[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]


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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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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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 http://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 http://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 http://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 http://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).
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[[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: http://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


