AD 2003-09-09 R1

AD Final Rules - 030909R1.pdf
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AD Number:
2003-09-09 R1
Document Type:
AD Final Rules
Docket Number:
2002-CE-18-AD
Subject Heading:
Airworthiness Directives; Cessna Aircraft Company Models 441 and F406 Airplanes
Subject:
Fuel pump boost wiring
Status:
Current
Citation:
Federal Register: January 12, 2004 (Volume 69, Number 7)
Citation Publish Date:
01/12/2004
Effective Date:
01/22/2004
Make:
Cessna Aircraft Company | Reims Aviation S.A.
Model:
441 | F406
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
2003-09-09
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
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[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]


–––––––––––––––––––––––––––––––––––


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


–––––––––––––––––––––––––––––––––––


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.
2


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).