[Federal Register: January 12, 2004 (Volume 69, Number 7)]
[Rules and Regulations]
[Page 1657-1659]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12ja04-4]
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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
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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. 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:
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Actions Compliance Procedures
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(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.
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(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.
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(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.
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(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.
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[[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]
BILLING CODE 4910-13-P