[Federal Register Volume 67, Number 203 (Monday, October 21, 2002)]
[Proposed Rules]
[Pages 64568-64571]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-26662]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-CE-18-AD]
RIN 2120-AA64
Airworthiness Directives; Cessna Aircraft Company Models 441 and
F406 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede Airworthiness Directive
(AD) 2002-09-13, which currently requires a one-time inspection of the
fuel boost pump wiring inside and outside the boost pump reservoir and
repair or replacement of the wiring as necessary on certain Cessna
Aircraft Company (Cessna) Model 441 airplanes. AD 2002-09-13 resulted
from several reports of chafing and/or arcing of the fuel boost pump
wiring inside and outside the fuel pump reservoir. This proposed AD
would retain the actions required in AD 2002-09-13, make the one-time
inspection repetitive, require the inspection and possible replacement
of the wire harness, lead wires and fuel boost pump on Model F406
airplanes, and require eventual installation of an improved design wire
harness and fuel boost pump as terminating action for the repetitive
inspections. The actions specified by this proposed AD are intended to
detect, correct, and prevent chafing and/or arcing fuel boost pump
wiring, which could result in arcing within the wing fuel storage
system. Such a condition could lead to ignition of explosive vapor
within the fuel storage system.
DATES: The Federal Aviation Administration (FAA) must receive any
comments on this proposed rule on or before December 30, 2002.
ADDRESSES: Submit comments to FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 2002-CE-18-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-18-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, P.O. 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: Robert Adamson, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room
100, Wichita, Kansas 67209; telephone: 316-946-4145; facsimile: 316-
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 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
[[Page 64569]]
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-18-AD.'' We will date stamp and
mail the postcard back to you.
Discussion
Has FAA Taken Any Action to This Point?
Reports of chafing and/or arcing of the fuel boost pump wiring
inside the fuel pump reservoir that supplies fuel to each engine on
Cessna Model 441 airplanes caused us to issue AD 2002-09-13, Amendment
39-12746 (67 FR 31117, May 9, 2002). AD 2002-09-13 requires you to: (1)
Do a one-time inspection of the electrical wiring going to the fuel
boost pump reservoir and the boost pump wiring inside the reservoir for
chafing or damage, and (2) repair or replace the wiring as necessary.
These actions are required in accordance with Cessna Conquest
Service Bulletin No.: CQB02-1R1, Revision 1, dated April 22, 2002.
What Has Happened Since AD 2002-09-13 To Initiate This Action?
Further analysis of this situation reveals that:
--The actions required by AD 2002-09-13 should also apply to Model
F406 airplanes;
--The inspection should be repetitive; and
--Improved design wire harnesses and fuel boost pumps should
eventually be installed as terminating action for the repetitive
inspections.
Has the Manufacturer Issued Service Information That Pertains to the
Model F406 Airplanes?
Cessna has issued Caravan Service Bulletin No.: CAB02-8, dated June
3, 2002, Fuel Boost Pump Wiring Harness Inspection/Modification. This
service bulletin affects the Model F406 airplane, a model of similar
type design as the Model 441 airplane.
Cessna has also replaced Conquest Service Bulletin No.: CQB02-1,
Revision 1, with Conquest Service Bulletin No.: CQB02-1, Revision 2,
dated October 7, 2002.
Service Bulletins Numbers: CAB02-8 and CQB02-1, Revision 2, also
specify and include procedures for installing improved design wire
harnesses and fuel boost pumps (as a terminating action for the
repetitive inspections).
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 441 and F406 airplanes of the same type
design;
--The actions of AD 2002-09-13 should be repetitive and the
improved design parts eventually incorporated; and
--AD action should be taken in order to correct this unsafe
condition.
What Would This Proposed AD Require?
This proposed AD would supersede AD 2002-09-13 with a new AD that
would require repetitive inspections of the Models 441 and F406
airplanes fuel boost pump wiring inside and outside the boost pump
reservoir for chafing or damage and replacement of the wiring and (for
the Model F406) fuel boost pump, as necessary, and require eventual
installation of an improved design wire harness and fuel boost pump as
terminating action for the repetitive inspections.
How Would This Action Relate to the FAA's Aging Commuter-Class Aircraft
Policy?
The FAA's aging commuter aircraft policy briefly states that when a
modification exists that could eliminate or reduce the number of
required critical inspections, the modification should be incorporated.
This policy is based on the FAA's determination that reliance on
critical repetitive inspections on airplanes utilized in commuter
service carries an unnecessary safety risk when a design change exists
that could eliminate or, in certain instances, reduce the number of
those critical inspections. In determining what inspections are
critical, the FAA considers (1) the safety consequences of the airplane
if the known problem is not detected by the inspection; (2) the
reliability of the inspection such as the probability of not detecting
the known problem; (3) whether the inspection area is difficult to
access; and (4) the possibility of damage to an adjacent structure as a
result of the problem.
The alternative to replacing the fuel boost pump wiring and fuel
boost pump would be to repetitively inspect this area for the life of
the airplane. Therefore, FAA has determined that the improved design
wire harness and fuel boost pump should be incorporated in all affected
airplanes.
Cost Impact
How Many Airplanes Would This Proposed AD Impact?
We estimate that this proposed AD affects 370 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
Labor cost Parts cost airplane Total cost on U.S. operators
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8 workhours x $60 per hour = None.................... $480 $480 x 370 = $177,600
$480..
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For Model 441 airplanes, we estimate the following costs to
accomplish the proposed replacements:
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Labor cost Parts cost Total cost per airplane
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8 workhours x $60 per hour = $480................................ $13,101 $480 + $13,101 = $13,581
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For Model F406 airplanes, we estimate the following costs to
accomplish the proposed replacements:
[[Page 64570]]
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Labor cost Parts cost Total cost per airplane
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8 workhours x $60 per hour = $480................................ $7,558. $480 + $7,558 = $8,038
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Compliance Time of This Proposed AD
Why Is the Compliance Time of This Proposed AD Presented in Both Hours
Time-In-Service (TIS) and Calendar Time?
The initial compliance time of this proposed AD is presented in
both hours TIS (25 hours) and calendar time (60 days). Because the
affected airplanes are used in general aviation operations, some
operators may accumulate 25 hours TIS on the airplane in a week while
others may not accumulate 25 hours TIS in a year. Although the
condition specified by this proposed AD is only unsafe during airplane
operation, the condition could exist on an airplane with 500 hours TIS
or 2,000 hours TIS. We have determined that the dual compliance time:
--Gives all owners/operators of the affected airplanes adequate time to
schedule and do the actions in this proposed AD; and
--ensures that the unsafe condition referenced in this proposed AD will
be corrected within a reasonable time period without inadvertently
grounding any of the affected airplanes.
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)
2002-09-13, Amendment 39-12746 (67 FR 31117, May 9, 2002), and by
adding a new AD to read as follows:
Cessna Aircraft Company: Docket No. 2002-CE-18-AD; Supersedes AD
2002-09-13, Amendment 39-12746.
(a) What airplanes are affected by this AD? This AD applies to
the following airplane models and serial numbers that are
certificated in any category:
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Model Serial Nos.
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441....................................... 0001 through 0362 and 698
F406...................................... 0001 through 0089
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(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 chafing and/or
arcing fuel boost pump wiring, which could result in arcing within
the wing fuel system. Such a condition could lead to ignition of
explosive vapor within the fuel storage system.
(d) What actions must I accomplish to address this problem? To
address this problem, you must accomplish the following:
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Actions Compliance Procedures
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(1) For Model 441 airplanes: Initially at In accordance with
Inspect the part number (P/ whichever occurs Cessna Conquest
N) 5718106-1 wire harness first, unless Service Bulletin
and fuel boost pump lead already No.: CQB02-1,
wires for chafing or damage. accomplished: Revision 2, dated
Within the next 25 October 7, 2002.
hours time-in-
service (TIS) or 60
days after May 31,
2002 (the effective
date of AD 2002-09-
13); and
repetitively
thereafter at
intervals not to
exceed 200 hours
TIS.
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(2) For Model F406 Initially at In accordance with
airplanes: Inspect the P/N whichever occurs Cessna Caravan
5718106-4 wire harness and first, unless Service Bulletin
fuel boost pump lead wires already No.: CAB02-8, dated
for chafing or damage. accomplished: June 3, 2002.
Within the next 25
hours TIS after the
effective date of
this AD or 60 days
after the effective
date of this AD;
and repetitively
thereafter at
intervals not to
exceed 200 hours
TIS.
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[[Page 64571]]
(3) If chafing or damage is Before further For the Model 441
found during any inspection flight after any airplanes: In
required in paragraph inspection required accordance with
(d)(1) or (d)(2) of this in paragraphs Cessna Conquest
AD:. (d)(1) and (d)(2) Service Bulletin
(i) For the Model 441 of this AD in which No.: CQB02-1,
airplanes, replace the wire damage is found. If Revision 2, dated
harnesses, repair fuel improved design October 7, 2002.
boost pump lead wires, or wire harnesses and For the Model F406
replace the fuel boost fuel boost pumps airplanes: In
pump, as applicable.. are not installed, accordance with
(ii) For the Model F406 continue to inspect Cessna Caravan
airplanes, repair or as specified in Service Bulletin
replace the wire harnesses paragraph (d)(1) or No.: CAB02-8, dated
or lead wires, or fuel (d)(2) of this AD June 3, 2002.
boost pump, as applicable. until these
improved design
parts are installed.
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(4) Perform the following Within the next 400 For the Model 441
installations:. hours TIS after the airplanes: In
(i) For the Model 441 effective date of accordance with
airplanes: Install improved this AD, unless Cessna Conquest
design fuel boost pump (P/N already Service Bulletin
1C12-17 or FAA-approved accomplished. No.: CQB02-1,
equivalent P/N) and Revision 2, dated
improved design wire October 7, 2002.
harness (P/N 5718106-6 or For the Model F406
FAA-approved equivalent P/ airplanes: In
N). Installing both accordance with
improved part numbers in Cessna Caravan
each wing tank terminates Service Bulletin
the repetitive inspection No.: CAB02-8, dated
requirements of paragraph June 3, 2002.
(d)(1) of this AD..
(ii) For the Model F406
airplanes: Install improved
design fuel boost pump (P/N
1C12-17 or FAA-approved
equivalent P/N) and
improved design wire
harness (P/N 406 28 01 or
FAA-approved equivalent P/
N). Installing both
improved part numbers in
each wing tank terminates
the repetitive inspection
requirements of paragraph
(d)(2) of this AD.
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(5) Only install improved As of the effective Not applicable.
design wire harnesses and date of this AD.
fuel boost pumps as
specified in paragraphs
(d)(4)(i) and (d)(4)(ii) of
this AD.
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(e) Can I comply with this AD in any other way?
(1) You may use an alternative method of compliance or adjust
the compliance time if:
(i) Your alternative method of compliance provides an equivalent
level of safety; and
(ii) 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.
(2) Alternative methods of compliance approved in accordance
with AD 2002-09-13, which is superseded by this AD, are approved as
alternative methods of compliance for all inspection requirements of
this AD. Regardless, you still must comply with the replacement
requirements of this AD.
Note: 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 Robert Adamson, Aerospace
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport
Road, Room 100, Wichita, Kansas 67209; telephone: 316-946-4145;
facsimile: 316-946-4407.
(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
sections 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) 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.
(i) Does this AD action affect any existing AD actions? This
amendment supersedes AD 2002-09-13, Amendment 39-12746.
Issued in Kansas City, Missouri, on October 15, 2002.
Dorenda D. Baker,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 02-26662 Filed 10-18-02; 8:45 am]
BILLING CODE 4910-13-P