[Federal Register Volume 69, Number 7 (Monday, January 12, 2004)]
[Rules and Regulations]
[Pages 1657-1659]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-475]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-CE-18-AD; Amendment 39-13406; AD 2003-09-09 R1]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Models 441 and 
F406 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule

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SUMMARY: This amendment revises Airworthiness Directive (AD) 2003-09-
09, which applies to certain Cessna Aircraft Company (Cessna) Models 
441 and F406 airplanes. AD 2003-09-09 currently requires repetitively 
inspecting the fuel boost pump wiring inside and outside the boost pump 
reservoir and repair or replacement of the wiring as necessary. AD 
2003-09-09 also requires eventual installation of an improved design 
wire harness and fuel boost pump as terminating action for the 
repetitive inspections. The way the compliance time is currently 
written puts certain airplane owners/operators in non-compliance with 
the AD. Also, the terminating action for the repetitive inspections did 
not provide the option of installing the protective sleeving 
modification for boost pump lead wires. This document clarifies and 
corrects the compliance time and provides the option of installing the 
protective sleeving modification for boost pump lead wires. The actions 
specified by this AD are intended to detect, correct, and prevent 
chafing and/or arcing of the fuel boost pump wiring, which could result 
in arcing within the wing fuel storage system. This condition could 
lead to ignition of explosive vapor within the fuel storage system.

DATES: This AD becomes effective on January 22, 2004.
    The Director of the Federal Register previously approved the 
incorporation by reference of certain publications listed in the 
regulations as of June 24, 2003 (68 FR 23186, May 1, 2003).

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-18-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: Robert Adamson, Aerospace Engineer, 
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 
100, Wichita, Kansas 67209; telephone: 316-946-4145; facsimile: 316-
946-4107.

SUPPLEMENTARY INFORMATION:

Discussion

What Prior AD Action Did FAA Take on This Subject?

    We issued AD 2003-09-09, Amendment 39-13138 (68 FR 23186, May 1, 
2003), in order to detect, correct, and prevent chafing and/or arcing 
of the fuel boost pump wiring on certain Cessna Models 441 and F406 
airplanes. This AD currently requires repetitively inspecting the fuel 
boost pump wiring inside and outside the boost pump reservoir and 
repair or replacement of the wiring as necessary, and requires eventual 
installation of an improved design wire harness and fuel boost pump as 
terminating action for the repetitive inspections. AD 2003-09-09 
superseded AD 2002-09-13, which required only a one-time inspection and 
repair or replacement of the wiring as necessary on Model 441 
airplanes.

What Has Happened To Necessitate Further AD Action?

    We established the compliance time of AD 2003-09-09 to coincide 
with the initial inspection of AD 2002-09-13. The compliance time is 
currently written as:

    ``Initially at whichever occurs first, unless already 
accomplished: Within the next 25 hours time-in-service (TIS) or 60 
days after May 31, 2002 (the effective date of AD 2002-09-13): 
Repetitively thereafter at intervals not to exceed 200 hours TIS.''

    The FAA has found that there are a few airplanes that have already 
accumulated more than 200 hours TIS after the last inspection required 
by AD-2002-09-13. The way the compliance time is currently written puts 
these airplane owners/operators in non-compliance with the AD.
    This was not FAA's intent. Our intent was to give every owner/
operator of the affected airplanes a grace period for accomplishing the 
AD without jeopardizing the safety of these airplanes.
    The option of installing the protective sleeving modification for 
boost pump lead wires is included in the service information. However, 
AD 2003-09-09 did not address this option. It is FAA's intent that the 
AD provide this option for the affected airplanes.
    Consequently, FAA sees a need to clarify and correct AD 2003-09-09 
to assure that every owner/operator of the affected airplanes is able 
to comply with the AD action.

Correction of Publication

What Is the Purpose of This Document?

    This document clarifies the intent of the compliance time of AD 
2003-09-09, adds the option of installing the protective sleeving 
modification, and adds the amendment to section 39.13 of the Federal 
Aviation Regulations (14 CFR 39.13).

Is It Necessary To Seek Public Input?

    Since this action only clarifies the intent of the compliance time 
and provides a compliance option, it has no adverse economic impact and 
imposes no additional burden on any person than would have been 
necessary to comply with AD 2003-09-09. Therefore, FAA has determined 
that prior notice and opportunity for public comment are unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 1658]]

Adoption of the Amendment

0
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

0
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]

0
2. FAA amends Sec.  39.13 by removing airworthiness Directive (AD) 
2003-09-09, Amendment 39-13138 (68 FR 23186, May 1, 2003), and by 
adding a new AD to read as follows:

2003-09-09 R1 Cessna Aircraft Company: Amendment 39-13406; Docket 
No. 2002-CE-18-AD; Revises AD 2003-09-09; which superseded AD 2002-
09-13, Amendment 39-12746.

    (a) What airplanes are affected by this AD? This AD affects the 
following airplane models and serial numbers that are certificated 
in any category:

------------------------------------------------------------------------
                 Model                            Serial numbers
------------------------------------------------------------------------
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. This 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 inspect at  Follow Cessna
 Inspect the part number (P/   whichever occurs      Conquest Service
 N) 5718106-1 wire harness     later, unless         Bulletin No.: CQB02-
 and fuel boost pump lead      already               1, Revision 2,
 wires for chafing or damage.  accomplished:         dated October 7,
                               Within the next 200   2002.
                               hours time-in-
                               service (TIS) after
                               the last inspection
                               required by AD 2002-
                               09-13 or within the
                               next 25 hours TIS
                               after June 24, 2003
                               (the effective date
                               of AD 2003-09-09).
                               Repetitively
                               inspect thereafter
                               at intervals not to
                               exceed 200 hours
                               TIS.
------------------------------------------------------------------------
(2) For Model F406            Initially inspect at  Follow Reims/Cessna
 airplanes: Inspect the P/N    whichever occurs      Caravan Service
 5718106-4 wire harness and    later, unless         Bulletin No.: CAB02-
 fuel boost pump lead wires    already               8, dated June 3,
 for chafing or damage.        accomplished:         2002.
                               within the next 25
                               hours TIS or 60
                               days after June 24,
                               2003 (the effective
                               date of AD 2003-0-
                               09). Repetitively
                               inspect thereafter
                               at intervals not to
                               exceed 200 hours
                               TIS.
------------------------------------------------------------------------
(3) If chafing or damage is   Before further        For Model 441
 found during any inspection   flight after any      airplanes: Follow
 required in paragraph         inspection required   Cessna Conquest
 (d)(1) or (d)(2) of this      in paragraphs         Service Bulletin
 AD:                           (d)(1) and (d)(2)     No.: CQB02-1,
(i) For Model 441 airplanes,   of this AD in which   Revision 2, dated
 replace the wire harnesses,   damage is found. If   October 7, 2002.
 repair fuel boost pump lead   the improved design   For Model F406
 wires, or replace of fuel     or repaired           airplanes: Follow
 boost pump, as applicable.    components are not    Reims/Cessna
(ii) For Model F406            installed per         Caravan Service
 airplanes, repair or          paragraphs            Bulletin No.: CAB2-
 replace the wire harnesses    (d)(3)(i),            8, dated June 3,
 or lead wires, or fuel        (d)(3)(ii),           2002.
 boost pump, as applicable.    (d)(4)(i), and
                               (d)(4)(ii), as
                               applicable, then
                               you must continue
                               to repetitively
                               inspect per
                               paragraph (d)(1) or
                               (d)(2) of this AD.
------------------------------------------------------------------------
(4) Perform the               Within the next 400   Follow Cessna
 installations of paragraph    hours TIS after       conquest Service
 (d)(4)(i) or (d)(4)(ii) of    June 24, 2003 (the    Bulletin No.: CQB02-
 this AD for Model 441         effective date of     1, Revision 2,
 airplanes:.                   AD 2003-09-09),       dated October 7,
(i) Install improved design    unless already        2002.
 fuel boost pump (P/N 1C12-    accomplished.
 17 or FAA-approved
 equivalent P/N) and
 improved design wire
 harness (P/N 5718106-6 or
 FAA-approved equivalent P/
 N).
(ii) Install the protective
 sleeving modification for
 boost pump lead wires that
 are not damaged or any lead
 wires that exhibit any
 chafing of the sleeve or
 outer jacket.
(iii) Installing both
 improved part numbers in
 each wing tank or
 protective sleeving
 modification for the
 existing fuel boost pump
 lead wires terminates the
 repetitive inspection
 requirements of paragraph
 (d)(1) of this AD.
------------------------------------------------------------------------

[[Page 1659]]

 
(5) Perform the installation  Within the next 400   Follow Reims/Cessna
 in either (d)(5)(i) or        hours TIS after       Caravan Service
 (d)(5)(ii) of this AD for     June 24, 2003 (the    Bulletin No.: CAB02-
 Model F406 airplanes:         effective date AD     8, dated June 3,
(i) Install improved design    2003-09-09), unless   2002.
 fuel boost pump (P/N 1C12-    already
 17 or FAA-approved            accomplished.
 equivalent P/N) and
 improved design wire
 harness (P/N 406 28 01 or
 FAA-approved equivalent P/
 N).
(ii) Install the protective
 sleeving modification for
 boost pump lead wires that
 are not damaged or any lead
 wires that exhibit any
 chafing of the sleeve or
 outer jacket must be
 modified by installing a
 protective sleeving over
 the boost pump lead wires.
(iii) Installing both
 improved part numbers in
 each wing tank or
 protective sleeving
 modification for the
 existing fuel boost pump
 lead wires terminates the
 repetitive inspection
 requirements of paragraph
 (d)(2) of this AD.
------------------------------------------------------------------------
(6) Removing the following    As of June 24, 2003   Not applicable.
 warnings for Model 441        (the effective date
 airplanes after compliance    AD 2003-09-09).
 with Cessna Conquest
 Service Bulletin No.: CQB02-
 1, Revision 2, dated
 October 7, 2002:
(i) ``PRIOR TO THE INITIAL
 INSPECTION: THE AIRPLANE
 SHOULD NOT BE OPERATED WITH
 LESS THAN 300 POUNDS OF
 FUEL IN EACH WING.''.
(ii) ``AFTER THE INITIAL
 INSPECTION: THE AIRPLANE
 SHOULD NOT BE OPERATED
 WHENEVER THE LEFT OR RIGHT
 LOW FUEL ANNUNCIATOR IS
 ILLUMINATED.
------------------------------------------------------------------------
(7) Install only improved     As of June 24, 2003   Not applicable.
 design wire harnesses and     (the effective date
 fuel boost pumps as           of AD 2003-09-09).
 specified in paragraphs
 (d)(4) and (d)(5) 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 2003-09-09 or AD 2002-09-13 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: 316-946-4107.
    (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 following Cessna 
Conquest Service Bulletin No.: CQB02-1, Revision 2, dated October 7, 
2002; and Reims Cessna Caravan Service Bulletin No.: CAB02-8, dated 
June 3, 2002. The Director of the Federal Register previously 
approved this incorporation by reference under 5 U.S.C. 552(a) and 1 
CFR part 51 on June 24, 2003 (68 FR 23186, May 1, 2003). You may get 
copies from Cessna Aircraft Company, Product Support, P.O. 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) Does this AD action affect any existing AD actions? This 
amendment revises AD 2002-09-13, Amendment 39-12746.
    (j) When does this amendment become effective? This amendment 
becomes effective on January 22, 2004.

    Issued in Kansas City, Missouri, on January 5, 2004.
Dorenda D. Baker,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-475 Filed 1-9-04; 8:45 am]
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