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PROPOSED 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 al-
    ready 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 Revi-
     sion 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 Tempo-
      rary 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 Tempo-
     rary 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 Revi-
     sion 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 Tempo-
      rary 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 Temp-
       orary 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 in-
    spector, 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 Eng-
    ineer, Wichita ACO Branch, 1801 Airport Road, Rm. 100, Wichita, Kansas
    67209;  telephone: (316) 946-4141;  fax: (316) 946-4107;  email: tara.
    shawn@faa.gov or Wichita-COS@faa.gov.

(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.

DATES: The FAA must receive comments on this proposed AD by June 29, 2020.
PREAMBLE 

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).

-----------------------------------------------------------------------

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 Wichita-COS@faa.gov.

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 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

Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Inspection 2 work-hours x $85 per hour = $170
Not applicable
$170
$1,119,620

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

Action
Labor cost
Parts cost
Cost per product
Replace left-hand (LH) stabilizer hinge bracket. 4 work-hours x $85 per workhour = $340 $551 $891
Replace right-hand (RH) stabilizer hinge bracket.
4 work-hours x $85 per workhour = $340
530 870
Replace LH tailcone reinforcement angle. 12 work-hours x $85 per workhour = $1,020 2,291 3,311
Replace RH tailcone reinforcement angle. 12 work-hours x $85 per workhour = $1,020 3,006 4,026
Replace LH corner reinforcement. 6 work-hours x $85 per workhour = $510 169 679
Replace RH corner reinforcement.
6 work-hours x $85 per workhour = $510
390 900
Replace LH stabilizer hinge reinforcement channel.
6 work-hours x $85 per workhour = $510
99 609
Replace RH stabilizer hinge reinforcement channel. 6 work-hours x $85 per workhour = $510 99 609
Replace LH stabilizer hinge assembly. 1 work-hours x $85 per workhour = $85 570 655
Replace RH stabilizer hinge assembly. 1 work-hours x $85 per workhour = $85 694 779
Replace LH stabilizer aft spar reinforcement. * 825 825
Replace RH stabilizer aft spar reinforcement. * 466 466
Replace stabilizer aft spar (* includes work-hour cost for replacing stabilizer aft spar reinforcement parts). 28* work-hours x $85 per workhour = $2,380 563 2,943
Remove and replace horizontal and vertical stabilizers and rig flight controls. 8 work-hours x $85 per workhour = $680 (*) 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 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


1. The authority citation for part 39 continues to read as follows:

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

Sec. 39.13 [Amended]

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