Airworthiness Directives; Textron Aviation Inc. Airplanes

[Federal Register Volume 85, Number 195 (Wednesday, October 7, 2020)]
[Rules and Regulations]
[Pages 63195-63200]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-22039]


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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; Amendment 
39-21222; AD 2020-18-01]
RIN 2120-AA64


Airworthiness Directives; Textron Aviation Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) 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, FR182, R182, TR182, 
206, 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, T207A, 210-5 (205), 210-5A (205A), 210B, 210C, 210D, 210E, 210F, 
and T210F airplanes. This AD was prompted by cracks found in the lower 
area of the forward cabin doorpost bulkhead. This AD requires 
repetitively inspecting the lower area of the forward cabin doorposts 
at the strut attach fitting for cracks and repairing any cracks. The 
FAA is issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective November 12, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 12, 
2020.

ADDRESSES: For service information identified in this final rule, 
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, Policy and 
Innovation Division, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call (816) 
329-4148. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0049.

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 final rule, any comments received, and other information. The 
address for Docket Operations (phone: 800-647-5527) is U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

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:

Discussion

    The FAA issued a supplemental notice of proposed rulemaking (SNPRM) 
to amend 14 CFR part 39 by adding an AD that would apply to certain 
serial-numbered Textron Aviation Inc. (Textron) (type certificate 
previously held by Cessna Aircraft Company) Model 172N, 172P, 172Q, 
172RG, F172N, F172P, FR172K, R172K, 182E,

[[Page 63196]]

182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, T182, 
F182P, F182Q, FR182, R182, TR182, 206, 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, T207A, 210-5 (205), 
210-5A (205A), 210B, 210C, 210D, 210E, 210F, and T210F airplanes. The 
SNPRM published in the Federal Register on May 29, 2020 (85 FR 32308).
    The FAA preceded the SNPRM with a notice of proposed rulemaking 
(NPRM) that published in the Federal Register on February 1, 2018 (83 
FR 4605). The NPRM was prompted by reports of cracks in the lower area 
of the forward cabin doorpost bulkhead on more than four dozen Textron 
100 and 200 airplanes. 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. The SNPRM proposed to modify 
the estimated costs of the proposed AD, the repetitive inspection 
intervals, and the credit allowed for previous actions; clarify the 
inspection instructions for airplanes with the service kit installed; 
correct the contact information for obtaining the service information; 
and add a reporting requirement to collect the inspection results. The 
SNPRM also changed 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.
    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.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The following presents the comments 
received on the SNPRM and the FAA's response to each comment.

Support for the SNPRM

    Patrick Imperatrice expressed support for the proposed AD.

Request To Extend or Remove Calendar Compliance Time

    Kermit Bunde expressed support for the 1,000-hour time-in-service 
(TIS) inspection interval but requested the FAA remove the 36-month 
calendar time inspection interval. The commenter stated that the 36-
month interval is too often and that cracking is a function of usage 
and not only elapsed time. The commenter provided examples of Cessna 
maintenance actions that have no calendar time limit.
    The FAA disagrees. Both the manufacturer's guidance, which is 
published in the supplemental inspection documents (SIDs) for certain 
airplanes, and fleet history support the 36-month interval for 
inspecting this location. Loading conditions outside of flight, such as 
ground loads, handling loads, and tie down loads, may also cause 
cracking at this location. Therefore, the FAA determined the inspection 
interval of 36 calendar months or 1,000 hours TIS, whichever occurs 
first, is necessary to address the unsafe condition. The FAA did not 
change this AD based on this comment.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety and the public interest 
require adopting this final rule as proposed.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Cessna Single Engine Service Bulletin SEB93-5, 
Revision 2, dated May 29, 2019 (SEB93-5R2) and Cessna Single Engine 
Service Bulletin SEB95-19, dated December 29, 1995 (SEB95-19). 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 the applicable Cessna service kit.
    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. In addition, the FAA 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.

Costs of Compliance

    The FAA estimates that this AD affects 14,653 airplanes of U.S. 
registry.
    The FAA estimates the following costs to comply with this 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   Not applicable.......         $127.50   $1,868,257.50
 forward cabin doorposts for         per hour = $127.50.
 cracks.
Reporting requirement.............  1 work-hour x $85 per  Not applicable.......              85       1,245,505
                                     hour = $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repairs 
that would be required based on the results of the 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.

[[Page 63197]]



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

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 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 control 
number for the collection of information required by this AD 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 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 
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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2020-18-01 Textron Aviation Inc.: Amendment 39-21222; Docket No. FAA 
2018-0049; Product Identifier 2017-CE-031-AD.

(a) Effective Date

    This AD is effective November 12, 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:
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(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 
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:

[[Page 63200]]

    (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 SEB93-5, dated March 26, 1993; 
or Cessna Single Engine Service Bulletin SEB93-5, 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) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (4) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Cessna Single Engine Service Bulletin SEB93-5, Revision 2, 
dated May 29, 2019.
    (ii) Cessna Single Engine Service Bulletin SEB95-19, dated 
December 29, 1995.
    (3) 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.
    (4) You may view this 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on August 24, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-22039 Filed 10-6-20; 8:45 am]
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