Airworthiness Directives; Textron Aviation Inc. Airplanes, 6114-6118 [2018-02551]
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Federal Register / Vol. 83, No. 30 / Tuesday, February 13, 2018 / Rules and Regulations
(d) Subject
Air Transport Association of America
(ATA) Code 28: Fuel.
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
issued by the aviation authority of another
country to identify and address an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as nonconforming fuel tank caps. We are issuing
this AD to detect and address nonconforming fuel tank caps, which could
result in fuel loss and lead to fuel starvation
and inflight engine shutdown.
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(f) Actions and Compliance
Unless already done, do the following
actions.
(1) Within 15 days after March 5, 2018 (the
effective date of this AD), insert the CAA,
Civil Aviation Authority of New Zealand,
Supplement to AIR 2825 and AIR 3237,
Section 2, Limitations, Revision 1, dated
December 8, 2017, into the pilot’s operating
handbook/airplane flight manual (POH/
AFM).
(2) Within 45 days after March 5, 2018 (the
effective date of this AD), inspect the fuel
tank caps, part number (P/N) 457–1015–12,
following the Accomplishment Instructions
in Pacific Aerospace Mandatory Service
Bulletin, PACSB/XL/089, Issue 01, dated
December 8, 2017.
(3) If a damaged or non-conforming fuel
tank cap is found during the inspection
required in paragraph (f)(2) of this AD, before
further flight, replace any damaged or nonconforming fuel tank cap with a modified
fuel tank cap, P/N 11–21087–1.
(4) After replacement of damaged or nonconforming fuel tank caps with P/N 11–
21087–1, as required in paragraph (f)(3) of
this AD, remove the CAA Supplement to AIR
2825 and AIR 3237, Section 2, Limitations,
Revision 1, dated December 8, 2017, from the
POH/AFM.
(5) Replacement of damaged or nonconforming fuel tank caps with P/N 11–
21087–1, as required in paragraph (f)(3) of
this AD, terminates the repetitive inspections
required in the CAA Supplement to AIR 2825
and AIR 3237, Section 2, Limitations,
Revision 1, dated December 8, 2017.
(6) Long-range aircraft delivery ferry flights
and oceanic flights are prohibited until the
inspection required in paragraph (f)(2) of this
AD and any necessary replacements required
by paragraph (f)(3) of this AD have been
completed.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Small Airplane
Standards Branch, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Mike Kiesov,
Aerospace Engineer, FAA, Small Airplane
Standards Branch, 901 Locust, Room 301,
Kansas City, Missouri 64106; telephone:
(816) 329–4144; fax: (816) 329–4090; email:
mike.kiesov@faa.gov. Before using any
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approved AMOC on any airplane to which
the AMOC applies, notify your appropriate
principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, Small Airplane Standards
Branch, FAA; or the CAA, which is the
aviation authority for New Zealand.
(h) Related Information
Refer to MCAI from the CAA, AD DCA/
750XL/20, dated December 8, 2017; Pacific
Aerospace Mandatory Service Bulletin
PACSB/XL/089, Issue 01, dated December 8,
2017; and CAA Supplement to AIR 2825 and
AIR 3237 (POH/AFM), Section 2,
Limitations, Revision 1, dated December 8,
2017, for related information. You may
examine the MCAI on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2018–0066.
(i) 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) Pacific Aerospace Mandatory Service
Bulletin PACSB/XL/089, Issue 01, dated
December 8, 2017.
(ii) CAA, Civil Aviation Authority of New
Zealand, Supplement to AIR 2825 and AIR
3237, Section 2, Limitations, Revision 1,
dated December 8, 2017.
(3) For service information identified in
this AD, contact Pacific Aerospace Limited,
Airport Road, Hamilton, Private Bag 3027,
Hamilton 3240, New Zealand; phone: +64
7843 6144; fax: +64 843 6134; email: pacific@
aerospace.co.nz; internet:
www.aerospace.co.nz.
(4) You may view this referenced service
information at the FAA, Policy and
Innovation Division, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call
(816) 329–4148. It is also available on the
internet at https://www.regulations.gov by
searching for locating Docket No. FAA–2018–
0066.
(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, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Kansas City, Missouri, on January
25, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division,
Aircraft Certification Service.
[FR Doc. 2018–02611 Filed 2–12–18; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0068; Product
Identifier 2017–CE–049–AD; Amendment
39–19176; AD 2018–03–03]
RIN 2120–AA64
Airworthiness Directives; Textron
Aviation Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Textron Aviation Inc. Models 401,
401A, 401B, 402, 402A, 402B, 402C,
411, 411A, 414, 414A 421, 421A, 421B,
421C, and 425 airplanes. This AD
requires repetitively inspecting the left
and the right forward lower carry
through spar cap for cracks and
replacing the carry through spar if
cracks are found. This AD was
prompted by a report of a fully cracked
lower forward carry through spar cap
found on an affected airplane. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective February 28,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 28, 2018.
We must receive comments on this
AD by March 30, 2018.
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: 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 final rule, contact Textron Aviation
Inc., Textron Aviation Customer
Service, One Cessna Blvd., Wichita,
Kansas 67215; telephone: (316) 517–
5800; email: customercare@txtav.com;
SUMMARY:
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internet: www.txtav.com. You may view
this service information at the FAA,
Policy and Innovation Division, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148. It is also available on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2018–0068.
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–2018–
0068; 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,
the regulatory evaluation, any
comments received, and other
information. The street address for
Docket Operations (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Bobbie Kroetch, Aerospace Engineer,
Wichita ACO Branch, 1801 Airport
Road, Room 100, Wichita, Kansas
67209; telephone: (316) 946–4155; fax:
(316) 946–4107; email: bobbie.kroetch@
faa.gov or Wichita-COS@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We received a report of a fully
cracked lower forward carry through
spar cap found on a Textron Aviation
Inc. (type certificate previously held by
Cessna Aircraft Company) Model 402C
airplane. Investigation revealed that the
crack is a result of metal fatigue. At this
time, the cracking has only been found
on the Model 402C airplanes. However,
the carry through spar cap and
surrounding structure on the other
model airplanes included in this AD are
similar and the loads on the other model
airplanes are similar to (or higher than)
the Model 402C airplanes.
This condition, if not addressed,
could cause failure of the carry through
spar cap during flight and result in loss
of control. We are issuing this AD to
address the unsafe condition on these
products.
6115
Related Service Information Under 1
CFR Part 51
approved, and available, we may
consider additional rulemaking.
We reviewed Textron Aviation Multiengine Mandatory Service Letter MEL–
57–01 and Textron Aviation Conquest
Mandatory Service Letter CQL–57–01,
both dated December 18, 2017. As
applicable, these service letters describe
procedures for repetitively inspecting
the forward lower carry through spar
cap for cracks. 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 Justification and Determination
of the Effective Date
Other Related Service Information
We reviewed Textron Aviation
Conquest Service Bulletin CQB–57–01,
Textron Aviation Multi-engine Service
Bulletin MEB–57–01, and Textron
Multi-engine Service Bulletin MEB–57–
02, all dated December 20, 2017. As
applicable, these service bulletins
provide the manufacturer’s optional
procedures for installing access panels
for easier access to the forward lower
carry through spars. This AD does not
require installing the access panels.
FAA’s Determination
We are issuing this AD because we
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.
AD Requirements
This AD requires repetitively
inspecting the left and the right forward
lower carry through spar cap for cracks
and replacing the carry through spar if
cracks are found. This AD also requires
sending the inspection results to the
FAA.
Interim Action
We consider this AD interim action.
Textron Aviation Inc. is evaluating the
initial and repetitive inspection
intervals, as well as designing a
replacement lower carry through spar
cap from an improved material. After
the evaluations are complete and the
design modification is developed,
An unsafe condition exists that
requires the immediate adoption of this
AD without providing an opportunity
for public comments prior to adoption.
The FAA has found that the risk to the
flying public justifies waiving notice
and comment prior to adoption of this
rule because cracks in the left and/or the
right forward lower carry through spar
cap could cause the carry through spar
cap to fail during flight and result in
loss of control. Therefore, we find good
cause that notice and opportunity for
prior public comment are impracticable.
In addition, for the reason stated above,
we find that good cause exists for
making this amendment effective in less
than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment.
However, we invite you to send any
written data, views, or arguments about
this final rule. Send your comments to
an address listed under the ADDRESSES
section. Include the docket number
FAA–2018–0068 and Product Identifier
2017–CE–049–AD at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this final rule. We will
consider all comments received by the
closing date and may amend this final
rule because of those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this final rule.
Costs of Compliance
We estimate that this AD affects 2,147
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Cost on U.S.
operators
Inspect the left and the right forward
lower carry through spar cap for
cracks (without inspection access
panels).
12 work-hours × $85 per hour =
$1,020 per inspection cycle.
Not applicable .......
$1,020 per inspection cycle.
$2,189,940 per inspection cycle.
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Federal Register / Vol. 83, No. 30 / Tuesday, February 13, 2018 / Rules and Regulations
We estimate the following costs to do
any necessary replacement that would
be required based on the results of the
inspection. We have no way of
determining the number of aircraft that
might need this replacements:
ON-CONDITION COSTS
Action
Labor cost
Replace carry through spar ..........................................
800 work-hours × $85 per hour = $68,000 ..................
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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 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 current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW, Washington,
DC 20591. ATTN: Information
Collection Clearance Officer, AES–200.
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.
We are 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.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
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Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to small airplanes, gliders,
balloons, airships, domestic business jet
transport airplanes, and associated
appliances to the Director of the Policy
and Innovation Division.
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) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) 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.
Adoption of 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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2018–03–03 Textron Aviation Inc.:
Amendment 39–19176; Docket No.
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Parts cost
Cost per
product
$5,000
$73,000
FAA–2018–0068; Product Identifier
2017–CE–049–AD.
(a) Effective Date
This AD is effective February 28, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Textron
Aviation Inc. (type certificate previously held
by Cessna Aircraft Company) model
airplanes, that are certificated in any
category:
TABLE 1 TO PARAGRAPH (C) OF THIS
AD—AFFECTED MODELS AND SERIAL NUMBERS
Model
Serial numbers
401 .....
401A ...
401B ...
402 .....
402A ...
402B ...
402C ...
411 .....
411A ...
414 .....
414A ...
421 .....
421A ...
421B ...
421C ...
425 .....
401–0001 through 401–0322
401A0001 through 401A0132
401B0001 through 401B0221
402–0001 through 402–0322
402A0001 through 402A0129
402B0001 through 402B1384
689, 402C0001 through 402C1020
411–0001 through 411–0250
411–0251 through 411–0300
414–0001 through 414–0965
414A0001 through 414A1212
421–0001 through 421–0200
421A0001 through 421A0158
421B0001 through 421B0970
421C0001 through 421C1807
425–0001 through 425–0236
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report that a
fully cracked lower forward carry through
spar cap was found on a Textron Model 402C
airplane. We are issuing this AD to prevent
failure of the carry through spar cap during
flight. The unsafe condition, if not addressed,
could result in loss of control.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Initial Inspection for All Affected
Airplanes With 24,975 Hours Time-InService (TIS) or More on the Carry Through
Spars
Within the next 25 hours TIS after
February 28, 2018 (the effective date of this
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AD), do a detailed visual inspection of the
left and right forward lower carry through
spar cap for cracks. Using a 10X magnifier
visually inspect the bottom surface of the
carry through spar cap in the areas around
the fasteners located just inboard of the lefthand and right-hand forward lower wing
fittings. If a crack is not positively identified
during the detailed visual inspection but is
suspected or the area is questionable, before
further flight, do a surface eddy current
inspection of the suspected area. Do these
inspections using the Accomplishment
Instructions in Textron Aviation Multiengine Mandatory Service Letter MEL–57–01
and Textron Aviation Conquest Mandatory
Service Letter CQL–57–01, both dated
December 18, 2017, as applicable.
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(h) Initial Inspection for All Affected
Airplanes With Less Than 24,975 Hours TIS
on the Carry Through Spars
Using the compliance times listed in
paragraphs (h)(1) through (3) of this AD, do
a detailed visual inspection of the left and
right forward lower carry through spar cap
for cracks. Using a 10X magnifier visually
inspect the bottom surface of the carry
through spar cap in the areas around the
fasteners located just inboard of the left-hand
and right-hand forward lower wing fittings.
If a crack is not positively identified during
the detailed visual inspection but is
suspected or the area is questionable, before
further flight, do a surface eddy current
inspection of the suspected area. Do these
inspections using the Accomplishment
Instructions in Textron Aviation Multiengine Mandatory Service Letter MEL–57–01
and Textron Aviation Conquest Mandatory
Service Letter CQL–57–01, both dated
December 18, 2017, as applicable.
(1) For Models 401, 401A, 401B, 402, 402A,
402B, 402C, 411, 411A, 414, 414A, 421, and
421A airplanes: Before the accumulation of
15,000 TIS on the carry through spars or
within the next 50 hours TIS after February
28, 2018 (the effective date of this AD),
whichever occurs later.
(2) For Models 421B and 421C airplanes:
Before the accumulation of 12,000 hours TIS
on the carry through spars or within the next
50 hours TIS after February 28, 2018 (the
effective date of this AD), whichever occurs
later.
(3) For Model 425 airplanes: Before the
accumulation of 11,000 TIS on the carry
through spars or within the next 50 hours TIS
after February 28, 2018 (the effective date of
this AD), whichever occurs later.
(i) Repetitive Inspections for All Affected
Airplanes
If no cracks are found during the detailed
visual inspections or the surface eddy current
inspections required in paragraphs (g) and (h)
of this AD, repetitively thereafter inspect at
intervals not to exceed 50 hours TIS. Inspect
as specified in paragraphs (g) and (h) of this
AD using the service information specified in
each paragraph as applicable.
(j) Replacement of Carry Through Spars for
All Affected Airplanes
If cracks are found during any inspection
required in paragraphs (g) through (i) and
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paragraph (k) of this AD, before further flight,
replace the carry through spar.
(k) Initial and Repetitive Inspections of
Newly Replaced Carry Through Spars for
All Affected Airplanes
At the compliance times in paragraphs
(k)(1) through (3) of this AD, do a detailed
visual inspection of the left and right forward
lower carry through spar cap for cracks.
Using a 10X magnifier visually inspect the
bottom surface of the carry through spar cap
in the areas around the fasteners located just
inboard of the left-hand and right-hand
forward lower wing fittings. If a crack is not
positively identified during the detailed
visual inspection but is suspected or the area
is questionable, before further flight, do a
surface eddy current inspection of the
suspected area. Do these inspections using
the Accomplishment Instructions in Textron
Aviation Multi-engine Mandatory Service
Letter MEL–57–01 and Textron Aviation
Conquest Mandatory Service Letter CQL–57–
01, both dated December 18, 2017, as
applicable.
(1) For Models 401, 401A, 401B, 402, 402A,
402B, 402C, 411, 411A, 414, 414A, 421, and
421A airplanes: Before the accumulation of
15,000 hours TIS on the newly installed carry
through spar. If no cracks are found,
repetitively thereafter inspect at intervals not
to exceed 50 hours TIS.
(2) For Models 421B and 421C airplanes:
Before the accumulation of 12,000 hours TIS
on the newly installed carry through spar. If
no cracks are found, repetitively thereafter
inspect at intervals not to exceed 50 hours
TIS.
(3) For Model 425 airplanes: Before the
accumulation of 11,000 hours TIS on the
newly installed carry through spar. If no
cracks are found, repetitively thereafter
inspect at intervals not to exceed 50 hours
TIS.
(l) Reporting Requirement for All Affected
Airplanes
Within 30 days after each inspection
required by paragraphs (g) through (i) and
paragraph (k) of this AD, report the results of
the inspection to the FAA representative
identified in paragraph (q) of this AD using
the undated Attachment (titled Spar Cap
Inspection Results Form and Spar Cap
Inspection Results Form Continued) to
Textron Aviation Multi-engine Mandatory
Service Letter MEL–57–01 and Textron
Aviation Conquest Mandatory Service Letter
CQL–57–01, both dated December 18, 2017,
as applicable. Please identify AD 2018–03–03
in the subject line if submitted through
email.
(m) Installation of Optional Access Panels
All Affected Airplanes
Textron Aviation Conquest Service
Bulletin CQB–57–01, Textron Aviation
Multi-engine Service Bulletin MEB–57–01,
and Textron Multi-engine Service Bulletin
MEB–57–02, all dated December 20, 2017,
provide the manufacturer’s optional
procedures for installing access panels for
easier access to the forward carry through
spars. This AD does not require installing the
access panels, but does not restrict the
owner/operator from doing so.
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(n) Credit for Actions Done Following
Previous Service Information for Affected
Airplanes
This AD allows credit for the initial
inspection of the forward lower carry through
spar cap required in paragraphs (g) and (h)
of this AD if done before February 28, 2018
(the effective date of this AD) using the
following documents:
(1) Models 401, 401A, 401B, 402, 402A,
402B airplanes: Cessna Aircraft Company
Model 401/402 Supplemental Inspection
Document, Supplemental Inspection Number
57–10–10, dated June 3, 2002.
(2) Model 402C airplanes: Cessna Aircraft
Company Model 402C Maintenance Manual,
Supplemental Inspection Number 57–10–14,
dated June 3, 2002.
(3) Models 411 and 411A airplanes: Cessna
Aircraft Company Model 411, Supplemental
Inspection Document, Supplemental
Inspection Number 57–10–10, dated January
6, 2003.
(4) Model 414 airplanes: Cessna Aircraft
Company Model 414 Supplemental
Inspection Document, Supplemental
Inspection Number 57–10–10, dated August
1, 2002.
(5) Model 414A airplanes: Cessna Aircraft
Company Model 414A Supplemental
Inspection Document, Supplemental
Inspection Number 57–10–14, dated August
1, 2002.
(6) Models 421, 421A, and 421B airplanes:
Cessna Aircraft Company Model 421
Supplemental Inspection Document,
Supplemental Inspection Number 57–10–10,
dated March 3, 2003.
(7) Model 421C airplanes: Cessna Aircraft
Company Model 421C Supplemental
Inspection Document, Supplemental
Inspection Number 57–10–14, dated January
6, 2003.
(o) Paperwork Reduction Act Burden
Statement
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 current 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 be approximately 15 minutes
per response, including the time for
reviewing instructions, completing and
reviewing the collection of information. All
responses to this collection of information
are mandatory. Comments concerning the
accuracy of this burden and suggestions for
reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW,
Washington, DC 20591, Attn: Information
Collection Clearance Officer, AES–200.
(p) 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
E:\FR\FM\13FER1.SGM
13FER1
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Federal Register / Vol. 83, No. 30 / Tuesday, February 13, 2018 / Rules and Regulations
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 (q) 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.
(q) Related Information
For more information about this AD,
contact Bobbie Kroetch, Aerospace Engineer,
Wichita ACO Branch, 1801 Airport Road,
Room 100, Wichita, Kansas 67209; telephone:
(316) 946–4155; fax: (316) 946–4107; email:
bobbie.kroetch@faa.gov or Wichita-COS@
faa.gov.
(r) Material Incorporated by Reference
sradovich on DSK3GMQ082PROD with RULES
(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 this AD specifies otherwise.
(i) Textron Aviation Multi-engine
Mandatory Service Letter MEL–57–01, dated
December 18, 2017 (includes the undated
Attachment titled Spar Cap Inspection
Results Form and Spar Cap Inspection
Results Form Continued).
(ii) Textron Aviation Conquest Mandatory
Service Letter CQL–57–01, dated December
18, 2017 (includes the undated Attachment
titled Spar Cap Inspection Results Form and
Spar Cap Inspection Results Form
Continued).
(3) For Textron Aviation service
information identified in this AD, contact
Textron Aviation Inc., Textron Aviation
Customer Service, One Cessna Blvd.,
Wichita, Kansas 67215; telephone: (316) 517–
5800; email: customercare@txtav.com;
internet: www.txtav.com.
(4) You may view this service information
at FAA, Policy and Innovation Division, 901
Locust, Kansas City, Missouri 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, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Kansas City, Missouri, on
February 2, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division,
Aircraft Certification Service.
[FR Doc. 2018–02551 Filed 2–12–18; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
15:52 Feb 12, 2018
Jkt 244001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0952; Product
Identifier 2017–CE–028–AD; Amendment
39–19189; AD 2018–03–16]
RIN 2120–AA64
Airworthiness Directives; Stemme AG
Gliders
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2017–10–
11 for Stemme AG Model Stemme S10–
VT gliders (type certificate previously
held by Stemme GmbH & Co. KG). This
AD results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and address
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as certain propeller front
transmission gear wheels having
insufficient material strength because of
improper heat treatment during
manufacturing. We are issuing this AD
to require actions to address the unsafe
condition on these products and to add
Stemme AG Model Stemme S 12 gliders
to the Applicability section.
DATES: This AD is effective March 20,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 20, 2018.
ADDRESSES: You may examine the AD
docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0952; or in person at Docket Operations,
U.S. Department of Transportation, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
For service information identified in
this AD, contact STEMME AG,
Flugplatzstrasse F2, Nr. 6–7, D–15344
Strausberg, Germany; telephone: +49 (0)
3341 3612–0, fax: +49 (0) 3341 3612–30;
internet: https://www.stemme.com. You
may view this referenced service
information at the FAA, Policy and
Innovation Division, 901 Locust, Kansas
City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148. It is also
available on the internet at https://
www.regulations.gov by searching for
Docket No. FAA–2017–0952.
SUMMARY:
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
Jim
Rutherford, Aerospace Engineer, FAA,
Small Airplane Standards Branch, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4165; fax: (816) 329–4090; email:
jim.rutherford@faa.gov.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Stemme AG Model Stemme
S10–VT gliders (type certificate
previously held by Stemme GmbH & Co.
KG) and all Stemme AG Model Stemme
S 12 gliders equipped with a certain
front gearbox, part number 11AG. That
NPRM was published in the Federal
Register on October 10, 2017 (82 FR
46938), and proposed to supersede AD
2017–10–11, Amendment 39–18885 (82
FR 24239, May 26, 2017) (‘‘AD 2017–
10–11’’).
Since we issued AD 2017–10–11, we
have type certificated Stemme AG
Model Stemme S 12 gliders in the
United States and have determined
those model gliders should also be
included in the applicability of AD
2017–10–11. In addition, Stemme AG
has issued new service information with
procedures for addressing the unsafe
condition.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the proposal and the FAA’s
response to the comment.
Request for Manufacturer To Be
Responsible for All Associated Cost
Taylor Ray stated that the
manufacturer should be responsible for
replacing the front gearbox on the
affected gliders at no cost to the owners/
operators. We infer that the commenter
is referring to the cost for both parts and
labor.
Taylor Ray stated that since the
unsafe condition resulted from the
manufacturing process, the
manufacturer should be responsible for
fixing the unsafe condition.
We neither agree nor disagree since
the FAA does not get involved in who
pays for the cost of mitigating an unsafe
condition. The primary concern the
FAA has when issuing an AD is
addressing unsafe conditions on various
aircraft flying in the United States.
While we provide information related to
the estimated labor and parts cost
associated with each AD, we do not
control warranty coverage for owner/
operators of the affected aircraft nor can
E:\FR\FM\13FER1.SGM
13FER1
]]>Agencies
[Federal Register Volume 83, Number 30 (Tuesday, February 13, 2018)]
[Rules and Regulations]
[Pages 6114-6118]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02551]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0068; Product Identifier 2017-CE-049-AD; Amendment
39-19176; AD 2018-03-03]
RIN 2120-AA64
Airworthiness Directives; Textron Aviation Inc. Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Textron Aviation Inc. Models 401, 401A, 401B, 402, 402A, 402B, 402C,
411, 411A, 414, 414A 421, 421A, 421B, 421C, and 425 airplanes. This AD
requires repetitively inspecting the left and the right forward lower
carry through spar cap for cracks and replacing the carry through spar
if cracks are found. This AD was prompted by a report of a fully
cracked lower forward carry through spar cap found on an affected
airplane. We are issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective February 28, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 28,
2018.
We must receive comments on this AD by March 30, 2018.
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: 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 final rule, contact
Textron Aviation Inc., Textron Aviation Customer Service, One Cessna
Blvd., Wichita, Kansas 67215; telephone: (316) 517-5800; email:
[email protected];
[[Page 6115]]
internet: www.txtav.com. You may view this service information at the
FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the FAA,
call (816) 329-4148. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0068.
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-2018-
0068; 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, the regulatory evaluation, any comments received, and
other information. The street address for Docket Operations (phone:
800-647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, Aerospace Engineer,
Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209;
telephone: (316) 946-4155; fax: (316) 946-4107; email:
[email protected] or [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We received a report of a fully cracked lower forward carry through
spar cap found on a Textron Aviation Inc. (type certificate previously
held by Cessna Aircraft Company) Model 402C airplane. Investigation
revealed that the crack is a result of metal fatigue. At this time, the
cracking has only been found on the Model 402C airplanes. However, the
carry through spar cap and surrounding structure on the other model
airplanes included in this AD are similar and the loads on the other
model airplanes are similar to (or higher than) the Model 402C
airplanes.
This condition, if not addressed, could cause failure of the carry
through spar cap during flight and result in loss of control. We are
issuing this AD to address the unsafe condition on these products.
Related Service Information Under 1 CFR Part 51
We reviewed Textron Aviation Multi-engine Mandatory Service Letter
MEL-57-01 and Textron Aviation Conquest Mandatory Service Letter CQL-
57-01, both dated December 18, 2017. As applicable, these service
letters describe procedures for repetitively inspecting the forward
lower carry through spar cap for cracks. 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.
Other Related Service Information
We reviewed Textron Aviation Conquest Service Bulletin CQB-57-01,
Textron Aviation Multi-engine Service Bulletin MEB-57-01, and Textron
Multi-engine Service Bulletin MEB-57-02, all dated December 20, 2017.
As applicable, these service bulletins provide the manufacturer's
optional procedures for installing access panels for easier access to
the forward lower carry through spars. This AD does not require
installing the access panels.
FAA's Determination
We are issuing this AD because we 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.
AD Requirements
This AD requires repetitively inspecting the left and the right
forward lower carry through spar cap for cracks and replacing the carry
through spar if cracks are found. This AD also requires sending the
inspection results to the FAA.
Interim Action
We consider this AD interim action. Textron Aviation Inc. is
evaluating the initial and repetitive inspection intervals, as well as
designing a replacement lower carry through spar cap from an improved
material. After the evaluations are complete and the design
modification is developed, approved, and available, we may consider
additional rulemaking.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies waiving notice and comment prior to adoption of this rule
because cracks in the left and/or the right forward lower carry through
spar cap could cause the carry through spar cap to fail during flight
and result in loss of control. Therefore, we find good cause that
notice and opportunity for prior public comment are impracticable. In
addition, for the reason stated above, we find that good cause exists
for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this final rule. Send your comments to an address
listed under the ADDRESSES section. Include the docket number FAA-2018-
0068 and Product Identifier 2017-CE-049-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this final rule. We will
consider all comments received by the closing date and may amend this
final rule because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this final rule.
Costs of Compliance
We estimate that this AD affects 2,147 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspect the left and the 12 work-hours x $85 Not applicable.. $1,020 per $2,189,940 per
right forward lower carry per hour = $1,020 inspection inspection cycle.
through spar cap for cracks per inspection cycle. cycle.
(without inspection access
panels).
----------------------------------------------------------------------------------------------------------------
[[Page 6116]]
We estimate the following costs to do any necessary replacement
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need this
replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace carry through spar................. 800 work-hours x $85 per hour = $5,000 $73,000
$68,000.
----------------------------------------------------------------------------------------------------------------
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 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 current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW, Washington, DC 20591. ATTN: Information
Collection Clearance Officer, AES-200.
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.
We are 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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to small airplanes, gliders,
balloons, airships, domestic business jet transport airplanes, and
associated appliances to the Director of the Policy and Innovation
Division.
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) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
Adoption of 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 (AD):
2018-03-03 Textron Aviation Inc.: Amendment 39-19176; Docket No.
FAA-2018-0068; Product Identifier 2017-CE-049-AD.
(a) Effective Date
This AD is effective February 28, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the following Textron Aviation Inc. (type
certificate previously held by Cessna Aircraft Company) model
airplanes, that are certificated in any category:
Table 1 to Paragraph (c) of This AD--Affected Models and Serial Numbers
------------------------------------------------------------------------
Model Serial numbers
------------------------------------------------------------------------
401.................................... 401-0001 through 401-0322
401A................................... 401A0001 through 401A0132
401B................................... 401B0001 through 401B0221
402.................................... 402-0001 through 402-0322
402A................................... 402A0001 through 402A0129
402B................................... 402B0001 through 402B1384
402C................................... 689, 402C0001 through 402C1020
411.................................... 411-0001 through 411-0250
411A................................... 411-0251 through 411-0300
414.................................... 414-0001 through 414-0965
414A................................... 414A0001 through 414A1212
421.................................... 421-0001 through 421-0200
421A................................... 421A0001 through 421A0158
421B................................... 421B0001 through 421B0970
421C................................... 421C0001 through 421C1807
425.................................... 425-0001 through 425-0236
------------------------------------------------------------------------
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report that a fully cracked lower
forward carry through spar cap was found on a Textron Model 402C
airplane. We are issuing this AD to prevent failure of the carry
through spar cap during flight. The unsafe condition, if not
addressed, could result in loss of control.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Initial Inspection for All Affected Airplanes With 24,975 Hours
Time-In-Service (TIS) or More on the Carry Through Spars
Within the next 25 hours TIS after February 28, 2018 (the
effective date of this
[[Page 6117]]
AD), do a detailed visual inspection of the left and right forward
lower carry through spar cap for cracks. Using a 10X magnifier
visually inspect the bottom surface of the carry through spar cap in
the areas around the fasteners located just inboard of the left-hand
and right-hand forward lower wing fittings. If a crack is not
positively identified during the detailed visual inspection but is
suspected or the area is questionable, before further flight, do a
surface eddy current inspection of the suspected area. Do these
inspections using the Accomplishment Instructions in Textron
Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron
Aviation Conquest Mandatory Service Letter CQL-57-01, both dated
December 18, 2017, as applicable.
(h) Initial Inspection for All Affected Airplanes With Less Than 24,975
Hours TIS on the Carry Through Spars
Using the compliance times listed in paragraphs (h)(1) through
(3) of this AD, do a detailed visual inspection of the left and
right forward lower carry through spar cap for cracks. Using a 10X
magnifier visually inspect the bottom surface of the carry through
spar cap in the areas around the fasteners located just inboard of
the left-hand and right-hand forward lower wing fittings. If a crack
is not positively identified during the detailed visual inspection
but is suspected or the area is questionable, before further flight,
do a surface eddy current inspection of the suspected area. Do these
inspections using the Accomplishment Instructions in Textron
Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron
Aviation Conquest Mandatory Service Letter CQL-57-01, both dated
December 18, 2017, as applicable.
(1) For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411,
411A, 414, 414A, 421, and 421A airplanes: Before the accumulation of
15,000 TIS on the carry through spars or within the next 50 hours
TIS after February 28, 2018 (the effective date of this AD),
whichever occurs later.
(2) For Models 421B and 421C airplanes: Before the accumulation
of 12,000 hours TIS on the carry through spars or within the next 50
hours TIS after February 28, 2018 (the effective date of this AD),
whichever occurs later.
(3) For Model 425 airplanes: Before the accumulation of 11,000
TIS on the carry through spars or within the next 50 hours TIS after
February 28, 2018 (the effective date of this AD), whichever occurs
later.
(i) Repetitive Inspections for All Affected Airplanes
If no cracks are found during the detailed visual inspections or
the surface eddy current inspections required in paragraphs (g) and
(h) of this AD, repetitively thereafter inspect at intervals not to
exceed 50 hours TIS. Inspect as specified in paragraphs (g) and (h)
of this AD using the service information specified in each paragraph
as applicable.
(j) Replacement of Carry Through Spars for All Affected Airplanes
If cracks are found during any inspection required in paragraphs
(g) through (i) and paragraph (k) of this AD, before further flight,
replace the carry through spar.
(k) Initial and Repetitive Inspections of Newly Replaced Carry Through
Spars for All Affected Airplanes
At the compliance times in paragraphs (k)(1) through (3) of this
AD, do a detailed visual inspection of the left and right forward
lower carry through spar cap for cracks. Using a 10X magnifier
visually inspect the bottom surface of the carry through spar cap in
the areas around the fasteners located just inboard of the left-hand
and right-hand forward lower wing fittings. If a crack is not
positively identified during the detailed visual inspection but is
suspected or the area is questionable, before further flight, do a
surface eddy current inspection of the suspected area. Do these
inspections using the Accomplishment Instructions in Textron
Aviation Multi-engine Mandatory Service Letter MEL-57-01 and Textron
Aviation Conquest Mandatory Service Letter CQL-57-01, both dated
December 18, 2017, as applicable.
(1) For Models 401, 401A, 401B, 402, 402A, 402B, 402C, 411,
411A, 414, 414A, 421, and 421A airplanes: Before the accumulation of
15,000 hours TIS on the newly installed carry through spar. If no
cracks are found, repetitively thereafter inspect at intervals not
to exceed 50 hours TIS.
(2) For Models 421B and 421C airplanes: Before the accumulation
of 12,000 hours TIS on the newly installed carry through spar. If no
cracks are found, repetitively thereafter inspect at intervals not
to exceed 50 hours TIS.
(3) For Model 425 airplanes: Before the accumulation of 11,000
hours TIS on the newly installed carry through spar. If no cracks
are found, repetitively thereafter inspect at intervals not to
exceed 50 hours TIS.
(l) Reporting Requirement for All Affected Airplanes
Within 30 days after each inspection required by paragraphs (g)
through (i) and paragraph (k) of this AD, report the results of the
inspection to the FAA representative identified in paragraph (q) of
this AD using the undated Attachment (titled Spar Cap Inspection
Results Form and Spar Cap Inspection Results Form Continued) to
Textron Aviation Multi-engine Mandatory Service Letter MEL-57-01 and
Textron Aviation Conquest Mandatory Service Letter CQL-57-01, both
dated December 18, 2017, as applicable. Please identify AD 2018-03-
03 in the subject line if submitted through email.
(m) Installation of Optional Access Panels All Affected Airplanes
Textron Aviation Conquest Service Bulletin CQB-57-01, Textron
Aviation Multi-engine Service Bulletin MEB-57-01, and Textron Multi-
engine Service Bulletin MEB-57-02, all dated December 20, 2017,
provide the manufacturer's optional procedures for installing access
panels for easier access to the forward carry through spars. This AD
does not require installing the access panels, but does not restrict
the owner/operator from doing so.
(n) Credit for Actions Done Following Previous Service Information for
Affected Airplanes
This AD allows credit for the initial inspection of the forward
lower carry through spar cap required in paragraphs (g) and (h) of
this AD if done before February 28, 2018 (the effective date of this
AD) using the following documents:
(1) Models 401, 401A, 401B, 402, 402A, 402B airplanes: Cessna
Aircraft Company Model 401/402 Supplemental Inspection Document,
Supplemental Inspection Number 57-10-10, dated June 3, 2002.
(2) Model 402C airplanes: Cessna Aircraft Company Model 402C
Maintenance Manual, Supplemental Inspection Number 57-10-14, dated
June 3, 2002.
(3) Models 411 and 411A airplanes: Cessna Aircraft Company Model
411, Supplemental Inspection Document, Supplemental Inspection
Number 57-10-10, dated January 6, 2003.
(4) Model 414 airplanes: Cessna Aircraft Company Model 414
Supplemental Inspection Document, Supplemental Inspection Number 57-
10-10, dated August 1, 2002.
(5) Model 414A airplanes: Cessna Aircraft Company Model 414A
Supplemental Inspection Document, Supplemental Inspection Number 57-
10-14, dated August 1, 2002.
(6) Models 421, 421A, and 421B airplanes: Cessna Aircraft
Company Model 421 Supplemental Inspection Document, Supplemental
Inspection Number 57-10-10, dated March 3, 2003.
(7) Model 421C airplanes: Cessna Aircraft Company Model 421C
Supplemental Inspection Document, Supplemental Inspection Number 57-
10-14, dated January 6, 2003.
(o) Paperwork Reduction Act Burden Statement
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 current 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 be approximately 15 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(p) 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
[[Page 6118]]
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 (q) 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.
(q) Related Information
For more information about this AD, contact Bobbie Kroetch,
Aerospace Engineer, Wichita ACO Branch, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946-4155; fax: (316) 946-
4107; email: [email protected] or [email protected].
(r) 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 this AD specifies otherwise.
(i) Textron Aviation Multi-engine Mandatory Service Letter MEL-
57-01, dated December 18, 2017 (includes the undated Attachment
titled Spar Cap Inspection Results Form and Spar Cap Inspection
Results Form Continued).
(ii) Textron Aviation Conquest Mandatory Service Letter CQL-57-
01, dated December 18, 2017 (includes the undated Attachment titled
Spar Cap Inspection Results Form and Spar Cap Inspection Results
Form Continued).
(3) For Textron Aviation service information identified in this
AD, contact Textron Aviation Inc., Textron Aviation Customer
Service, One Cessna Blvd., Wichita, Kansas 67215; telephone: (316)
517-5800; email: [email protected]; internet: www.txtav.com.
(4) You may view this service information at FAA, Policy and
Innovation Division, 901 Locust, Kansas City, Missouri 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, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on February 2, 2018.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division, Aircraft Certification
Service.
[FR Doc. 2018-02551 Filed 2-12-18; 8:45 am]
BILLING CODE 4910-13-P
