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 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):
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