Airworthiness Directives; Textron Aviation Inc. Airplanes, 28890-28893 [2020-10316]
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28890
Federal Register / Vol. 85, No. 94 / Thursday, May 14, 2020 / Proposed Rules
39107, Revision No. 1, dated December 13,
2017.
TABLE 1 TO PARAGRAPH (g)—COMPLIANCE TIME REQUIREMENTS
Compliance time
[A or B, whichever occurs later after the effective date of this AD]
A .............................
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B .............................
Before the FCU accumulates 1,500 flight hours, or before the FCU accumulates six years since new or last overhaul,
whichever occurs first.
Within six months.
(h) Credit for Previous Actions
You may take credit for the replacement of
the FCU that is required by paragraph (g) of
this AD if you replaced the FCU with an FCU
that incorporates a stainless steel air adapter
before the effective date of this AD using
P&WC SB No. PT6B–72–39107, Original
Issue, dated December 15, 2016.
DEPARTMENT OF TRANSPORTATION
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO 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 ECO Branch, send it to
the attention of the person identified in
paragraph (j)(1) of this AD. You may email
your request to: ANE-AD-AMOC@faa.gov.
(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.
RIN 2120–AA64
(j) Related Information
(1) For more information about this AD,
contact Mehdi Lamnyi, Aerospace Engineer,
ECO Branch, FAA, 1200 District Avenue,
Burlington, MA, 01803; phone: 781–238–
7743; fax: 781–238–7199; email:
Mehdi.Lamnyi@faa.gov.
(2) Refer to Transport Canada Civil
Aviation (Transport Canada) AD CF–2019–
05, dated February 19, 2019, for more
information. You may examine the Transport
Canada AD in the AD docket on the internet
at https://www.regulations.gov by searching
for and locating it in Docket No. FAA–2020–
0471.
(3) For service information identified in
this AD, contact Pratt & Whitney Canada
Corp., 1000 Marie-Victorin, Longueuil,
Quebec, Canada, J4G 1A1; phone: 800–268–
8000; fax: 450–647–2888; website: https://
www.pwc.ca/en/. You may view this
referenced service information at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on
the availability of this material at the FAA,
call 781–238–7759.
Issued on May 5, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–09944 Filed 5–13–20; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0472; Product
Identifier 2018–CE–060–AD]
Airworthiness Directives; Textron
Aviation Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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,
SUMMARY:
PO 00000
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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.
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 WichitaCOS@faa.gov.
FOR FURTHER INFORMATION CONTACT:
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
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28891
Federal Register / Vol. 85, No. 94 / Thursday, May 14, 2020 / Proposed Rules
summarizing each substantive verbal
contact received about this NPRM.
separation with consequent loss of
control of the airplane.
Discussion
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.
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
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 timein-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
product
Action
Labor cost
Parts cost
Inspection ..........................
2 work-hours × $85 per hour = $170 ........................
Not applicable ..................
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
Cost on U.S.
operators
$170
$1,119,620
number of aircraft that might need these
actions:
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ON-CONDITION COSTS
Cost per
product
Action
Labor cost
Parts cost
Replace left-hand (LH) stabilizer hinge bracket ...........
Replace right-hand (RH) stabilizer hinge bracket ........
Replace LH tailcone reinforcement angle ....................
Replace RH tailcone reinforcement angle ...................
Replace LH corner reinforcement ................................
Replace RH corner reinforcement ................................
Replace LH stabilizer hinge reinforcement channel ....
Replace RH stabilizer hinge reinforcement channel ....
Replace LH stabilizer hinge assembly .........................
Replace RH stabilizer hinge assembly ........................
Replace LH stabilizer aft spar reinforcement ...............
Replace RH stabilizer aft spar reinforcement ..............
Replace stabilizer aft spar (* includes work-hour cost
for replacing stabilizer aft spar reinforcement parts).
Remove and replace horizontal and vertical stabilizers
and rig flight controls.
4 work-hours × $85 per workhour = $340 ....................
4 work-hours × $85 per workhour = $340 ....................
12 work-hours × $85 per workhour = $1,020 ...............
12 work-hours × $85 per workhour = $1,020 ...............
6 work-hours × $85 per workhour = $510 ....................
6 work-hours × $85 per workhour = $510 ....................
6 work-hours × $85 per workhour = $510 ....................
6 work-hours × $85 per workhour = $510 ....................
1 work-hours × $85 per workhour = $85 .....................
1 work-hours × $85 per workhour = $85 ......................
* ....................................................................................
* ....................................................................................
28* work-hours × $85 per workhour = $2,380 .............
$551
530
2,291
3,006
169
390
99
99
570
694
825
466
563
$891
870
3,311
4,026
679
900
609
609
655
779
825
466
2,943
8 work-hours × $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
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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
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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
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Federal Register / Vol. 85, No. 94 / Thursday, May 14, 2020 / Proposed Rules
§ 39.13
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.
jbell on DSKJLSW7X2PROD with PROPOSALS
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.
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[Amended]
2. The FAA amends § 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
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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,
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Federal Register / Vol. 85, No. 94 / Thursday, May 14, 2020 / Proposed Rules
Room 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.
[FR Doc. 2020–10316 Filed 5–13–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0473; Product
Identifier 2018–CE–058–AD]
RIN 2120–AA64
Airworthiness Directives; Polskie
Zaklady Lotnicze Sp. z o.o. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Polskie Zaklady Lotnicze Sp. z
o.o. Model PZL M28 05 airplanes. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country to identify
and correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as defective
thermo-shrinkable tubes installed on the
electrical harnesses located in the fuel
tanks. 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 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.
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SUMMARY:
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• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Polskie
Zaklady Lotnicze Sp. z o.o., Wojska
Polskiego 3, 39–300 Mielec, Poland, +48
17 743 1901, email: pzl.lm@lmco.com,
internet: www.pzlmielec.pl. You may
review this referenced 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–
0473; 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 proposed
AD, 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:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Standards Branch,
901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposed AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2020–0473;
Product Identifier 2018–CE–058–AD’’ at
the beginning of your comments. The
FAA specifically invites comments on
the overall regulatory, economic,
environmental, and energy aspects of
this proposed AD. The FAA will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
The FAA will post all comments we
receive, without change, to https://
regulations.gov, including any personal
information you provide. The FAA will
also post a report summarizing each
substantive verbal contact received
about this proposed AD.
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28893
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No. 2018–
0242, dated October 8, 2018 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
During accomplishment of maintenance on
an M28 05 military version airplane, torn
pieces of thermo-shrinkable tubes were found
in the header section of the main fuel tank.
These tubes are installed on electrical
harnesses located in the fuel tanks and serve
as marking and protection devices against
mechanical damage during manufacturing
and servicing. Pieces of these tubes may
travel with the fuel flow and may block the
jet pump or reduce its performance,
particularly in the centre-wing fuel tank, in
which the jet pump is the only way of further
transfer of fuel to the engine. Subsequent
investigation determined that degradation of
the tube material was caused by a
manufacturing deficiency, leading to
insufficient material resistance against
mechanical damage when a tube is located in
a fuel.
This condition, if not detected and
corrected, could lead to reduced fuel supply
to the engines, inability to use all the fuel in
fuel tanks and reduced available engine
power, resulting in reduced aeroplane
performance.
To address this potentially unsafe
condition, PZL identified the batch of
aeroplanes that are potentially equipped with
thermo-shrinkable tubes having this
manufacturing defect, and issued the [service
bulletin] SB providing inspection and
replacement instructions.
For the reasons described above, this
[EASA] AD requires a one-time inspection of
the electrical harnesses located in the fuel
tanks and, depending on findings,
replacement of the affected harness.
Polskie Zaklady Lotnicze Sp. z o.o.
informed us the potential for damage to
the thermo-shrinkable tubes does not
progress with time. Therefore, we
determined repetitive inspections are
not required. You may examine the
MCAI on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0473.
Related Service Information Under 1
CFR Part 51
Polskie Zaklady Lotnicze Sp. z o.o.
has issued Service Bulletin No. E/
12.141/2018, dated May 15, 2018. The
service information contains procedures
for inspecting the thermo-shrinkable
tubes on the electrical harnesses in the
center and outer wing fuel tanks for
damage and replacing any electrical
harness with damaged thermoshrinkable tubes. This service
information is reasonably available
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]]>Agencies
[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]
BILLING CODE 4910-13-P
