(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 certifi-
    cate 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 al-
    ready 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 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 righthand 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  righthand  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,  re-
    place 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
    Multiengine  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 re-
    quired to respond to,  nor shall  a person be subject to a penalty for
    failure to comply  with a collection of information subject to the re-
    quirements 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 review-
    ing instructions,  completing and reviewing the collection of informa-
    tion.  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
    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 identi-
    fied in paragraph (q) of this AD.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector,  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

(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 In-
    spection 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,  con-
    tact 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: 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 Ser-
vice.

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.