed 
service kit; instead, inspect for cracking that extends beyond the 
modified parts.
    (i) At the applicable time specified in paragraph (g)(1)(i) or 
(ii) of this AD.
    (ii) Within 1,000 hours TIS or 36 calendar months, whichever 
occurs first, since installing the service kit.

(h) Repetitive Inspections

    (1) If no cracks are found during the initial inspection 
required by paragraph (g)(1) or (2) of this AD, thereafter repeat 
the inspection at intervals not to exceed 36 calendar months or 
1,000 hours TIS, whichever occurs first from the last inspection, as 
long as no cracks are found.
    (2) If cracks are found during any inspection required by 
paragraph (g)(1) or (h)(1) of this AD, do the inspection specified 
in paragraph (g)(2) of this AD within 36 calendar months or 1,000 
hours TIS, whichever occurs first after installing the service kit 
required by paragraph (i)(1) of this AD. Thereafter, repeat the 
inspection at intervals not to exceed 36 calendar months or 1,000 
hours TIS, whichever occurs first from the last inspection, as long 
as no additional cracks are found.

(i) Corrective Actions

    (1) If cracks are found during any inspection required by 
paragraph (g)(1) or paragraph (h)(1) of this AD, before further

[[Page 32315]]

flight, install a service kit in accordance with step 1.D. of the 
Accomplishment Instructions in SEB95-19; or step 1.C. of the 
Accomplishment Instructions in SEB93-5R2; as applicable to your 
model airplane.
    (2) If cracks are found during any inspection required by 
paragraph (g)(2) or (h)(2) of this AD, before further flight, repair 
the area using a method approved by the Manager, Wichita ACO Branch, 
FAA. For a repair method to be approved by the Manager, Wichita ACO 
Branch as required by this paragraph, the Manager's approval letter 
must specifically refer to this AD. You may use the contact 
information in paragraph (n)(1) of this AD to obtain FAA approval of 
your repair method.

(j) Reporting Requirement

    Within 30 days after the effective date of this AD, or within 30 
days after completing the initial inspection required by paragraph 
(g) of this AD, whichever occurs later, report the findings of the 
initial inspection (regardless if cracks were found or not) to the 
FAA at [email protected]. Thereafter, within 30 days after 
completing each repetitive inspection required by paragraph (h) of 
this AD, if any crack was found, report the crack findings to the 
FAA at [email protected]. Include in your reports the following 
information:
    (1) Name and address of the owner;
    (2) Date of the inspection;
    (3) Name, address, telephone number, and email address of the 
person submitting the report;
    (4) Airplane serial number and total hours TIS on the airplane 
at the time of the inspection; and
    (5) If any crack was found during the inspection, provide 
detailed crack information as specified below:
    (i) A sketch or picture detailing the crack location;
    (ii) Measured length of the crack(s) found;
    (iii) Installation of a Cessna service kit or any other kit or 
repair before the inspection; and
    (iv) Installation of any supplemental type certificates (STCs), 
alterations, repairs, or field approvals affecting the area of 
concern or affecting gross weight.

(k) Credit for Previous Actions

    (1) You may take credit for the initial inspection required by 
paragraph (g) of this AD if you performed the inspection before the 
effective date of this AD using Cessna Single Engine Service 
Bulletin SEB93-5, dated March 26, 1993; or Cessna Single Engine 
Service Bulletin SEB93-5, Revision 1, dated September 8, 1995.
    (2) You may take credit for the installation required by 
paragraph (i)(1) of this AD as follows.
    (i) For Model 207, T207, 207A, and T207A airplanes with a 
service kit installed using SK206-42, SK206-42A, SK206-42B, or 
SK206-42C: You may take credit for the installation if done before 
the effective date of this AD using Cessna Single Engine Service 
Bulletin SEB93-5, dated March 26, 1993, or Cessna Single Engine 
Service Bulletin SEB93-5, Revision 1, dated September 8, 1995; if 
the reinforcement of the lower forward doorpost bulkhead and wing 
strut fitting specified in Cessna Single Engine Service Kit SK207-
19A, dated May 29, 2019, is also accomplished within 200 hours TIS 
after the effective date of this AD.
    (ii) For all other models: You may take credit for the 
installation if done before the effective date of this AD using 
Cessna Single Engine Service Bulletin SEB 93-5, dated March 26, 
1993; or Cessna Single Engine Service Bulletin SEB 93-5, Revision 1, 
dated September 8, 1995.

(l) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 1 hour per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita ACO Branch, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or local Flight Standards District 
Office, as appropriate. If sending information directly to the 
manager of the certification office, send it to the attention of the 
person identified in paragraph (n)(1) of this AD.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(n) Related Information

    (1) For more information about this AD, contact Bobbie Kroetch, 
Aerospace Engineer, Wichita ACO Branch, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: (316) 946-4155; fax: (316) 946-
4107; email: [email protected] or [email protected].
    (2) For service information identified in this AD, contact 
Textron Aviation Inc., Textron Aviation Customer Service, One Cessna 
Blvd., Wichita, Kansas 67215; telephone: (316) 517-5800; email: 
[email protected]; internet: https://support.cessna.com. You 
may review this referenced service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 901 
Locust, Kansas City, Missouri 64106. For information on the 
availability of this material at the FAA, call (816) 329-4148.

    Issued on May 21, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-11340 Filed 5-28-20; 8:45 am]
BILLING CODE 4910-13-P