[Federal Register Volume 86, Number 43 (Monday, March 8, 2021)]
[Rules and Regulations]
[Pages 13157-13159]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-03478]
[[Page 13157]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0811; Product Identifier 2019-CE-055-AD; Amendment
39-21431; AD 2021-04-10]
RIN 2120-AA64
Airworthiness Directives; Textron Aviation, Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Textron Aviation Inc. (Textron) (type certificate previously
held by Cessna Aircraft Company) Models 208 and 208B airplanes. This AD
was prompted by reports of loose elevator torque tube attach fasteners.
This AD requires repetitively inspecting the inboard and outboard
elevator torque tube attachments for loose or incorrectly installed
fasteners, replacing all fasteners if loose or incorrectly installed
fasteners are found, and reporting the inspection results to the FAA.
This AD also includes optional actions to terminate the repetitive
inspections. The FAA is issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective April 12, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 12,
2021.
ADDRESSES: For service information identified in this final rule,
contact Textron Aviation Inc., One Cessna Boulevard, Wichita, KS 67215;
phone: 316-517-5800; email: [email protected]; website:
https://support.cessna.com. You may view this service information at
the FAA, Airworthiness Products Section, Operational Safety Branch, 901
Locust St., Kansas City, MO 64106. For information on the availability
of this material at the FAA, call 816-329-4148. It is also available at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2020-0811.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0811; 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 final rule, any
comments received, and other information. The address for Docket
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, Aviation Safety
Engineer, Wichita ACO Branch, FAA, 1801 Airport Road, Wichita, KS
67209; phone: 316-946-4155; fax: 316-946-4107; email:
[email protected] or [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Textron (type
certificate previously held by Cessna Aircraft Company) Models 208 and
208B airplanes. The NPRM published in the Federal Register on September
22, 2020 (85 FR 59457). The NPRM was prompted by reports of loose
elevator torque tube attach fasteners on low flight time Textron Model
208B airplanes. Textron identified a quality escape affecting certain
serial-numbered Model 208 and 208B airplanes. Fastener holes in the
inboard and outboard elevator torque tube connections may have been
oversized and fasteners at the inboard and outboard torque tube
connections may have been installed incorrectly.
In the NPRM, the FAA proposed to require repetitively inspecting
the inboard and outboard elevator torque tube attachments for loose or
incorrectly installed fasteners, replacing all fasteners if loose or
incorrectly installed fasteners are found, and reporting the inspection
results to the FAA. The NPRM also proposed optional actions to
terminate the repetitive inspections. This condition, if not addressed,
could result in failure of the elevator torque tube fasteners, leading
to loss of elevator control and loss of controlled flight. The FAA is
issuing this AD to address the unsafe condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the costs.
Conclusion
The FAA reviewed the relevant data and determined that air safety
requires adopting this AD as proposed. Accordingly, the FAA is issuing
this AD to address the unsafe condition on these products. This AD is
adopted as proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Task 27-30-00-290, Left and Right Elevator Torque
Tube Attach Points (Borescope) Special Detailed Inspection, dated
October 1, 2018, of the Cessna Model 208 Maintenance Manual (Task 27-
30-00-290). This service information contains procedures for performing
a detailed borescope inspection of the left and right elevator torque
tube attach points. 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 ADDRESSES.
Other Related Service Information
The FAA also reviewed Textron Aviation Mandatory Caravan Service
Bulletin CAB-27-06, dated October 14, 2019 (CAB-27-06). This service
information contains instructions for visually inspecting the left and
right elevator torque tube attach points for the presence of loose
rivets and replacing loose or incorrectly installed rivets.
Differences Between This AD and the Service Information
Task 27-30-00-290 only specifies replacing loose fasteners. This AD
requires replacement of all 48 fasteners if any single inboard or
outboard elevator torque tube attach fastener is found loose or
incorrectly installed. The FAA determined based on field evidence that
identification of one loose fastener often indicates other fasteners
may be affected.
CAB-27-06, which is not incorporated by reference in this AD,
specifies performing an initial inspection within 800 flight hours or
12 months from date of receipt, whichever occurs first. This AD
requires an initial inspection before the airplane accumulates 800
hours time-in-service (TIS) or within 200 hours TIS after the AD
effectivity date, whichever occurs later.
CAB-27-06 also specifies, without sufficient data, that an
inspection is not required for airplanes that have reached 4,000 hours.
The FAA determined an inspection of high-time airplanes is necessary to
verify whether these airplanes are affected. This AD requires a one-
time visual inspection for airplanes that have already accumulated
4,000 hours TIS.
Costs of Compliance
The FAA estimates that this AD affects 232 airplanes of U.S.
registry.
[[Page 13158]]
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection..................... 1 work-hour x $85 Not applicable........ $85 per $19,720 per
per hour = $85. inspection cycle. inspection
cycle.
Reporting Requirement.......... 1 work-hour x $85 Not applicable........ $85 per report... $19,720 per
per hour = $85. report.
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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
inspection. The FAA has no way of determining the number of airplanes
that might need these replacements:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Fastener Replacement: All 48 Fasteners........ 16 work-hours x $85 per hour = $10 $1,370
$1,360.
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The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Send comments regarding this burden estimate
or any other aspect of this collection of information, including
suggestions for reducing this burden to: Information Collection
Clearance Officer, Federal Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177-1524.
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
This AD will not have federalism implications under Executive Order
13132. This AD will 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 that this AD:
(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 Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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:
2021-04-10 Textron Aviation, Inc. (Type Certificate Previously Held
by Cessna Aircraft Company): Amendment 39-21431; Docket No. FAA-
2020-0811; Product Identifier 2019-CE-055-AD.
(a) Effective Date
This airworthiness directive (AD) is effective April 12, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Textron Aviation Inc. (Textron) (type
certificate previously held by Cessna Aircraft Company) Model 208
airplanes, serial numbers 20800564 through 20800594 and 20800603
through 20800605; and Model 208B airplanes, serial numbers 208B5141
through 208B5285, 208B5287 through 208B5305, 208B5307 through
208B5312, 208B5314, 208B5316 through
[[Page 13159]]
208B5344, 208B5346 through 208B5350, 208B5353, 208B5354, 208B5356
through 208B5359, 208B5362 through 208B5366, 208B5401, 208B5403,
208B5404, and 208B5408; certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC) Code: 5520, Elevator
Structure.
(e) Unsafe Condition
This AD was prompted by reports of loose elevator torque tube
attach fasteners. The FAA is issuing this AD to detect and correct
loosening and eventual failure of the elevator torque tube attach
fasteners. The unsafe condition, if not addressed, could result in
loss of elevator control, resulting in loss of control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection and Fastener Replacement
(1) At the following compliance times, inspect each inboard and
outboard elevator torque tube attach fastener for looseness and
fretting by following sections 2.C. and 2.D. of Task 27-30-00-290,
Left and Right Elevator Torque Tube Attach Points (Borescope)
Special Detailed Inspection, dated October 1, 2018, of the Cessna
Model 208 Maintenance Manual. You must also inspect for incorrectly
installed fasteners.
(i) For airplanes that have accumulated less than 800 hours
time-in-service (TIS) as of the effective date of this AD, complete
the initial inspection before the airplane accumulates 800 hours TIS
or within 200 hours TIS after the effective date of the AD,
whichever occurs later. Thereafter, repeat the visual inspection at
intervals not to exceed 200 hours TIS until the airplane has
accumulated 4,000 hours TIS or until all 48 elevator torque tube
attach fasteners are replaced, whichever occurs first.
(ii) For airplanes that have accumulated 800 or more hours TIS
but less than 4,000 hours TIS as of the effective date of this AD,
complete the initial inspection within 200 hours TIS after the
effective date of the AD. Thereafter, repeat the visual inspection
at intervals not to exceed 200 hours TIS until the airplane has
accumulated 4,000 hours TIS or until all 48 elevator torque tube
attach fasteners are replaced, whichever occurs first.
(iii) For airplanes that have accumulated 4,000 or more hours
TIS as of the effective date of this AD, complete a one-time visual
inspection within 200 hours TIS after the effective date of the AD.
No repetitive inspections are required after completion of the one-
time visual inspection.
(2) If there are any loose, fretting, or incorrectly installed
fasteners, remove the elevator and replace all 48 elevator torque
tube attach fasteners (24 per side, with 12 each on the inboard and
outboard elevator torque tube attach point) before further flight.
Maintain proper alignment by marking each part prior to removal and
by replacing one fastener at a time. Replacing all 48 fasteners is
terminating action for the repetitive inspections required by
paragraphs (g)(1)(i) and (ii) of this AD.
(3) If all 48 fasteners were replaced before the effective date
of this AD by following the instructions in paragraph (g)(2) of this
AD, then the initial and recurring inspections detailed in paragraph
(g)(1) of this AD are not required provided you report the
information required by paragraph (h) of this AD.
(h) Reporting Requirement
Within 30 days after doing the initial inspection (regardless if
loose, fretting, or incorrectly installed fasteners were found) or
within 30 days after the effective date of this AD, whichever occurs
later, and then within 30 days after each inspection where loose,
fretting, or incorrectly installed fasteners were found, report the
following information to the FAA at [email protected]:
(1) Name and address of owner.
(2) Date of the inspection.
(3) Name, address, phone number, and email address of person
submitting the report.
(4) Airplane serial number, registration number, and total hours
TIS on the airplane at the time of the inspection.
(5) If an earlier inspection identified loose, fretting, or
incorrectly installed fasteners, identify the hours TIS on the
airplane and which fasteners were replaced, if known, or if all
fasteners were replaced.
(6) If loose, fretting, or incorrectly installed fasteners were
found, detailed information including a sketch or picture showing
the location of the loose, fretting, or incorrectly installed
fasteners and identification of any installed supplemental type
certificates (STCs), alterations, repairs, or field approvals
affecting the area of concern.
(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 the Related Information section 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
For more information about this AD, contact Bobbie Kroetch,
Aviation Safety Engineer, Wichita ACO Branch, FAA, 1801 Airport
Road, Wichita, KS 67209; phone: 316-946-4155; fax: 316-946-4107;
email: [email protected] or [email protected].
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Task 27-30-00-290, Left and Right Elevator Torque Tube
Attach Points (Borescope) Special Detailed Inspection, dated October
1, 2018, of the Cessna Model 208 Maintenance Manual.
(ii) [Reserved]
(3) For Textron Aviation, Inc. service information identified in
this AD, contact Textron Aviation Inc., One Cessna Boulevard,
Wichita, KS 67215; phone: 316-517-5800; email:
[email protected]; website: https://support.cessna.com.
(4) You may view this service information at FAA, Airworthiness
Products Section, Operational Safety Branch, 901 Locust St., Kansas
City, MO 64106. For information on the availability of this material
at the FAA, call 816-329-4148.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on February 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-03478 Filed 3-5-21; 8:45 am]
BILLING CODE 4910-13-P