preamble attached >>>
ADs updated daily at www.Tdata.com
2020-18-01 TEXTRON AVIATION INC.:
Amendment 39-21222; Docket No. FAA 2018-0049; Product Identifier 2017-CE-031-AD.

(a) EFFECTIVE DATE

    This AD is effective November 12, 2020.

(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, cer-
    tificated in any category:

    TABLE 1 TO PARAGRAPH (C) OF THIS AD–AFFECTED MODELS AND SERIAL NUMBERS
    ______________________________________________________________________
    MODEL              SERIAL NUMBERS
    ______________________________________________________________________
    172N               17272885 through 17274009 inclusive

    172P               All serial numbers

    172Q               17275869, 17275927 through 17275934 inclusive,
                       17275952, 17275959, 17275960, 17275962, 17275964,
                       17275965, 17275967, 17275968, 17275969, 17275971,
                       17275992, 17275999, 17276002, 17276005, 17276029,
                       17276032, 17276042, 17276045, 17276051, 17276052,
                       17276054, 17276101, 17276109, 17276140, 17276147,
                       17276188, and 17276211

    172RG              All serial numbers

    F172N              F17201910 through F17202039 inclusive

    F172P              All serial numbers

    FR172K             FR17200656 through FR17200675 inclusive

    R172K              R1723200 through R1723454 inclusive

    182E               All serial numbers

    182F               All serial numbers

    182G               All serial numbers

    182H               All serial numbers

    182J               All serial numbers

    182K               All serial numbers

    182L               All serial numbers

    182M               All serial numbers

    182N               All serial numbers

    182P               All serial numbers

    182Q               All serial numbers

    182R               All serial numbers

    T182               All serial numbers

    F182P              All serial numbers

    F182Q              All serial numbers

    FR182              All serial numbers

    R182               R18200002 through R18200583 inclusive

    R182 and           R18200001 and R18200584 through R18202039 inclusive
    TR182

    206                All serial numbers

    P206, P206A,       All serial numbers
    P206B, P206C,
    P206D, P206E,
    TP206A, TP206B,
    TP206C, TP206D,
    and TP206E

    U206, U206A,       All serial numbers
    U206B, U206C,
    U206D, U206E,
    U206F, U206G,
    TU206A, TU206B,
    TU206C, TU206D,
    TU206E, TU206F,
    and TU206G

    207, 207A,         All serial numbers
    T207, and
    T207A

    210-5 (205)        All serial numbers

    210-5A (205A)      All serial numbers

    210B               All serial numbers

    210C               All serial numbers

    210D               All serial numbers

    210E               All serial numbers

    210F               All serial numbers

    T210F              All serial numbers
    ______________________________________________________________________

(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 of cracks found in the lower area  of
    the forward  cabin doorpost  bulkhead. The  FAA is  issuing this AD to
    detect and address cracking of the wing strut attach point. The unsafe
    condition, if not  addressed, could result  in failure of  the wing in
    operation, which could result in loss of control of the airplane.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) INITIAL INSPECTIONS

(1) For airplanes without a lower forward doorpost bulkhead and wing strut
    fitting  reinforcement   service  kit   (service  kit)   installed  in
    accordance with Cessna Single Engine Service Bulletin SEB95-19,  dated
    December 29, 1995 (SEB95-19), or Cessna Single Engine Service Bulletin
    SEB93-5, Revision 2, dated May 29, 2019 (SEB93-5R2): At the applicable
    compliance time specified in paragraph  (g)(1)(i) or (ii) of this  AD,
    do a  visual inspection  of the  lower forward  doorpost at  the strut
    attach fitting for cracks in  accordance with steps 1.A., 1.B.,  1.C.,
    and  1.B.  (the  step  following  step  1.C.)  of  the  Accomplishment
    Instructions in SEB95-19; or steps 1.A. and 1.B. of the Accomplishment
    Instructions in SEB93-5R2; as applicable to your model airplane.

(i) For  airplanes  that  have  accumulated less than 4,000 hours time-in-
    service (TIS) as of the  effective date of this AD:  Initially inspect
    prior to the accumulation  of 4,000 hours TIS  or within the next  200
    hours TIS after the effective date of this AD, whichever occurs later.

(ii) For airplanes that have accumulated 4,000 or more hours TIS as of the
     effective date  of this  AD: Initially  inspect within  200 hours TIS
     after the  effective date  of this  AD or  within 12  calendar months
     after the effective date of this AD, whichever occurs first.

(2) For airplanes with a service kit installed in accordance with SEB95-19
    or  SEB93-5R2:  At the  later  of the  times  specified in  paragraphs
    (g)(2)(i) and (ii)  of this AD,  do a visual  inspection of the  lower
    forward doorpost at the strut attach fitting for cracks in  accordance
    with steps 1.A., 1.B., 1.C.,  and 1.B. (the step following  step 1.C.)
    of the Accomplishment Instructions in SEB95-19; or steps 1.A. and 1.B.
    of the Accomplishment Instructions in SEB93-5R2; as applicable to your
    model  airplane. Do  not remove  the installed  service kit;  instead,
    inspect for cracking that extends beyond the modified parts.

(i) At the applicable time specified  in  paragraph (g)(1)(i)  or  (ii) of
    this AD.

(ii) Within 1,000 hours TIS or 36 calendar months, whichever occurs first,
     since installing the service kit.

(h) REPETITIVE INSPECTIONS

(1) If no cracks are found during the initial inspection required by para-
    graph (g)(1)  or  (2) of this AD,  thereafter repeat the inspection at
    intervals not to exceed 36 calendar months or 1,000 hours TIS,  which-
    ever occurs first  from the last inspection,  as long as no cracks are
    found.

(2) If cracks are found during any inspection required by paragraph (g)(1)
    or (h)(1) of this AD, do the inspection specified in paragraph  (g)(2)
    of this  AD within  36 calendar  months or  1,000 hours TIS, whichever
    occurs first after  installing the service  kit required by  paragraph
    (i)(1) of this AD. Thereafter, repeat the inspection at intervals  not
    to exceed  36 calendar  months or  1,000 hours  TIS, whichever  occurs
    first from the  last inspection, as  long as no  additional cracks are
    found.

(i) CORRECTIVE ACTIONS

(1) If cracks are found during any inspection required by paragraph (g)(1)
    or paragraph (h)(1) of this AD, before further flight, install a serv-
    ice kit  in  accordance  with step 1.D. of the Accomplishment Instruc-
    tions in SEB95-19;  or step 1.C. of the Accomplishment Instructions in
    SEB93-5R2; as applicable to your model airplane.

(2) If cracks are found during any inspection required by paragraph (g)(2)
    or (h)(2) of this AD, before  further flight, repair the area using  a
    method approved by the Manager, Wichita ACO Branch, FAA. For a  repair
    method to be approved by  the Manager,  Wichita ACO Branch as required
    by this  paragraph, the  Manager's approval  letter must  specifically
    refer to  this AD.  You may  use the  contact information in paragraph
    (n)(1) of this AD to obtain FAA approval of your repair method.

(j) REPORTING REQUIREMENT

    Within 30 days after the effective date of this AD,  or within 30 days
    after completing the initial inspection required  by paragraph (g)  of
    this  AD,  whichever occurs later,  report the findings of the initial
    inspection  (regardless if cracks were found or not)  to  the  FAA  at
    Wichita-COS@faa.gov.  Thereafter, within 30 days after completing each
    repetitive inspection required  by  paragraph (h) of this AD,  if  any
    crack was found,  report the crack findings to the FAA at Wichita-COS@
    faa.gov. Include in your reports the following information:

(1) Name and address of the owner;

(2) Date of the inspection;

(3) Name, address, telephone number,  and email address of the person sub-
    mitting the report;

(4) Airplane serial number and total hours TIS on the airplane at the time
    of the inspection; and

(5) If any crack was found during the inspection,  provide  detailed crack
    information as specified below:

(i) A sketch or picture detailing the crack location;

(ii) Measured length of the crack(s) found;

(iii) Installation of a Cessna service kit or any other kit  or repair be-
      fore the inspection; and

(iv) Installation  of  any  supplemental type certificates (STCs), altera-
     tions,  repairs,  or field approvals affecting the area of concern or
     affecting gross weight.

(k) CREDIT FOR PREVIOUS ACTIONS

(1) You may take credit for the initial inspection required  by  paragraph
    (g) of this AD if you performed the inspection  before  the  effective
    date of this  AD using  Cessna Single Engine Service Bulletin SEB93-5,
    dated March 26, 1993; or Cessna Single Engine Service Bulletin SEB93-5
    Revision 1, dated September 8, 1995.

(2) You may take credit for the installation required  by paragraph (i)(1)
    of this AD as follows.

(i) For Model 207, T207, 207A, and T207A airplanes  with a service kit in-
    stalled using SK206-42, SK206-42A, SK206-42B,  or SK206-42C:  You  may
    take credit for the installation if done  before the effective date of
    this  AD  using  Cessna Single Engine Service Bulletin SEB93-5,  dated
    March 26, 1993,  or  Cessna Single Engine  Service  Bulletin  SEB93-5,
    Revision 1, dated September 8, 1995; if the reinforcement of the lower
    forward doorpost bulkhead  and  wing strut fitting specified in Cessna
    Single Engine  Service Kit  SK207-19A,  dated  May 29, 2019,  is  also
    accomplished within 200 hours TIS after the effective date of this AD.

(ii) For  all  other  models:  You may take credit for the installation if
     done before the effective date of this AD  using Cessna Single Engine
     Service Bulletin  SEB93-5,  dated  March 26, 1993;  or  Cessna Single
     Engine Service Bulletin SEB93-5, Revision 1, dated September 8, 1995.

(l) 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
    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 1 hour  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.

(m) 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 (n)(1) 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.

(n) RELATED INFORMATION

(1) 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.

(2) Service information  identified in this AD that is not incorporated by
    reference is available at the addresses specified in paragraphs (o)(3)
    and (4) of this AD.

(o) 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) Cessna Single Engine Service Bulletin SEB93-5,  Revision 2,  dated May
    29, 2019.

(ii) Cessna Single Engine Service Bulletin  SEB95-19,  dated  December 29,
     1995.

(3) For  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: https://support.cessna.com.

(4) You may view  this  service  information  at  the  FAA,  Airworthiness
    Products Section, Operational Safety Branch,  901 Locust, Kansas City,
    Missouri 64106.  For information  on the availability of this material
    at the FAA, call (816) 329-4148.

(5) You  may  view  this  service  information  that  is  incorporated  by
    reference at the National Archives and Records Administration  (NARA).
    For information on the availability of this material  at  NARA,  email
    fedreg.legal@nara.gov,  or  go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on August 24, 2020. Lance T Gant, Director, Compliance & Airworthi-
ness Division, Aircraft Certification Service.

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.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0049; Product Identifier 2017-CE-031-AD; Amendment
39-21222; AD 2020-18-01]
RIN 2120-AA64

Airworthiness Directives; Textron Aviation Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Textron Aviation Inc. (Textron) Model 172N, 172P, 172Q, 172RG,
F172N, F172P, FR172K, R172K, 182E, 182F, 182G, 182H, 182J, 182K, 182L,
182M, 182N, 182P, 182Q, 182R, T182, F182P, F182Q, FR182, R182, TR182,
206, P206, P206A, P206B, P206C, P206D, P206E, TP206A, TP206B, TP206C,
TP206D, TP206E, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G,
TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G, 207, 207A,
T207, T207A, 210-5 (205), 210-5A (205A), 210B, 210C, 210D, 210E, 210F,
and T210F airplanes. This AD was prompted by cracks found in the lower
area of the forward cabin doorpost bulkhead. This AD requires
repetitively inspecting the lower area of the forward cabin doorposts
at the strut attach fitting for cracks and repairing any cracks. The
FAA is issuing this AD to address the unsafe condition on these
products.

DATES: This AD is effective November 12, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 12,
2020.

ADDRESSES: 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; internet: https://support.cessna.com. You may
review 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 and locating Docket No. FAA-2018-0049.

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-
0049; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, any comments received, and other information. The
address for Docket Operations (phone: 800-647-5527) is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, 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

The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD that would apply to certain
serial-numbered Textron Aviation Inc. (Textron) (type certificate
previously held by Cessna Aircraft Company) Model 172N, 172P, 172Q,
172RG, F172N, F172P, FR172K, R172K, 182E,
182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, T182,
F182P, F182Q, FR182, R182, TR182, 206, P206, P206A, P206B, P206C,
P206D, P206E, TP206A, TP206B, TP206C, TP206D, TP206E, U206, U206A,
U206B, U206C, U206D, U206E, U206F, U206G, TU206A, TU206B, TU206C,
TU206D, TU206E, TU206F, TU206G, 207, 207A, T207, T207A, 210-5 (205),
210-5A (205A), 210B, 210C, 210D, 210E, 210F, and T210F airplanes. The
SNPRM published in the Federal Register on May 29, 2020 (85 FR 32308).
The FAA preceded the SNPRM with a notice of proposed rulemaking
(NPRM) that published in the Federal Register on February 1, 2018 (83
FR 4605). The NPRM was prompted by reports of cracks in the lower area
of the forward cabin doorpost bulkhead on more than four dozen Textron
100 and 200 airplanes. The NPRM proposed to require repetitively
inspecting the lower area of the forward cabin doorposts at the strut
attach fitting for cracks and repairing any cracks found by modifying
the area with the applicable service kit. The SNPRM proposed to modify
the estimated costs of the proposed AD, the repetitive inspection
intervals, and the credit allowed for previous actions; clarify the
inspection instructions for airplanes with the service kit installed;
correct the contact information for obtaining the service information;
and add a reporting requirement to collect the inspection results. The
SNPRM also changed some of the model designations listed in the
applicability in order to match the models as they are listed in the
type certificate data sheet.
The FAA is issuing this AD to detect and address cracking of the
wing strut attach point. The unsafe condition, if not addressed, could
result in failure of the wing in operation, which could result in loss
of control of the airplane.

Comments

The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the SNPRM and the FAA's response to each comment.

Support for the SNPRM

Patrick Imperatrice expressed support for the proposed AD.

Request To Extend or Remove Calendar Compliance Time


Kermit Bunde expressed support for the 1,000-hour time-in-service
(TIS) inspection interval but requested the FAA remove the 36-month
calendar time inspection interval. The commenter stated that the 36-
month interval is too often and that cracking is a function of usage
and not only elapsed time. The commenter provided examples of Cessna
maintenance actions that have no calendar time limit.
The FAA disagrees. Both the manufacturer's guidance, which is
published in the supplemental inspection documents (SIDs) for certain
airplanes, and fleet history support the 36-month interval for
inspecting this location. Loading conditions outside of flight, such as
ground loads, handling loads, and tie down loads, may also cause
cracking at this location. Therefore, the FAA determined the inspection
interval of 36 calendar months or 1,000 hours TIS, whichever occurs
first, is necessary to address the unsafe condition. The FAA did not
change this AD based on this comment.

Conclusion

The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule as proposed.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Cessna Single Engine Service Bulletin SEB93-5,
Revision 2, dated May 29, 2019 (SEB93-5R2) and Cessna Single Engine
Service Bulletin SEB95-19, dated December 29, 1995 (SEB95-19). For the
applicable model airplanes, the service information contains procedures
for repetitively inspecting the lower area of the forward cabin
doorposts for cracks and repairing any cracks found by modifying the
area with the applicable Cessna service kit.
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

The FAA reviewed Cessna Single Engine Service Kit SK172-147, dated
December 29, 1995. This service kit provides instructions to add a
channel to each forward cabin doorpost bulkhead. The FAA also reviewed
Cessna Single Engine Service Kit SK182-115, dated December 29, 1995;
Cessna Single Engine Service Kit SK206-42D, dated May 29, 2019; and
Cessna Single Engine Service Kit SK210-156, dated December 29, 1995.
For the applicable model airplanes, these service kits provide
instructions to add a doubler and a channel to each forward cabin
doorpost bulkhead. In addition, the FAA reviewed Cessna Single Engine
Service Kit SK207-19A, dated May 29, 2019. The service information
contains procedures to reinforce the lower forward doorpost bulkhead
and wing strut fitting by adding a doubler and a channel to each
forward cabin doorpost bulkhead.

Costs of Compliance

The FAA estimates that this AD affects 14,653 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspect the lower area of the forward cabin doorposts for cracks. 1.5 work-hours x $85 per hour = $127.50 Not applicable $127.50 $1,868,257.50
Reporting requirement 1 work-hour x $85 per hour = $85 Not applicable 85 1,245,505

The FAA estimates the following costs to do any necessary repairs
that would be required based on the results of the inspection.
Reference the applicable Cessna single engine service bulletin for kit
applicability. The FAA has no way of determining the number of
airplanes that might need this repair.

On-Condition Costs

Action Labor cost Parts cost Cost per product
Install Cessna Single-Engine Service Kit SK172-147 36 work-hours x $85 per hour = $3,060 $3,415 $6,475
Install Cessna Single-Engine Service Kit SK182-115 36 work-hours x $85 per hour = $3,060 7,490 10,550
Install Cessna Single-Engine Service Kit SK206-42D 36 work-hours x $85 per hour = $3,060 3,115 6,175
Install Cessna Single-Engine Service Kit SK207-19A 36 work-hours x $85 per hour = $3,060 4,957 8,017
Install Cessna Single-Engine Service Kit SK210-156 36 work-hours x $85 per hour = $3,060 7,020 10,080

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. Public reporting for this collection of information is estimated
to be approximately 1 hour per response, including the time for
reviewing instructions, searching existing data sources, gathering and
maintaining the data needed, completing and reviewing the collection of
information. All responses to this collection of information are
mandatory. Send comments regarding this burden estimate or any other
aspect of this collection of information, including suggestions for
reducing this burden to: Information Collection Clearance Officer,
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX
76177-1524.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings

This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):