[Federal Register Volume 85, Number 94 (Thursday, May 14, 2020)]
[Proposed Rules]
[Pages 28890-28893]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-10316]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0472; Product Identifier 2018-CE-060-AD]
RIN 2120-AA64


Airworthiness Directives; Textron Aviation Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Textron Aviation Inc. (Textron) Models 180, 180A, 180B, 180C, 
180D, 180E, 180F, 180G, 180H, 180J, 180K, 182, 182A, 182B, 182C, 182D, 
185, 185A, 185B, 185C, 185D, 185E, A185E, and A185F airplanes. This 
proposed AD was prompted by a report of cracks found in the tailcone 
and horizontal stabilizer attachment structure. This proposed AD would 
require inspecting the tailcone and horizontal stabilizer for corrosion 
and cracks and repairing or replacing damaged parts as necessary. The 
FAA is proposing this AD to address the unsafe condition on these 
products.

DATES: The FAA must receive comments on this proposed AD by June 29, 
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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Textron 
Aviation Customer Service, P.O. Box 7706, Wichita, Kansas 67277, (316) 
517-5800; customercare@txtav.com; https://txtav.com. 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.

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-2020-
0472; 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 NPRM, the regulatory evaluation, 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: Tara Shawn, Aerospace Engineer, 
Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209; 
telephone: (316) 946-4141; fax: (316) 946-4107; email: 
tara.shawn@faa.gov or 297e404a41405d48046a667a694f4848074e465f.

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-2020-0472; 
Product Identifier 2018-CE-060-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. The FAA will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report

[[Page 28891]]

summarizing each substantive verbal contact received about this NPRM.

Discussion

    The FAA received a report of cracks in the tailcone and horizontal 
stabilizer attachment structure on a Textron (type certificate 
previously held by Cessna Aircraft Company) Model 185 airplane. It was 
observed during maintenance that the horizontal stabilizer tail section 
moved up and down and had excessive play. After a detailed inspection, 
the tailcone reinforcement braces were found cracked on both sides of 
the airplane. Upon further investigation, the FAA discovered similar 
conditions on 29 additional Textron 180 and 185 series airplanes. The 
FAA determined that the combination of the attachment structure design 
and high loads during landing contribute to the development of cracks 
in the tailcone and horizontal stabilizer attachment structure. This 
condition, if unaddressed, could result in failure of the horizontal 
stabilizer to tailcone attachment and lead to tail separation with 
consequent loss of control of the airplane.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Textron Aviation Single Engine Mandatory Service 
Letter SEL-55-01, dated December 7, 2017. The service information 
contains procedures for inspecting the stabilizer hinge brackets, 
tailcone reinforcement angles, corner reinforcements, stabilizer hinge 
reinforcement channel, stabilizer hinge assemblies, stabilizer aft spar 
reinforcement, and the lower half of the stabilizer aft spar from 
station (STA) 16 on the left side of the stabilizer aft spar to STA 16 
on the right side for cracks and corrosion. 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.

FAA's Determination

    The FAA is proposing this AD because it 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.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously.

Differences Between This Proposed AD and the Service Information

    The service information applies to airplanes with more than 3,000 
total hours time-in-service or 10 years in service, while this proposed 
AD would apply regardless of the airplane's time-in-service. This 
proposed AD would require inspecting for and replacing loose or sheared 
rivets, which is not specified in the service information.

Costs of Compliance

    The FAA estimates that this proposed AD would affect 6,586 
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
----------------------------------------------------------------------------------------------------------------
Inspection.......................  2 work-hours x $85 per    Not applicable.....            $170      $1,119,620
                                    hour = $170.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
proposed inspection. The FAA has no way of determining the number of 
aircraft that might need these actions:

                                               On-Condition Costs
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                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace left-hand (LH) stabilizer hinge      4 work-hours x $85 per workhour =              $551            $891
 bracket.                                     $340.
Replace right-hand (RH) stabilizer hinge     4 work-hours x $85 per workhour =               530             870
 bracket.                                     $340.
Replace LH tailcone reinforcement angle....  12 work-hours x $85 per workhour =            2,291           3,311
                                              $1,020.
Replace RH tailcone reinforcement angle....  12 work-hours x $85 per workhour =            3,006           4,026
                                              $1,020.
Replace LH corner reinforcement............  6 work-hours x $85 per workhour =               169             679
                                              $510.
Replace RH corner reinforcement............  6 work-hours x $85 per workhour =               390             900
                                              $510.
Replace LH stabilizer hinge reinforcement    6 work-hours x $85 per workhour =                99             609
 channel.                                     $510.
Replace RH stabilizer hinge reinforcement    6 work-hours x $85 per workhour =                99             609
 channel.                                     $510.
Replace LH stabilizer hinge assembly.......  1 work-hours x $85 per workhour =               570             655
                                              $85.
Replace RH stabilizer hinge assembly.......  1 work-hours x $85 per workhour =               694             779
                                              $85.
Replace LH stabilizer aft spar               *..................................             825             825
 reinforcement.
Replace RH stabilizer aft spar               *..................................             466             466
 reinforcement.
Replace stabilizer aft spar (* includes      28* work-hours x $85 per workhour =             563           2,943
 work-hour cost for replacing stabilizer      $2,380.
 aft spar reinforcement parts).
Remove and replace horizontal and vertical   8 work-hours x $85 per workhour =               (*)             680
 stabilizers and rig flight controls.         $680.
----------------------------------------------------------------------------------------------------------------
* Not applicable.

    Since corrosion may affect any or all of the parts subject to the 
inspection in this proposed AD differently and the severity of the 
corrosion on each part would affect the time necessary to correct the 
condition, the FAA has no way to determine an overall cost per product 
for removing the corrosion. Similarly, loose or sheared rivets may also 
affect any or all of the parts subject to the inspection in this 
proposed AD differently, and the time necessary to correct the 
condition on each product would be different. Therefore, the FAA has no 
way to determine an overall cost

[[Page 28892]]

per product for replacing loose or sheared rivets.

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

    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-2020-0472; Product Identifier 
2018-CE-060-AD.

(a) Comments Due Date

    The FAA must receive comments by June 29, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Textron Aviation Inc. (type certificate 
previously held by Cessna Aircraft Company) Models 180, 180A, 180B, 
180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K, 182, 182A, 182B, 
182C, 182D, 185, 185A, 185B, 185C, 185D, 185E, A185E, and A185F 
airplanes, all serial numbers, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage; 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by a report of cracks found in the tailcone 
and horizontal stabilizer attachment structure. The FAA is issuing 
this AD to detect and correct corrosion and cracks in the tailcone 
and horizontal stabilizer attachment structure. The unsafe 
condition, if not addressed, could result in failure of the 
horizontal stabilizer to tailcone attachment, which could lead to 
tail separation with consequent loss of control of the airplane.

(f) Compliance

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

(g) Inspect, Repair, and Replace

    Within the next 100 hours time-in-service (TIS) after the 
effective date of this AD or within the next 12 months after the 
effective date of this AD, whichever occurs later, and thereafter 
every 500 hours TIS or 5 years, whichever occurs first, visually 
inspect each stabilizer hinge bracket, tailcone reinforcement angle, 
corner reinforcement, stabilizer hinge reinforcement channel, 
stabilizer hinge assembly, stabilizer aft spar reinforcement, and 
the lower half of the stabilizer aft spar from station (STA) 16 on 
the left side to STA 16 on the right side for corrosion and cracks; 
remove any corrosion; and replace any part with a crack by following 
the Accomplishment Instructions, paragraphs 9 through 11 and 13, of 
Textron Aviation Single Engine Mandatory Service Letter SEL-55-01, 
dated December 7, 2017. Also inspect for loose rivets and sheared 
rivets. If there is a loose or sheared rivet, before further flight, 
replace the rivet.

(h) Credit for Previous Actions

    Actions accomplished before the effective date of this AD within 
the previous 5 years or 500 hours TIS, whichever was the most 
recent, in accordance with the procedures specified in the documents 
listed in paragraphs (h)(i) through (viii) of this AD as applicable 
to your airplane are considered acceptable for compliance with the 
corresponding actions in paragraph (g) of this AD. The time between 
any inspection for which credit is allowed by this paragraph and the 
next inspection accomplished in accordance with paragraph (g) of 
this AD must not exceed 500 hours TIS or 5 years, whichever occurs 
first.
    (i) Cessna Aircraft Company Model 100 Series (1953-1962) Service 
Manual, Supplemental Inspection Number: 53-10-01, D138-1-13 
Temporary Revision Number 8, dated May 18, 2015.
    (ii) Cessna Aircraft Company Model 100 Series (1963-1968) 
Service Manual, Supplemental Inspection Number: 53-10-01, D637-1-13 
Temporary Revision Number 10, dated May 18, 2015;
    (iii) Cessna Aircraft Company Model 180/185 Series (1969-1980) 
Service Manual, Supplemental Inspection Number: 53-10-01, D2000-9-13 
Temporary Revision Number 9, dated May 18, 2015.
    (iv) Cessna Aircraft Company Model 180/185 Series (1981-1985) 
Service Manual, Supplemental Inspection Number: 53-10-01, D2067-1TR9 
Temporary Revision Number 9, dated May 1, 2016.
    (v) Cessna Aircraft Company Model 100 Series (1953-1962) Service 
Manual, Supplemental Inspection Number: 55-10-01, D138-1-13 
Temporary Revision Number 7, dated December 1, 2011.
    (vi) Cessna Aircraft Company Model 100 Series (1963-1968) 
Service Manual, Supplemental Inspection Number: 55-10-01, D637-1-13 
Temporary Revision Number 9, dated December 1, 2011.
    (vii) Cessna Aircraft Company Model 180/185 Series (1969-1980) 
Service Manual, Supplemental Inspection Number: 55-10-01, D2000-9-13 
Temporary Revision Number 7, dated December 1, 2011.
    (viii) Cessna Aircraft Company Model 180/185 Series (1981-1985) 
Service Manual, Supplemental Inspection Number: 55-10-01, D2067-1-13 
Temporary Revision Number 7, dated December 1, 2011.

(i) 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 (j) 
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.

(j) Related Information

    (1) For more information about this AD, contact Tara Shawn, 
Aerospace Engineer, Wichita ACO Branch, 1801 Airport Road,

[[Page 28893]]

Room 100, Wichita, Kansas 67209; telephone: (316) 946-4141; fax: 
(316) 946-4107; email: tara.shawn@faa.gov or 3e69575d56574a5f137d716d7e585f5f10595148.
    (2) For service information identified in this AD, contact 
Textron Aviation Customer Service, P.O. Box 7706, Wichita, Kansas 
67277, (316) 517-5800; customercare@txtav.com; https://txtav.com. 
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.

    Issued on May 8, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-10316 Filed 5-13-20; 8:45 am]
BILLING CODE 4910-13-P


