[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]


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

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).

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

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:

----------------------------------------------------------------------------------------------------------------
                                                               Total cost per
            Labor cost                    Parts cost              airplane        Total cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
8 workhours x $60 per hour =       None....................               $480  $480 x 370 = $177,600
 $480..
----------------------------------------------------------------------------------------------------------------

    For Model 441 airplanes, we estimate the following costs to 
accomplish the proposed replacements:

----------------------------------------------------------------------------------------------------------------
                            Labor cost                                 Parts cost       Total cost per airplane
----------------------------------------------------------------------------------------------------------------
8 workhours x $60 per hour = $480................................            $13,101    $480 + $13,101 = $13,581
----------------------------------------------------------------------------------------------------------------

    For Model F406 airplanes, we estimate the following costs to 
accomplish the proposed replacements:

[[Page 64570]]



----------------------------------------------------------------------------------------------------------------
                            Labor cost                                 Parts cost       Total cost per airplane
----------------------------------------------------------------------------------------------------------------
8 workhours x $60 per hour = $480................................            $7,558.      $480 + $7,558 = $8,038
----------------------------------------------------------------------------------------------------------------

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:

------------------------------------------------------------------------
                   Model                             Serial Nos.
------------------------------------------------------------------------
441.......................................  0001 through 0362 and 698
F406......................................  0001 through 0089
------------------------------------------------------------------------

    (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:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(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.
-----------------------------
(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.
-----------------------------

[[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.
-----------------------------
(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.
-----------------------------
(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.
------------------------------------------------------------------------

    (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