[Federal Register: November 12, 2002 (Volume 67, Number 218)]
[Rules and Regulations]
[Page 68508-68510]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12no02-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-CE-23-AD; Amendment 39-12944; AD 2002-22-17]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Models 208 and
208B Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to all Cessna Aircraft Company (Cessna) Models 208 and 208B
airplanes. This AD requires you to repetitively inspect the inboard
forward flap bellcranks for cracks or replace bellcranks depending on
the amount of usage. This AD is the result of Cessna re-evaluating the
bellcrank life limit analysis and determining that the original
estimate is too high. The actions specified by this 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: This AD becomes effective on December 31, 2002.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the regulations as of
December 31, 2002.
ADDRESSES: You may get the service information 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 this information at the Federal Aviation Administration (FAA),
Central Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2002-CE-23-AD, 901 Locust, Room 506, Kansas City, Missouri 64106;
or at the Office of the Federal Register, 800 North Capitol Street, NW,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Paul Nguyen, Aerospace Engineer, FAA,
Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: 316-946-4125; facsimile: 816-946-4407.
SUPPLEMENTARY INFORMATION:
Discussion
What Events Have Caused This AD?
A search by the FAA of the service difficulty database has revealed
10 cracked bellcrank incidents on Cessna Models 208 and 208B airplanes.
As a result, Cessna has re-evaluated the bellcrank life limit analysis
and determined 7,000 landings is more accurate than the original
estimate of 9,000 landings. Cessna has revised the Models 208 and 208B
Maintenance Manual and developed a service bulletin to notify the
public that the inboard forward flap bellcrank life limit has been
reduced to 7,000 landings. Since some Model 208 airplanes have exceeded
7,000 landings, we have determined that an AD is necessary to require
replacement of the bellcrank in those airplanes.
What Is the Potential Impact if FAA Took No Action?
If not detected and corrected, a cracked bellcrank could fail. Such
failure could lead to damage to the flap system and surrounding
structure and result in reduced or loss of control of the airplane.
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 June
26, 2002 (67 FR 43056). The NPRM proposed to repetitively inspect the
inboard forward flap bellcranks for cracks or replace bellcranks
depending on the amount of usage and reduce the life limits of the
bellcranks from 9,000 landings to 7,000 landings.
Was the Public Invited to Comment?
The FAA encouraged interested persons to participate in the making
of this amendment. The following presents the comments received on the
proposal and FAA's response to each comment:
[[Page 68509]]
Comment Issue 1: Which Flap Bellcrank(s) Does the Proposed AD Affect?
What Is the Commenter's Concern?
A commenter asks if the proposed AD only affects the right inboard
flap bellcrank or the right and the left flap inboard bellcranks?
What Is FAA's Response to the Concern?
The Cessna Model 208 airplane has only one inboard flap bellcrank
assembly and it is located on the right hand side of the aircraft. This
flap bellcrank assembly controls both the right and left flaps.
Therefore, inspection of the only flap bellcrank assembly in accordance
with the Cessna Service Bulletin CABO2-1 will comply with the proposed
AD.
We have not changed the final rule as a result of this comment.
Comment Issue 2: The Limits in the Service Information Are Sufficient
and the Proposed AD Is Not Warranted.
What is the Commenter's Concern?
A commenter states that Cessna has revised their airworthiness
limitations to reflect what the NPRM proposes. The limitations now
include a 7,000 landings limit, with repetitive inspections every 500
landings until 7,000 landings are accumulated. For this reason, the
commenter recommends that we withdraw the NPRM.
What is FAA's Response to the Concern?
We disagree. Airworthiness Directives that apply more restrictive
limits to products are issued when the current limits contribute to an
unsafe condition. The AD establishes a deadline to come into compliance
with the new life limits.
We have not changed the final rule as a result of this comment.
FAA's Determination
What Is FAA's Final Determination on This Issue?
We carefully reviewed all available information related to the
subject presented above and determined that air safety and the public
interest require the adoption of the rule as proposed except for the
changes discussed above and minor editorial questions. We have
determined that these changes and minor corrections:
--Provide the intent that was proposed in the NPRM for correcting the
unsafe condition; and
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
Cost Impact
How Many Airplanes Does This AD Impact?
We estimate that this AD affects 1,300 airplanes in the U.S.
registry.
What Is the Cost Impact of This AD on Owners/Operators of the Affected
Airplanes?
We estimate the following costs to accomplish the inspection:
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Total Cost on U.S.
Labor Cost Parts Cost Total Cost Per Airplane Operators
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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 that would be required based on the reduced life limits:
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Total Cost on U.S.
Labor Cost Parts Cost Total Cost Per Airplane Operators
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3 workhours x $60 per hour = $180 $1,793................... $180 + $1,793 = $1,973.. $1,973 x $1,300 =
$2,564,900
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Regulatory Impact
Does This AD Impact Various Entities?
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
Does This AD Involve a Significant Rule or Regulatory Action?
For the reasons discussed above, I certify that this 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) 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 final evaluation prepared for this
action is contained 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, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 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 adding a new AD to read as follows:
2002-22-17 Cessna Aircraft Company: Amendment 39-12944; Docket No.
2002-CE-23-AD.
(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:
[[Page 68510]]
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Actions Compliance Procedures
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(1) Inspect, using eddy Initially inspect In accordance with
current inspection, the upon the the Inspection
inboard forward flap accumulation of Instructions of
bellcrank for cracks. 4,000 landings on Cessna Service
the bellcrank or Bulletin No. CAB02-
within the next 250 1, dated February
landings after 11, 2002, and the
December 31, 2002 applicable
(the effective date maintenance manual.
of this AD),
whichever occurs
later. Repetitively
inspect thereafter
at every 500
landings until
7,000 landings are
accumulated.
(2) Replace the inboard Prior to further In accordance with
forward flap bellcrank. flight when cracks the Inspection
are found; and upon Instructions of
the accumulation of Cessna Service
7,000 landings or Bulletin No. CAB02-
within the next 75 1, dated February
landings after 11, 2002, and the
December 31, 2002 applicable
(the effective date maintenance manual.
of this AD),
whichever occurs
later.
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Note 1: Inboard forward flap bellcranks with 7,000 landings or
more do not have to be replaced until 75 landings after the
effective date of this AD.
Note 2: The compliance times of this AD are presented in
landings instead of hours. 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? You may use an
alternative method of compliance or adjust the compliance time if:
(1) Your alternative method of compliance provides an equivalent
level of safety; and
(2) The Manager, Wichita Aircraft Certification Office (ACO),
approves your alternative. Submit your request through an FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Wichita ACO.
Note 3: This AD applies to each airplane identified in paragraph
(a) of this AD, regardless of whether it has been modified, altered,
or repaired in the area subject to the requirements of this AD. For
airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the owner/
operator must request approval for an alternative method of
compliance in accordance with paragraph (e) of this AD. The request
should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD;
and, if you have not eliminated the unsafe condition, specific
actions you propose to address it.
(f) Where can I get information about any already-approved
alternative methods of compliance? Contact Paul Nguyen, Aerospace
Engineer, FAA, Aircraft Certification Office, 1801 Airport Road,
Room 100, Wichita, Kansas 67209; telephone: 316-946-4125; facsimile:
816-946-4407.
(g) What if I need to fly the airplane to another location to
comply with this AD? The FAA can issue a special flight permit under
Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate your airplane to a location where
you can accomplish the requirements of this AD.
(h) Are any service bulletins incorporated into this AD by
reference? Actions required by this AD must be done in accordance
with Cessna Service Bulletin No. CAB02-1, dated February 11, 2002.
The Director of the Federal Register approved this incorporation by
reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may get
copies from Cessna Aircraft Company, Product Support, PO Box 7706,
Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316)
942-9006. You may view copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri,
or at the Office of the Federal Register, 800 North Capitol Street,
NW, suite 700, Washington, DC.
(i) When does this amendment become effective? This amendment
becomes effective on December 31, 2002.
Issued in Kansas City, Missouri, on October 31, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-28408 Filed 11-8-02; 8:45 am]
BILLING CODE 4910-13-P