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2015-19-10 M7 AEROSPACE: Amendment 39-18272; Docket No. FAA-2015-2207; Directorate Identifier 2015-CE-003-AD.
(a) EFFECTIVE DATE

    This AD is effective November 3, 2015.

(b) AFFECTED ADS

    This AD supersedes AD 97-02-02, Amendment 39-9886 (62 FR 2552, January
    17, 1997).

(c) APPLICABILITY

    This AD applies to M7 Aerospace LLC Models SA26-AT, SA26-T,  SA226-AT,
    SA226-T, SA226-T(B),  SA226-TC, SA227-AC  (C-26A), SA227-AT,  SA227-BC
    (C-26A),  SA227-CC, SA227-DC  (C-26B), SA227-TT,  all serial  numbers,
    certificated in any category.

(d) SUBJECT

    Joint Aircraft System Component (JASC)/Air Transport Association (ATA)
    of America Code 27, Flight Controls.

(e) UNSAFE CONDITION

    AD 97-02-02  (62 FR 2552, January 17, 1997)  ("AD 97-02-02")  resulted
    from reports of Fairchild SA227 series airplanes losing pitch  control
    in-flight. This supersedure was  prompted by an operator  experiencing
    complete  loss of  elevator control  because  of  failure of  the bolt
    attaching the elevator control rod to the elevator walking beam  under
    the cockpit floor.  We are issuing  this AD to  prevent loss of  pitch
    control, which  if not  corrected, could  result in  loss of  airplane
    control.

(f) COMPLIANCE

    Comply  with this  AD within  the compliance  times specified,  unless
    already done. Models SA227-CC  and SA227-DC, serial numbers  892, 893,
    and 895 and up, have the revised (modified) configuration. Since those
    airplanes  are already  in compliance,  they  do  not have  to do  the
    actions  in  paragraphs  (h)  or   (i)  of  this  AD,  including   all
    subparagraphs. Those airplanes must  still do the actions  required in
    paragraph (j) of this AD, including all subparagraphs.

(g) CREDIT  FOR  ACTIONS  ACCOMPLISHED IN ACCORDANCE WITH PREVIOUS SERVICE
    INFORMATION

    This AD  allows credit  for the  control column  pivot bearing  torque
    check and initial replacement required in paragraph (i)(2) of this  AD
    and the elevator rod bolt inspection and initial replacement  required
    in paragraphs (j)(1) and (j)(3)(i) of this AD, if done before November
    3, 2015  (the effective  date of  this AD),  following the  procedures
    specified in the Accomplishment Instructions of the applicable service
    information listed in paragraphs (g)(1) through (g)(4) of this AD:

(1) M7 Aerospace SA227 Commuter Category  Service Bulletin No. CC7-27-010,
    original issue or revision 1.

(2) M7 Aerospace  SA227 Series Service Bulletin  No. 227-27-041,  original
    issue or revision 1.

(3) M7 Aerospace SA226 Series Service Bulletin  No.  226-27-060,  original
    issue or revision 1.

(4) M7 Aerospace SA26 Series Service Bulletin No.  26-27-30-046,  original
    issue or revision 1.

(h) CONTROL COLUMN PIVOT BEARING REVISED (MODIFIED) CONFIGURATION

(1) On or before the airplane accumulates a total of 35,000 hours time-in-
    service (TIS)  or within  the next  1,000 hours  TIS after November 3,
    2015 (the effective date of this AD), whichever occurs later, you must
    revise (modify)  the control  column pivot  bearing configuration with
    the improved design. Use the applicable service information listed  in
    paragraphs  (h)(1)(i)   through  (h)(1)(iv)   of  this   AD.  Revising
    (modifying) the configuration of the control column pivot bearing with
    the improved design terminates the  actions for paragraph (i) of  this
    AD,  including  all subparagraphs,  but  you must  still  complete the
    required  actions  in  paragraph   (j)  of  this  AD,   including  all
    subparagraphs.

(i) Fairchild Aircraft  SA26  Series  Service  Bulletin  No. 26-27-30-047,
    dated June 16, 1997;

(ii) Fairchild Aircraft  SA226  Series  Service  Bulletin  No. 226-27-061,
     dated June 16, 1997;

(iii) Fairchild Aircraft SA227  Series  Service  Bulletin  No. 227-27-042,
      dated June 16, 1997; or

(iv) Fairchild Aircraft SA227  Series  Commuter  Category  No. CC7-27-011,
     dated June 16, 1997.

(2) You  may  at  any  time  before  35,000 hours TIS  revise (modify) the
    control column pivot bearing configuration with the improved design to
    terminate the  repetitive replacement  of the  original control column
    pivot  bearing  using  the applicable  service  information  listed in
    paragraphs  (h)(1)(i)  through  (h)(1)(iv)  of  this  AD.  This action
    terminates the requirements of paragraph (i) of this AD, including all
    subparagraphs, but  you must  still complete  the required  actions in
    paragraph (j) of this AD, including all subparagraphs.

(i) TORQUE CHECK OR REPLACEMENT OF THE CONTROL COLUMN PIVOT BEARING

(1) Use the service information,  as applicable,  listed in paragraphs (i)
    (1)(i) through  (i)(1)(iv) of  this AD  to do  a control  column pivot
    bearing torque check or replacement at the applicable compliance times
    in paragraph (i)(2) or (i)(3) of this AD, including all subparagraphs:

(i) M7 Aerospace LLC SA26  Series  Service  Bulletin  No. 26-27-30-046 R2,
    dated December 5, 2014;

(ii) M7 Aerospace LLC SA226 Series  Service  Bulletin  No.  226-27-060 R2,
     dated December 5, 2014;

(iii) M7 Aerospace LLC SA227 Series  Service  Bulletin  No. 227-27-041 R2,
      dated December 5, 2014; or

(iv) M7 Aerospace LLC SA227 Series Commuter Category  Service Bulletin No.
     CC7-27-010 R2, December 5, 2014.

(2) For  airplanes where  the control column pivot bearing has been torque
    checked or replaced within the  last 10,000 hours TIS before  November
    3, 2015 (the effective date  of this AD) using the  applicable service
    information listed  in paragraph  (g)(1) through  (g)(4) or  (i)(1)(i)
    through (i)(1)(iv) of this AD, do one of the following actions:

(i) Within  the  next 10,000 hours TIS after the last control column pivot
    bearing replacement or within the next 1,000 hours TIS after  November
    3, 2015 (the effective date  of this AD), whichever occurs  later, and
    repetitively thereafter  every 10,000  hours TIS,  replace the control
    column pivot  bearing following  paragraph 2.B.  of the Accomplishment
    Instructions  of   the  applicable   service  information   listed  in
    paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or

(ii) Within the next 10,000 hours TIS after  the last control column pivot
     bearing replacement or within the next 1,000 hours TIS after November
     3, 2015  (the effective  date of  this AD),  whichever occurs  later,
     revise (modify) the control  column pivot bearing configuration  with
     the improved design using  the applicable service information  listed
     in  paragraphs  (h)(1)(i)  through (h)(1)(iv)  of  this  AD. Revising
     (modifying) the  configuration of  the control  column pivot  bearing
     with the improved design terminates the repetitive replacement of the
     original control column pivot bearing. No other actions are  required
     for paragraph (i)  of this AD,  including all subparagraphs,  but you
     must  still  complete  the  actions  in  paragraph  (j)  of  this AD,
     including all subparagraphs.

(3) For  airplanes  where  the  control column pivot bearing  has not been
    torque checked  or replaced  within the  last 10,000  hours TIS before
    November 3, 2015 (the effective date of this AD) using the  applicable
    service  information listed  in  paragraphs  (g)(1) through  (g)(4) or
    (i)(1)(i) through (i)(1)(iv) of this AD, within the next 200 hours TIS
    after November 3, 2015 (the  effective date of this AD),  torque check
    the  control  column pivot  bearing  following paragraph  2.A.  of the
    service information listed in paragraphs (i)(1)(i) through  (i)(1)(iv)
    of this AD.

(4) If nut movement occurs during  the  torque check required in paragraph
    (i)(3) of this AD, do one of the following actions:

(i) Before further flight and  repetitively thereafter at intervals not to
    exceed  every  10,000  hours TIS,  replace  the  control column  pivot
    bearing following paragraph 2.B. of the Accomplishment Instructions of
    the  applicable  service information  listed  in paragraphs  (i)(1)(i)
    through (i)(1)(iv) of this AD; or

(ii) Before further flight, revise (modify) the control column pivot bear-
     ing  configuration  with  the improved  design  using  the applicable
     service information listed in paragraphs (h)(1)(i) through (h)(1)(iv)
     of this  AD. Revising  (modifying) the  configuration of  the control
     column  pivot  bearing  with  the  improved  design  terminates   the
     repetitive replacement of the original control column pivot  bearing.
     No other actions are required for paragraph (i) of this AD, including
     all  subparagraphs,  but  you  must  still  complete  the  actions in
     paragraph (j) of this AD, including all subparagraphs.

(5) If no nut movement occurs  during  the  torque check required in para-
    graph (i)(3) of this AD, do one of the following actions:

(i) Within the  next 1,000 hours TIS after November 3, 2015 (the effective
    date of this AD), replace  the control column pivot bearing  following
    paragraph 2.B.  of the  Accomplishment Instructions  of the applicable
    service information listed in paragraphs (i)(1)(i) through  (i)(1)(iv)
    of this AD; or

(ii) Within the next 1,000 hours TIS after November 3, 2015 (the effective
     date of this  AD), revise (modify)  the control column  pivot bearing
     configuration with the improved  design using the applicable  service
     information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this
     AD.  Revising (modifying)  the  configuration  of the  control column
     pivot  bearing with  the improved  design terminates  the  repetitive
     replacement of the original control column pivot bearing.

(j) INSPECT THE ELEVATOR CONTROL ROD ENDS AND HARDWARE

(1) Within  the  next 200 hours TIS after  November 3, 2015 (the effective
    date of this AD), inspect  the elevator control rod ends  and hardware
    for wear, creasing, or other  damage and verify the elevator  rod bolt
    and attachment hardware for correct configuration following  paragraph
    2.D.  of the  Accomplishment Instructions  of  the  applicable service
    information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of  this
    AD.

(2) If any damage is  found  during  the  inspection required in paragraph
    (j)(1) of  this AD  or the  elevator rod  bolt and attachment hardware
    does not match the correct configuration,  before further flight,  re-
    place the elevator rod bolt, rod ends, and associated hardware follow-
    ing  paragraph  2.D.  of   the  Accomplishment  Instructions  of   the
    applicable service information listed in paragraphs (i)(1)(i)  through
    (i)(1)(iv) of this AD.

(3) Replace  the  elevator rod end bolt and  associated hardware following
    paragraph 2.D.  of the  Accomplishment Instructions  of the applicable
    service information listed in paragraphs (i)(1)(i) through  (i)(1)(iv)
    of this AD at whichever of the following compliance times applies  and
    repetitively thereafter at intervals not to exceed 10,000 hours TIS:

(i) For airplanes  where  the  elevator rod bolt has been replaced: Within
    the next 10,000 hours TIS after the last elevator rod bolt replacement
    or  within  the next  1,000  hours TIS  after  November 3,  2015  (the
    effective date of this AD), whichever occurs later; or

(ii) For airplanes  where  the  elevator rod bolt has never been replaced:
     Within the next 200 hours  TIS after November 3, 2015  (the effective
     date of this AD).

(k) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The Manager, Fort Worth Airplane Certification Office,  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 ACO, send  it to the attention  of the
    person identified in paragraph (l)(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.

(l) RELATED INFORMATION

(1) For more information about this AD,  contact Andrew McAnaul, Aerospace
    Engineer,  FAA,  ASW-143 (c/o San Antonio MIDO),  10100 Reunion Place,
    Suite 650, San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210)
    308-3370; email: andrew.mcanaul@faa.gov.

(m) 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) M7 Aerospace LLC SA26  Series  Service  Bulletin  No. 26-27-30-046 R2,
    dated December 5, 2014.

(ii) M7 Aerospace LLC SA226  Series  Service  Bulletin  No. 226-27-060 R2,
     dated December 5, 2014.

(iii) M7 Aerospace LLC SA227 Series  Service  Bulletin  No. 227-27-041 R2,
      dated December 5, 2014.

(iv) M7 Aerospace LLC SA227 Series Commuter Category  Service Bulletin No.
     CC7-27-010 R2, December 5, 2014.

(v) Fairchild Aircraft SA26  Series  Service  Bulletin  No.  26-27-30-047,
    dated June 16, 1997.

(vi) Fairchild Aircraft SA226  Series  Service  Bulletin  No.  226-27-061,
     dated June 16, 1997.

(vii) Fairchild Aircraft SA227  Series  Service  Bulletin  No. 227-27-042,
      dated June 16, 1997.

(viii) Fairchild Aircraft SA227 Series Commuter  Category  No. CC7-27-011,
       dated June 16, 1997.

(3) For  service information identified in this AD,  contact  M7 Aerospace
    LLC,  10823 NE Entrance Road, San Antonio, Texas 78216;  phone:  (210)
    824-9421;  fax: (210) 804-7766;  Internet: http://www.elbitsystems-us.
    com; email: MetroTech@M7Aerospace.com.

(4) You  may  view  this  service  information  at  FAA,   Small  Airplane
    Directorate, 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  September 17, 2015.  Melvin Johnson,
Acting  Manager,  Small   Airplane  Directorate,  Aircraft   Certification
Service.

FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer,  FAA,
ASW-143  (c/o  San Antonio MIDO),  10100  Reunion  Place,  Suite 650,  San
Antonio, Texas 78216;  phone: (210) 308-3365;  fax: (210) 308-3370; email:
andrew.mcanaul@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2207; Directorate Identifier 2015-CE-003-AD;
Amendment 39-18272; AD 2015-19-10]
RIN 2120-AA64

Airworthiness Directives; M7 Aerospace LLC Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 97-02-02 for
certain Models SA26-AT, SA26-T, SA226-AT, SA226-T, SA226-T(B), SA226-
TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC
(C-26B), and SA227-TT airplanes. AD 97-02-02 required applying torque
to the control column pitch bearing attaching nuts, inspecting the
bearing assembly, inspecting the elevator control rod end bearing
retainer/dust seals, and replacing or installing new parts as
necessary. This new AD requires inspecting for movement and correct
torque of the elevator control pivot bearing, inspecting the elevator
control rod for damage and correct configuration, and replacing parts
as necessary. This AD also requires a 10,000-hour time-in-service (TIS)
repetitive replacement of the control column pivot bearing and elevator
control rod bolt and requires replacement of the control column pivot
bearing with the improved design by 35,000 hours TIS. This AD was
prompted by loss of elevator control due to failure of the bolt
attaching the elevator control rod to the elevator walking beam under
the cockpit floor. We are issuing this AD to correct the unsafe
condition on these products.

DATES: This AD is effective November 3, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 3,
2015.

ADDRESSES: For service information identified in this AD, contact M7
Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone:
(210) 824-9421; fax: (210) 804-7766; Internet: http://www.elbitsystems-us.com;
email: MetroTech@M7Aerospace.com. You may view this referenced
service information at the FAA, Small Airplane Directorate, 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 Docket No.
FAA-2015-2207.

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-2015-
2207; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Document Management Facility, 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: Andrew McAnaul, Aerospace Engineer,
FAA, ASW-143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650,
San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370;
email: andrew.mcanaul@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 97-02-02, Amendment 39-9886 (62 FR 2552,
January 17, 1997), (``AD 97-02-02''). AD 97-02-02 applied to certain M7
Aerospace LLC Models SA26-AT, SA26-T, SA226-AT, SA226-T, SA226-T(B),
SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC,
SA227-DC (C-26B), and SA227-TT airplanes. The NPRM published in the
Federal Register on June 16, 2015 (80 FR 34326). The NPRM was prompted
by an operator experiencing complete loss of elevator control due to
failure of the bolt attaching the elevator control rod to the elevator
walking beam under the cockpit floor. A follow-on inspection of the
operator's fleet revealed a variety of hardware installed. Some
hardware matched the illustrated parts catalog (IPC), some matched the
AD 97-02-02 configuration, and some matched neither of those
configurations.
When AD 97-02-02 was issued, the IPC was never revised to match the
hardware configuration called out in AD 97-02-02 or in the service
information associated with that AD. Because of the conflict between
the AD and the IPC configurations, an airplane that was in compliance
with the requirements of AD 97-02-02 could have had an incorrect
hardware configuration installed during routine maintenance after
complying with the AD. The IPC has been updated and corrected by M7
Aerospace, LLC.
Also, since we issued AD 97-02-02, the manufacturer developed an
improved design for the control column pivot bearing and support
structure that terminates the repetitive torque check and replacement
of control column pivot bearings.
The manufacturer also issued new service information that adds the
10,000-hour TIS repetitive replacement of the control column pivot
bearing that is in the airworthiness limitations section (ALS) of the
airplane maintenance manual (AMM) and (if this revision is mandated)
requires the replacement of the pivot bearing with the improved design
by 35,000 hours TIS that is in the supplemental inspections document
(SID). Issuance of the new service information, the revised IPC, and this AD will
eliminate the conflicts between AD 97-02-02, the service information,
the IPC, the ALS, and the SID.
The NPRM (80 FR 34326, June 16, 2015) proposed to require
inspecting for movement and correct torque of the elevator control
pivot bearing, inspecting the elevator control rod for damage and
correct configuration, and replacing parts as necessary. The NPRM also
proposed to require a 10,000-hour TIS repetitive replacement of the
control column pivot bearing and elevator control rod bolt and require
replacement of the control column pivot bearing with the improved
design by 35,000 hours TIS. Replacing the original control column pivot
bearing with the improved design terminates the requirement to
repetitively replace the original control column pivot bearing every
10,000 hours. We are issuing this AD to correct the unsafe condition on
these products.

Comments

We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (80 FR 34326, June 16,
2015) or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (80 FR 34326, June 16, 2015) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 34326, June 16, 2015).

Relevant Service Information Under 1 CFR 51

We reviewed M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-
046 R2, dated December 5, 2014; Fairchild Aircraft SA26 Series Service
Bulletin No. 26-27-30-047, dated June 16, 1997; M7 Aerospace SA226
Series Service Bulletin No. 226-27-060 R2, dated December 5, 2014;
Fairchild Aerospace SA226 Series Service Bulletin No. 226-27-061, dated
June 16, 1997; M7 Aerospace SA227 Series Service Bulletin, No. 227-27-
041 R2, dated December 5, 2014; Fairchild Aircraft SA227 Series Service
Bulletin No. 227-27-042, dated June 16, 1997; M7 Aerospace LLC SA227
Series Commuter Category Service Bulletin No. CC7-27-010 R2, dated
December 5, 2014; and Fairchild Aircraft SA227 Series Commuter Category
Service Bulletin No. CC7-27-011, dated June 16, 1997. The service
information describes procedures for inspecting for movement and
correct torque of the elevator control pivot bearing, inspecting the
elevator control rod for damage, and replacing parts as necessary. The
service information also adds a repetitive replacement of the control
column pivot bearings at 10,000 hours TIS and requires replacement of
the control column pivot bearing with the improved design within 35,000
hours TIS. This 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 of this
AD.

Costs of Compliance

We estimate that this AD affects 360 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:

Estimated Costs

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection of torque on the control column pivot bearing. 2 work-hours x $85 per hour = $170 Not applicable $170 $61,200
Control column pivot bearing replacement. 8 work-hours x $85 per hour = $680 $300 980 352,800
New designed control column pivot bearing replacement. 20 work-hours x $85 per hour = $1,700 $2,450 4,150 1,494,000
Elevator rod end bolt replacement. 4 work-hours x $85 per hour = $340 $10 350 126,000

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.

Regulatory Findings

We have determined that 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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
97-02-02, Amendment 39-9886 (62 FR 2552, January 17, 1997), and adding
the following new AD: