DEPARTMENT OF TRANSPORTATION

FEDERAL AVIATION ADMINISTRATION

14 CFR Part 39

[Docket No. 2002-CE-23-AD]
RIN 2120-AA64
 
AIRWORTHINESS DIRECTIVES; Cessna Aircraft Company Models 208 and 
208B Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to revise Airworthiness Directive (AD)  2002
-22-17, which  currently requires  you to  repetitively inspect  the inboard
forward flap bellcranks for  cracks and eventually replace  these bellcranks
on all Cessna  Aircraft Company (Cessna)  Models 208 and  208B airplanes. AD
2002-22-17  resulted  from  Cessna re-evaluating  the  bellcrank  life limit
analysis and determining that the  original estimate is too high.  Since FAA
issued AD 2002-22-17, Cessna has designed  a new flap bellcrank with a  life
limit of 40,000 landings (instead of 7,000 landings). This proposed AD would
retain the  requirement that  you repetitively  inspect the  inboard forward
flap bellcranks for cracks and eventually replace these bellcranks and would
provide the option of installing  the new design flap bellcrank  to increase
the  life  limits  and terminate  the  repetitive  inspections. The  actions
specified by this proposed AD  are intended to detect, correct,  and prevent
future cracks in the bellcrank, which could result in failure of this  part.
Such  failure  could lead  to  damage to  the  flap system  and  surrounding
structure and result in reduced or loss of control of the airplane.

DATES: The Federal Aviation  Administration (FAA) must receive  any comments
on this proposed rule on or before October 6, 2003.

ADDRESSES: Submit comments  to FAA, Central  Region, Office of  the Regional
Counsel, Attention: Rules  Docket No. 2002-CE-23-AD,  901 Locust, Room  506,
Kansas City,  Missouri 64106.  You may  view any  comments at  this location
between 8 a.m. and 4  p.m., Monday through Friday, except  Federal holidays.
You may also send comments electronically to the following address:  9-ACE-7
-Docket@faa.gov.  Comments  sent electronically  must  contain ``Docket  No.
2002-CE-23-AD'' in the subject line. If you send comments electronically  as
attached electronic files, the files must be formatted in Microsoft Word  97
for Windows or ASCII text.

You may get service information that applies to this proposed AD from Cessna
Aircraft  Company,  Product Support,  PO  Box 7706,  Wichita,  Kansas 67277;
telephone: (316) 517-5800; facsimile: (316) 942-9006. You may also view this
information at the Rules Docket at the address above.

FOR  FURTHER  INFORMATION  CONTACT: Paul  Nguyen,  Aerospace  Engineer, FAA,
Wichita  Aircraft Certification  Office ACO,  1801 Airport  Road, Room  100,
Wichita, Kansas 67209; telephone: 316-946-4125; facsimile: 816-946- 4407.

SUPPLEMENTARY INFORMATION:

COMMENTS INVITED

How do  I comment  on this  proposed AD?  The FAA  invites comments  on this
proposed rule. You may submit whatever written data, views, or arguments you
choose. You  need to  include the  proposed rule's  docket number and submit
your comments to the address specified under the caption ADDRESSES. We  will
consider all comments received on or  before the closing date. We may  amend
this proposed rule in light  of comments received. Factual information  that
supports your ideas and suggestions  is extremely helpful in evaluating  the
effectiveness of this proposed AD action and determining whether we need  to
take additional rulemaking action.

Are there any specific portions of  this proposed AD I should pay  attention
to?  The  FAA  specifically  invites  comments  on  the  overall regulatory,
economic, environmental, and energy aspects of this proposed rule that might
suggest a  need to  modify the  rule. You  may view  all comments we receive
before and after the closing date of  the rule in the Rules Docket. We  will
file a report in the Rules Docket that summarizes each contact we have  with
the public that concerns the substantive parts of this proposed AD.

How can I be  sure FAA receives my  comment? If you want  FAA to acknowledge
the receipt  of your  mailed comments,  you must  include a  self-addressed,
stamped postcard. On  the postcard, write  ``Comments to Docket  No. 2002-CE
-23-AD.'' We will date stamp and mail the postcard back to you.

DISCUSSION

Has FAA taken any action to  this point? Ten cracked bellcrank incidents  on
Cessna  Models 208  and 208B  airplanes caused  us to  issue AD  2002-22-17,
Amendment 39-12944 (67 FR 68508, November 12, 2002). AD 2002-22-17 currently
requires the following on Cessna Models 208 and 208B airplanes:

--Inspecting,  using  eddy  current  inspection,  the  inboard  forward flap
  bellcrank for cracks; and

--Replacing the inboard forward flap bellcrank.

What has  happened since  AD 2002-22-17  to initiate  this proposed  action?
Since we  issued AD  2002-22-17, Cessna  has designed  a new flap bellcrank,
part number (P/N) 2622311-7, with  a life limit of 40,000  landings (instead
of  7,000  landings).  The  new  flap  bellcrank  (P/N  2622311-7)  may   be
substituted for the older flap bellcranks, either P/N 2622281-2, 2622281-12,
or 2692001-2. Installation  of this new  flap bellcrank would  eliminate the
need for repetitive inspections.

Is there service information that applies to this subject? Cessna has issued
the following service information:

--Cessna Caravan Service Bulletin No.: CAB02-1, dated February 11, 2002;

--Cessna Caravan Service Bulletin  No.: CAB02-12, Revision 1,  dated January
  27, 2003; and

--Cessna Caravan Service Kit No.: SK208-148A, dated January 27, 2003.

What are the provisions of this service information? The service information
includes procedures for:

--Inspecting, using eddy current methods, the inboard forward flap bellcrank
  for cracks; and

--Replacing bellcranks.

The  FAA's  Determination  and  an Explanation  of  the  Provisions  of This
Proposed AD

What has FAA  decided? After examining  the circumstances and  reviewing all
available  information related  to the  incidents described  above, we  have
determined that:

--The unsafe condition referenced in  this document exists or could  develop
  on other Cessna Models 208 and 208B airplanes of the same type design;

--The installation  of either  the 7,000  landings or  40,000 landings  life
  limit bellcranks addresses the unsafe condition;

--The  actions specified  in the  previously-referenced service  information
  should be accomplished on the affected airplanes; and

--AD action should be taken in order to correct this unsafe condition.

What would this  proposed AD require?  This proposed action  would revise AD
2002-22-17 by proposing a new AD that would:

--Retain the requirements of AD 2002-22-17; and

--Provide  the  option  of   installing  the  40,000  landings   life  limit
  bellcranks.

How does the revision to 14 CFR part 39 affect this proposed AD? On July 10,
2002, FAA published a new version of  14 CFR part 39 (67 FR 47997,  July 22,
2002), which governs FAA's AD system. This regulation now includes  material
that relates to special  flight permits, alternative methods  of compliance,
and  altered  products.  This  material  previously  was  included  in  each
individual AD. Since this  material is included in  14 CFR part 39,  we will
not include it in future AD actions.

COST IMPACT

How many  airplanes would  this proposed  AD impact?  We estimate  that this
proposed AD affects 1,300 airplanes in the U.S. registry.

What would be the  cost impact of this  proposed AD on owners/  operators of
the affected airplanes?  We estimate the  following costs to  accomplish the
proposed inspection:

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                                                                       TOTAL COST PER      TOTAL COST ON U.S.
              LABOR COST                         PARTS COST               AIRPLANE             OPERATORS
----------------------------------------------------------------------------------------------------------------
1 workhour x $60 per hour = $60......          No cost for parts............ $60         $60 x 1,300 = $78,000
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We estimate  the following  costs to  accomplish any  necessary replacements
using the same flap bellcrank (P/N 2622281-2, 2622281-12, 2692001-2, or  FAA
-approved  equivalent P/N)  that would  be required  based on  the proposed
inspection or the reduced life limits:

----------------------------------------------------------------------------------------------------------------
              LABOR COST                PARTS COST    TOTAL COST PER AIRPLANE     TOTAL COST ON U.S. OPERATORS
----------------------------------------------------------------------------------------------------------------
3 workhours x $60 per hour = $180.....     $1,793      $180 + $1,793 = $1,973       $1,973 x 1,300 = $2,564,900
----------------------------------------------------------------------------------------------------------------

We estimate  the following  costs to  accomplish any  necessary replacements
using  the name  flap bellcrank  (P/N 2622311-7  2692001-2, or  FAA-approved
equivalent P/N) that would be  required based on the proposed  inspection or
the  reduced  life limits.  We  have no  way  of determining  the  number of
airplanes that may need such replacement with the new flap bellcrank:

------------------------------------------------------------------------
         LABOR COST              PARTS COST     TOTAL COST PER AIRPLANE
------------------------------------------------------------------------
3 workhours x $60 per.......       $1,845        $180 + $1,845 = $2,025
hour = $180.................
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What is the difference between the  cost impact of this proposed AD  and the
cost impact  of AD  2002-22-17? AD  2002-22-17 already  established the life
limit for the flap bellcrank  (P/N 2622281-2, 2622281-12, 2692001-2, or  FAA
-approved  equivalent  P/N)  on  the  affected  airplanes.  Therefore,   the
replacement is already required through that AD. The only difference in  the
cost impact upon  the public of  this proposed AD  and AD 2002-22-17  is the
additional $52 cost difference for the new flap bellcrank.

REGULATORY IMPACT

Would this  proposed AD  impact various  entities? The  regulations proposed
herein would  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. Therefore, it  is determined that  this proposed rule  would not
have federalism implications under Executive Order 13132.

Would this proposed AD involve a significant rule or regulatory action?  For
the reasons discussed above, I certify that this proposed action (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);  and  (3)  if  promulgated,  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. A
copy of the  draft regulatory evaluation  prepared for this  action has been
placed in the Rules Docket. A copy  of it may be obtained by contacting  the
Rules Docket at the location provided under the caption ADDRESSES.

LIST OF SUBJECTS IN 14 CFR PART 39

Air transportation, Aircraft, Aviation safety, Safety.

THE PROPOSED AMENDMENT

Accordingly, under the authority delegated  to me by the Administrator,  the
Federal Aviation  Administration proposes  to amend  part 39  of the Federal
Aviation Regulations (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. FAA amends Sec.  39.13  by removing Airworthiness Directive (AD)  2002-22
-17, Amendment 39-12944 (67  FR 68508, November 12,  2002), and by adding  a
new AD to read as follows: