[Federal Register Volume 68, Number 144 (Monday, July 28, 2003)]
[Proposed Rules]
[Pages 44252-44255]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-19059]


=======================================================================
-----------------------------------------------------------------------

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).

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

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: [email protected]. 
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

[[Page 44253]]

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:

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

    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.................
------------------------------------------------------------------------

    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

[[Page 44254]]

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:

Cessna Aircraft Company: Docket No. 2002-CE-23-AD; Revises AD 2002-
22-17, Amendment 39-*****.

    (a) What airplanes are affected by this AD? This AD affects 
Models 208 and 208B airplanes, all serial numbers, that are 
certificated in any category.
    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the airplanes identified in paragraph (a) of this AD must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to detect, correct, and prevent 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.
    (d) What actions must I accomplish to address this problem? To 
address this problem, you must accomplish the following:

----------------------------------------------------------------------------------------------------------------
               Actions                             Compliance                            Procedures
----------------------------------------------------------------------------------------------------------------
(1) Repetitive Inspections: Inspect,  Initially inspect upon the            In accordance with the Inspection
 using eddy current method, any        accumulation of 4,000 landings on     Instructions of Cessna Caravan
 inboard forward flap bellcrank        the bellcrank or within the next      Service Bulletin No.: CAB02-1,
 (part number (P/N) 2622281-2,         250 landings after the effective      dated February 11, 2002, and the
 2622281-12, 2692001-2, or FAA-        date of this AD, whichever occurs     applicable maintenance manual.
 approved equivalent (P/N) for         later. Repetitively inspect
 cracks.                               thereafter at every 500 landings
                                       until 7,000 landings are
                                       accumulated at which time you must
                                       replace as required in paragraphs
                                       (d)(2) and (d)(3) of this AD.
-------------------------------------
(2) Initial Replacement: Replace any  Must be replaced prior to further     For flap bellcrank (P/N 2622281-2,
 inboard forward flap bellcrank (P/N   flight if cracks are found. If        2622281-12, 2692001-2, or FAA-
 2622281-2, 2622281-12, 2692001-2,     cracks are not found, initially       approved equivalent P/N): In
 or FAA-approved equivalent P/N)       replace at whichever occurs later;    accordance with the Inspection
 with either:                          upon the accumulation of 7,000        Instructions of Cessna Caravan
(i) the same flap bellcrank (P/N       landings on the bellcrank or within   Service Bulletin No.: CAB02-1,
 2622281-2, 2622281-12, 2692001-2,     the next 75 landings after the        dated February 11, 2002, and the
 or FAA-approved equivalent P/N); or   effective date of this AD.            applicable maintenance manual. For
(ii) a new flap bellcrank (P/N                                               new flap bellcrank (P/N 2622311-7
 2622311-7 or FAA-approved                                                   or FAA-approved equivalent P/N): In
 equivalent P/N).                                                            accordance with the Accomplishment
                                                                             Instructions of Cessna Caravan
                                                                             Service Bulletin No.: CAB02-12,
                                                                             Revision 1, dated January 27, 2003,
                                                                             and the Accomplishment Instructions
                                                                             of Cessna Caravan Service Kit No.:
                                                                             SK208-148A, dated January 27, 2003.
-------------------------------------
(3) Life Limits (Repetitive           Replace at the applicable referenced  Use the service information
 Replacements):                        life limits.                          referenced in paragraph (d)(2) of
(i) The life limit for the inboard                                           this AD.
 forward flap bellcranks (P/N
 2622281-2, 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 (d)(1) of this AD.
(ii) The life limit for the inboard
 forward flap bellcranks (P/N
 2622311-7 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 the effective date of this AD.



[[Page 44255]]


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

    (e) Can I comply with this AD in any other way?
    (1) To use an alternative method of compliance or adjust the 
compliance time, follow the procedures in 14 CFR 39.19. Send these 
requests to the Manager, Wichita Aircraft Certification Office 
(ACO). 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: 816-946-4407.
    (2) Alternative methods of compliance approved in accordance 
with AD 2002-22-17, which is revised by this AD, are not approved as 
alternative methods of compliance with this AD.
    (f) How do I get copies of the documents referenced in this AD? 
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.
    (g) Does this AD action affect any existing AD actions? This 
amendment revises AD 2002-22-17, Amendment 39-12944.

    Issued in Kansas City, Missouri, on July 21, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-19059 Filed 7-25-03; 8:45 am]
BILLING CODE 4910-13-P