[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; [email protected]; 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:
[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-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
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Inspection....................... 2 work-hours x $85 per Not applicable..... $170 $1,119,620
hour = $170.
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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
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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.
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* 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: [email protected] or [email protected].
(2) For service information identified in this AD, contact
Textron Aviation Customer Service, P.O. Box 7706, Wichita, Kansas
67277, (316) 517-5800; [email protected]; 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]
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