NPRM Reopening Comment Period. 208 & 208B Flap Bellcrank

NPRM Reopening Comment Period. 208 & 208B Flap Bellcrank

Reopening of the comment period.
[Docket No. 2002-CE-23-AD]
RIN 2120-AA64

Airworthiness Directives; Cessna Aircraft Company Models 208 and
208B Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
the comment period.

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

SUMMARY: The FAA proposes to revise an earlier NPRM airworthiness
directive (AD) action that applies to certain Cessna Aircraft Company
(Cessna) Models 208 and 208B airplanes. That proposed AD would have
revised 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 Models 208 and 208B airplanes.
The proposed AD would have provided the option of installing a newly
designed bellcrank to increase the life limits and terminate the
repetitive inspections. AD 2003-21-04 also requires inspections of the
inboard forward flap bellcranks on these airplanes. The FAA has
determined that additional inspections of the bellcranks are necessary
on Cessna Models 208 and 208B airplanes. We believe that it would be
less confusing if all of these actions were in one AD. Therefore, FAA
proposes to supersede AD 2002-22-17 and AD 2003-21-04. Since the added
actions from AD 2003-21-04 and other proposed inspections impose an
additional burden over that proposed in the NPRM, we are reopening the
comment period to allow the public the chance to comment on these
additional actions.

DATES: We must receive any comments on this proposed AD by May 17,
2004.

ADDRESSES: Use one of the following to submit comments on this proposed
AD:
     By mail: FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2002-CE-23-AD, 901
Locust, Room 506, Kansas City, Missouri 64106.
     By fax: (816) 329-3771.
     By e-mail: This e-mail address is being protected from spambots. You need JavaScript enabled to view it . 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.
    You may get the service information identified in this proposed AD
from Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita,
Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006.
    You may view the AD docket at FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2002-CE-23-AD, 901
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m.
to 4 p.m., Monday through Friday, except Federal holidays.

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-
4107.

SUPPLEMENTARY INFORMATION:

Comments Invited

How Do I Comment on This Proposed AD?

    We invite you to submit any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2002-CE-23-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it. We will date-stamp your postcard and
mail it back to you.

Are There Any Specific Portions of This Proposed AD I Should Pay
Attention To?

    We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. If you
contact us through a nonwritten communication and that contact relates
to a substantive part of this proposed AD, we will summarize the
contact and place the summary in the docket. We will consider all
comments received by the closing date and may amend this proposed AD in
light of those comments and contacts.

Discussion

What Events Have Caused This Proposed AD?

    The need to reduce the life limit and repetitively inspect the
inboard forward flap bellcrank on Cessna Models 208 and 208A airplanes
caused us to issue AD 2002-22-17, Amendment 29-12944 (67 FR 68508,
November 12, 2002).
    Since FAA 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, P/N
2622281-2, 2622281-12, or 2692001-2. Installation of this new flap
bellcrank will eliminate the need for repetitive inspections.

Has FAA Taken Any Action to This Point?

    We issued a proposal to amend part 39 of the Federal Aviation
Regulations (14 CFR part 39) to include an AD that would apply to all
Cessna Models 208 and 208B airplanes. This proposal was published in
the Federal Register as a notice of proposed rulemaking (NPRM) on July
28, 2003 (68 FR 44252). The NPRM proposed to 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.

Was the Public Invited To Comment?

    The FAA encouraged interested persons to participate in developing
this amendment. We did not receive any comments on the proposed rule or
on our determination of the cost to the public.

What Events Have Caused FAA To Issue a Supplemental NPRM?

    The FAA recently issued AD 2003-21-04, Amendment 39-13339 (68 FR
59707, October 17, 2003) to require you to immediately inspect certain
inboard forward flap bellcranks for cracks, deformation, and missing/
incomplete welds. If cracks, deformation, or missing/incomplete welds
are found, the AD would require you to immediately replace the flap
bellcrank or temporarily incorporate certain flap limitations.
    In addition, FAA has identified other bellcranks within the flap
system that require inspection. The FAA has determined that all of the
inspections and replacements of the bellcranks should be included in
one AD. These inspections are referenced in Cessna Caravan Service
Bulletin CAB03-11, Revision 1, dated September 24, 2003.

FAA's Determination and Requirements 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

[[Page 10642]]

on other Cessna Models 208 and 208B airplanes of the same type design
that are on the U.S. registry;
--We should combine the actions of AD 2002-22-17, AD 2003-21-04, and
those referenced in Cessna Caravan Service Bulletin CAB03-11, Revision
1, dated September 24, 2003; and
--We should take AD action to correct this unsafe condition.

The Supplemental NPRM

How Will the Changes to the NPRM Impact the Public?

    Adding the inspection and replacement requirements from both AD
2003-21-04 and Cessna Caravan Service Bulletin CAB03-11, Revision 1,
dated September 24, 2003, goes beyond the scope of what was originally
proposed in the NPRM. Therefore, we are reopening the comment period
and allowing the public the chance to comment on these additional
actions.

What Are the Provisions of the Supplemental NPRM?

    The proposed AD would supersede AD 2002-22-17 and AD 2003-21-04 by
requiring you to:
--Do all current requirements of AD 2002-22-17;
--Provide the option of installing the 40,000 landings life limit
bellcranks;
--Inspect all bellcranks for cracks, deformation, and missing/
incomplete welds; and
--If cracks, deformation, or missing/incomplete welds are found, the AD
would require you to immediately replace the bellcrank or temporarily
incorporate certain flap limitations.

How Does the Revision to 14 CFR Part 39 Affect This Proposed AD?

    On July 10, 2002, we 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 altered products,
special flight permits, and alternative methods of compliance. 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.

Costs of Compliance

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?

    For the proposed actions retained from AD 2003-21-04, and the
addition of all bellcranks to the applicability, we estimate the
following costs to do this proposed inspection:

----------------------------------------------------------------------------------------------------------------
                                                             Total cost
             Labor cost                    Parts cost           per           Total cost on  U.S. operators
                                                              airplane
----------------------------------------------------------------------------------------------------------------
2 workhours x $65 per hour = $130..  No cost for parts....         $130  $130 x 1,300 for = $169,000.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements of
the right inboard forward flap bellcrank (P/N 2622311-7, alternate P/N
2622311-16) that would be required based on the results of this
proposed inspection. We have no way of determining the number of
airplanes that may need this replacement:

----------------------------------------------------------------------------------------------------------------
                   Labor cost                      Parts cost               Total cost  per airplane
----------------------------------------------------------------------------------------------------------------
3 workhours x $65 per hour = $195...............       $1,845  $195 + $1,845 = $2,040.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements of
the left inboard forward flap bellcrank (P/N 2622281-1) that would be
required based on the results of this proposed inspection. We have no
way of determining the number of airplanes that may need this
replacement:

----------------------------------------------------------------------------------------------------------------
                   Labor cost                      Parts cost               Total cost  per airplane
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 per hour = $65.................       $1,201  $65 + $1,201 = $1,266.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements of
the right inboard aft flap bellcrank (P/N 2622267-8) that would be
required based on the results of this proposed inspection. We have no
way of determining the number of airplanes that may need this
replacement:

----------------------------------------------------------------------------------------------------------------
                   Labor cost                      Parts cost               Total cost  per airplane
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 per hour = $65.................       $1,273  $65 + $1,273 = $1,338.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements of
the left inboard aft flap bellcrank (P/N 2622267-7) that would be
required based on the results of this proposed inspection. We have no
way of determining the number of airplanes that may need this
replacement:

[[Page 10643]]



----------------------------------------------------------------------------------------------------------------
                   Labor cost                      Parts cost               Total cost  per airplane
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 per hour = $65.................       $2,098  $65 + $2,098 = $2,163.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements of
the left outboard flap bellcrank (P/N 2622091-17) that would be
required based on the results of this proposed inspection. We have no
way of determining the number of airplanes that may need this
replacement:

----------------------------------------------------------------------------------------------------------------
                   Labor cost                      Parts cost               Total cost  per airplane
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 per hour = $65.................         $627  $65 + $627 = $692.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements of
the right outboard flap bellcrank (P/N 2622091-18) that would be
required based on the results of this proposed inspection. We have no
way of determining the number of airplanes that may need this
replacement:

----------------------------------------------------------------------------------------------------------------
                   Labor cost                      Parts cost               Total cost  per airplane
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 per hour = $65.................         $661  $65 + $661 = $726.
----------------------------------------------------------------------------------------------------------------

    For the proposed requirements from AD 2002-22-17 that you
repetitively inspect the inboard forward flap bellcranks for cracks,
eventually replace these bellcranks, and provides the option of
installing the new design flap bellcrank to increase the life limits
and terminate the repetitive inspections, we estimate the following
costs to do the proposed inspection:

----------------------------------------------------------------------------------------------------------------
                                                               Total cost
             Labor cost                     Parts cost            per          Total cost on  U.S. operators
                                                                airplane
----------------------------------------------------------------------------------------------------------------
1 workhour x $65 per hour = $65.....  No cost for parts.....          $65  $65 x 1,300 = $84,500.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any proposed replacements
using the same flap bellcrank (P/N 2622281-2, 2622281-12, 2692001-2, or
FAA-approved equivalent P/N) that will 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 $65 per hour = $195...  $1,793................  $195 + $1,793 = $1,988                    $1,988 x 1,300 = $2,584,400.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any proposed replacements
using the new flap bellcrank (P/N 2622311-7 or FAA-approved equivalent
P/N) that will 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 this proposed replacement with the new flap
bellcrank:

----------------------------------------------------------------------------------------------------------------
                   Labor cost                      Parts cost               Total cost  per airplane
----------------------------------------------------------------------------------------------------------------
3 workhours x $65 per hour = $195...............       $1,845  $195 + $1,845 = $2,040.
----------------------------------------------------------------------------------------------------------------

What Is the Difference Between the Cost Impact of This Proposed AD and
the Cost Impacts of AD 2003-21-04 and AD 2002-22-17?

    AD 2003-21-04 already established the inspection and replacement of
the right inboard forward flap bellcrank assembly on the affected
airplanes. Therefore, the replacement is already required through that
AD. The only difference in the cost impact on the public of this
proposed AD and AD 2003-21-04 is the additional cost for the inspection
of all other bellcranks, and, if necessary, replacement.
    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 AD and AD 2002-22-17 is the additional
$52 cost difference for the new flap bellcrank.

Regulatory Findings

Would This Proposed AD Impact Various Entities?

    We have determined that this proposed AD would not have federalism
implications under Executive Order

[[Page 10644]]

13132. This proposed AD 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.

Would This Proposed AD Involve a Significant Rule or Regulatory Action?

    For the reasons discussed above, I certify that this proposed AD:
    1. Is not a ``significant regulatory action'' under Executive Order
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); 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.
    We prepared a summary of the costs to comply with this proposed AD
and placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2002-CE-23-AD'' in your request.

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 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 both Airworthiness
Directive (AD) 2002-22-17, Amendment 39-12944, and AD 2003-21-04,
Amendment 39-13339; and by adding the following new AD:
Cessna Aircraft Company: Docket No. 2002-CE-23-AD

When Is the Last Date I Can Submit Comments on This Proposed AD?

    (a) We must receive comments on this proposed airworthiness
directive (AD) by May 17, 2004.

What Other ADs Are Affected By This Action?

    (b) This AD supersedes AD 2002-22-17 and AD 2003-21-04.

What Airplanes Are Affected by This AD?

    (c) This AD affects the following airplane models and serial
numbers that are certificated in any category:
    (1) Group 1 (retains the actions from AD 2003-21-04, and adds
all flap bellcranks to the applicability):

------------------------------------------------------------------------
                 Model                            Serial Numbers
------------------------------------------------------------------------
208....................................  20800001 through 20800369.
208B...................................  208B0001 through 208B1014,
                                          208B1017, 208B1018, 208B1020
                                          through 208B1024, 208B1026,
                                          and 208B1029 through 208B1033.
------------------------------------------------------------------------

    (2) Group 2 (retains the requirement of AD 2002-22-17 that you
repetitively inspect the inboard forward flap bellcranks for cracks,
eventually replace these bellcranks, and provides the option of
installing the new design flap bellcrank to increase the life limits
and terminate the repetitive inspections): Models 208 and 208B
airplanes, all serial numbers.

What Is the Unsafe Condition Presented in This AD?

    (d) The actions specified in this AD are intended to prevent
failure of any bellcrank due to cracks, deformation, or missing/
incomplete welds. This failure could lead to damage to the flap
system and surrounding structure and result in reduced or loss of
control of the airplane.

What Must I Do To Address This Problem for Group 1 Airplanes?

    (e) To address this problem for Group 1 airplanes, you must do
the following:

------------------------------------------------------------------------
           Actions                  Compliance            Procedures
------------------------------------------------------------------------
(1) Inspect the right        Within the next 25    Use a flashlight and
inboard forward flap          landings after        a mirror as
bellcrank assembly for        October 21, 2003      necessary to see if
cracks, deformation, and      (the effective date   welds (1), (4),
missing/incomplete welds.     of AD 2003-21-04).    (5), and (6) exist
The affected flap bellcrank   If landings are       and are at least
incorporates one of the       unknown, then you     0.06-inch thick
following part numbers (P/    may multiply hours    around the full
N):                           time-in-service       circumference of
(i) P/N 2622083-18;           (TIS) by 1.25. For    the shaft. These
(ii) P/N 2622281-2;           the purposes of       welds and the
(iii) P/N 2692001-2; or       this AD, you may      inspection
(iv) P/N 2622281-12.          substitute 20 hours   procedures are
                               TIS for 25 landings.  referenced in
                                                     Figure 1, details
                                                     A, B, and C; and
                                                     Views A-A and B-B
                                                     of Cessna Caravan
                                                     Service Bulletin
                                                     CAB03-11, Revision
                                                     1, dated September
                                                     24, 2003.
-----------------------------
(2) Inspect the left         Within the next 25    Use a flashlight and
inboard forward bellcrank     landings after the    a mirror as
for cracks, deformation,      effective date of     necessary to see if
and missing/incomplete        this AD. If           welds (1) through
welds. The affected flap      landings are          (4) exist and are
bellcrank incorporates one    unknown, then you     at least 0.06-inch
of the following part P/Ns:   may multiply hours    thick around the
(i) P/N 2622083-15; or        TIS by 1.25. For      full circumference
(ii) P/N 2622281-1.           the purposes of       of the shaft. These
                               this AD, you may      welds and the
                               substitute 20 hours   inspection
                               TIS for 25 landings.  procedures are
                                                     referenced in
                                                     Figure 2, details
                                                     A, B, and C; and
                                                     Views A-A and B-B
                                                     of Cessna Caravan
                                                     Service Bulletin
                                                     CAB03-11, Revision
                                                     1, dated September
                                                     24, 2003.
-----------------------------
(3) Inspect the inboard aft  Within the next 25    Use a flashlight and
bellcrank for cracks,         landings after the    a mirror as
deformation, and missing/     effective date of     necessary to see if
incomplete welds. The         this AD. If           welds (1), (2),
affected flap bellcrank       landings are          (4), and (5) exist
incorporates one of the       unknown, then you     and are at least
following P/Ns:               may multiply hours    0.05-inch thick
(i) P/N 2622267-1; or         TIS by 1.25. For      around the full
(ii) P/N 2622267-2;           the purposes of       circumference of
(iii) P/N 2622267-7;          this AD, you may      the shaft. These
(iv) P/N 2622267-8;           substitute 20 hours   welds and the
(v) P/N 2622083-1; or         TIS for 25 landings.  inspection
(vi) P/N 2622083-2.                                 procedures are
                                                     referenced in
                                                     Figure 3, details
                                                     A, B, and C; and
                                                     Views A-A and B-B
                                                     of Cessna Caravan
                                                     Service Bulletin
                                                     CAB03-11, Revision
                                                     1, dated September
                                                     24, 2003.
-----------------------------

[[Page 10645]]


(4) Inspect the outboard      Within the next 25    Use a flashlight
bellcrank for cracks,         landings after the    and a mirror as
deformation, and missing/     effective date of     necessary to see if
incomplete welds. The         this AD. If           welds (1) through
affected flap bellcrank       landings are          (4) exist and are
incorporates one of the       unknown, then you     at least 0.05-inch
following P/Ns:               may multiply hours    thick around the
(i) P/N 2622091-1; or         TIS by 1.25. For      full circumference
(ii) P/N 2622091-2;           the purposes of       of the shaft. These
(iii) P/N 2622091-9;          this AD, you may      welds and the
(iv) P/N 2622091-10;          substitute 20 hours   inspection
(v) P/N 2622091-17; or        TIS for 25 landings.  procedures are
(iv) P/N 2622091-18.                                referenced in
                                                     Figure 4, details
                                                     A, B, and C; and
                                                     Views A-A and B-B
                                                     of Cessna Caravan
                                                     Service Bulletin
                                                     CAB03-11, Revision
                                                     1, dated September
                                                     24, 2003.
-----------------------------
(5) If you find cracks,       Replace or do the     Replacement: Use
deformation, or missing/      flap prohibition      the Accomplishment
incomplete welds during the   actions before        Instructions of
inspection required by        further flight        Cessna Caravan
paragraphs (e)(1) through     after the             Service Bulletin
(e)(4) of this AD, then do    inspection required   No.: CAB02-12,
one of the following:         in paragraphs         Revision 1, dated
(i) Replace the bellcrank     (e)(1) through        January 27, 2003,
with a new bellcrank; or      (e)(4) of this AD.    and the
(ii) Prohibit the use of      If you choose the     Accomplishment
flaps through the actions     flap prohibition,     Instructions of
of paragraph (g) of this      you must have the     Cessna Caravan
AD.                           replacement done      Service Kit No.:
                               within 200 hours      SK208-148A, dated
                               TIS after the         January 27, 2003,
                               inspection required   or refer to the
                               by paragraphs         Maintenance Manual,
                               (e)(1) through        Chapter 27, Flap
                               (e)(4) of this AD.    System--Maintenance
                               After the new flap    Practices, for
                               bellcrank is          bellcrank removal
                               installed, the        and installation
                               Temporary Revision    procedures
                               208PHTR02, dated      Flap Prohibition:
                               September 23, 2003,   Use the information
                               should be removed.    in the Temporary
                                                     Revision 208PHTR02,
                                                     dated September 23,
                                                     2003. The action is
                                                     referenced in
                                                     Cessna Caravan
                                                     Service Bulletin
                                                     CAB03-11, Revision
                                                     1, dated September
                                                     24, 2003.
------------------------------------------------------------------------

What Must I Do To Address This Problem for Group 2 Airplanes?

    (f) To address this problem for Group 2 airplanes, you must do
the following:

------------------------------------------------------------------------
           Actions                  Compliance            Procedures
------------------------------------------------------------------------
(1) Repetitive Inspections:   Initially inspect     Follow the
Inspect, using eddy current   upon the              Inspection
methods, any inboard          accumulation of       Instructions of
forward flap bellcrank P/N    4,000 landings on     Cessna Caravan
2622281-2, 2622281-12,        the bellcrank or      Service Bulletin
2692001-2, or FAA-approved    within the next 250   No.: CAB02-1, dated
equivalent P/N) for cracks.   landings after        February 11, 2002,
                               December 31, 2002     and the applicable
                               (the effective date   maintenance manual.
                               of AD 2002-22-17),
                               whichever occurs
                               later. Repetitively
                               inspect thereafter
                               at every 500
                               landings until
                               7,000 landings are
                               accumulated at
                               which time you must
                               replace as required
                               in paragraphs
                               (f)(2) and (f)(3)
                               of this AD. No
                               repetitive
                               inspections are
                               required when a P/N
                               2622311-7 (or FAA-
                               approved equivalent
                               P/N) inboard
                               forward flap
                               bellcrank is
                               installed.
-----------------------------
(2) Initial Replacement:      If cracks are         Replacement: For
Replace any inboard forward   found, replace or     flap bellcrank (P/N
flap bellcrank (P/N 2622281-  do the flap           2622281-2, 2622281-
2, 2622281-12, 2692001-2,     prohibition actions   12, 2692001-2, or
or FAA-approved equivalent    before further        FAA-approved
P/N) with either:             flight after the      equivalent P/N):
(i) the same flap bellcrank   inspection required   Follow the
(P/N 2622281-2, 2622281-12,   in paragraphs         Instructions of
2692001-2, or FAA-approved    (f)(1) of this AD.    Cessna Caravan
equivalent P/N); or           If you choose the     Service Bulletin
(ii) a new flap bellcrank     flap prohibition,     No.: CAB02-1, dated
(P/N 2622311-7 or FAA-        you must have the     February 11, 2002,
approved equivalent P/N).     replacement done      and the applicable
                               within 200 hours      maintenance manual.
                               TIS after the         For new flap
                               inspection required   bellcrank (P/N
                               by paragraphs         2622311-7 or FAA-
                               (f)(1) of this AD.    approved equivalent
                               After the new flap    P/N): Follow the
                               bellcrank is          Accomplishment
                               installed, the        Instructions of
                               Temporary Revision    Cessna Caravan
                               208PHTR02, dated      Service Bulletin
                               September 23, 2003,   No.: CAB02-12,
                               should be removed.    Revision 1, dated
                               If cracks are not     January 27, 2003,
                               found, initially      and the
                               replace at            Accomplishment
                               whichever occurs      Instructions of
                               later: Upon the       Cessna Caravan
                               accumulation of       Service Kit No.
                               7,000 landings on     SK203-148A, dated
                               the bellcrank or      January 27, 2003.
                               within the next 75   Flap Prohibition:
                               landings after        Use the information
                               December 31, 2002     in the Temporary
                               (the effective date   Revision 208PHTR02,
                               of AD 2002-22-17).    dated September 23,
                                                     2003.
-----------------------------

[[Page 10646]]


(3) Life Limits (Repetitive   Replace at the       Use the service
Replacements):                applicable            information
(i) The life limit for the    referenced life       referenced in
inboard forward flap          limits.               paragraph (f)(2) of
bellcranks (P/N 2622281-2,                          this AD.
2622281-12, 2692001-2, or
FAA-approved equivalent P/
N) is 7,000 landings.
Repetitive inspections
every 500 landings begin at
4,000 landings (see
paragraph (f)(1) of this
AD).
(ii) The life limit for the
inboard forward flap
bellcranks (P/N 26222311-7
or FAA-approved equivalent
P/N) is 40,000 landings. No
repetitive inspections are
required on these
bellcranks.
------------------------------------------------------------------------


    Note 1: Inboard forward flap bellcranks (P/N 2622281-2, 2622281-
12, or 2692001-2) with 7,000 landings or more do not have to be
replaced until 75 landings after December 31, 2002 (the effective
date of AD 2002-22-17), unless found cracked.


    Note 2: The compliance times of this AD are presented in
landings instead of hours TIS. If the number of landings is unknown,
hours TIS may be used by multiplying the number of hours TIS by
1.25.

What Are the Actions I Must Do if I Choose the Flap Prohibition Option?

    (g) Insert Temporary Revision, 208PHTR02, dated September 23,
2003, into the applicable pilot's operating handbook and FAA-
approved airplane flight manual. The owner/operator holding at least
a private pilot certificate as authorized by Sec.  43.7 of the
Federal Aviation Regulations (14 CFR 43.7) may incorporate this
information into the AFM. Make an entry into the aircraft records
showing compliance with this portion of the AD in accordance with
section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
    (1) This procedure applies to Cessna Models 208 and 208B
landplanes. For other FAA-approved aircraft configurations (for
example, amphibian, floatplanes, and so forth), you must operate
with flaps up per the appropriate airplane flight manual supplement.
    (2) This procedure allows for applicable deviation from the
Master Minimum Equipment List (MMEL) for these airplanes until the
flap bell crank is replaced. The applicable MMEL requirements go
back into effect at the time of flap bell crank replacement.

May I Request an Alternative Method of Compliance?

    (h) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.13. Send your request to the Manager, Wichita Aircraft
Certification Office (ACO), FAA. For information on any already
approved alternative methods of compliance, contact Paul Nguyen,
Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: 316-946-4125; facsimile: 816-946-
4107.
    (i) Alternative methods of compliance approved under AD 2002-22-
17 and AD 2003-21-04 are not approved for this AD.

May I Get Copies of the Documents Referenced in This AD?

    (j) You may get copies of the documents referenced in this AD
from Cessna Aircraft Company, Product Support, P.O. Box 7706,
Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316)
942-9006. You may view these documents at FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106.

    Issued in Kansas City, Missouri, on March 2, 2004.
Sandra J. Campbell,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-5130 Filed 3-5-04; 8:45 am]

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