[Federal Register Volume 70, Number 73 (Monday, April 18, 2005)]
[Proposed Rules]
[Pages 20083-20085]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-7674]



[[Page 20083]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20970; Directorate Identifier 2004-NM-53-AD]
RIN 2120-AA64


Airworthiness Directives; Cessna Model 500, 501, 550, S550, 551, 
and 560 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Cessna Model 500, 501, 550, S550, 551, and 560 airplanes. 
This proposed AD would require revising the airplane flight manual 
(AFM) to prohibit use of the wing fuel boost pumps for defueling under 
certain conditions; installing a placard; doing other specified 
investigative and corrective actions as necessary; and modifying the 
boost pumps. This proposed AD also would require the subsequent removal 
of the AFM revision and placard. This proposed AD is prompted by a 
report of a chafed electrical wiring harness, which was arcing inside 
the fuel tank. We are proposing this AD to prevent potential fuel vapor 
ignition in a fuel tank, which could result in explosion and loss of 
the airplane.

DATES: We must receive comments on this proposed AD by June 2, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     By fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For the service information identified in this proposed AD, contact 
Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, on 
the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-20970; the directorate identifier for this docket is 
2004-NM-53-AD.

FOR FURTHER INFORMATION CONTACT: Bryan Easterwood, Aerospace Engineer, 
Electrical Systems and Avionics Branch, ACE-119W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4132; fax (316) 
946-4107.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20970; 
Directorate Identifier 2004-NM-53-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is on the plaza level of the Nassif Building at the DOT street 
address stated in the ADDRESSES section. Comments will be available in 
the AD docket shortly after the DMS receives them.

Discussion

    We have received a report indicating that chafing can exist between 
the submerged electrical wiring harness on the wing fuel boost pump and 
an aluminum fuel line inside the wing fuel tank. When troubleshooting a 
tripped circuit breaker for the fuel boost pump on a Cessna Model 550 
airplane, technicians discovered that the electrical wiring harness of 
the wing fuel boost pump had chafed through the wire bundle insulation 
and was arcing on an aluminum fuel line inside the wing fuel tank. 
Subsequent inspections of additional airplanes revealed similar wire 
chafing on nearly half the inspected airplanes. The resulting potential 
for arcing and fuel vapor ignition, if not corrected, could result in 
explosion and loss of the airplane.
    The design of the wire routing installation, the type and spacing 
of electrical wire clamps or lack of clamping, and the fuel pump wire 
type in the area of the wing fuel boost pump on Model 550 airplanes are 
the same on Cessna Model 500, 501, S550, 551, and 560 airplanes; 
therefore, the unsafe condition could exist on all of these airplanes.

Relevant Service Information

    We have reviewed the Cessna service bulletins listed in the 
following table:

                                               Service Information
----------------------------------------------------------------------------------------------------------------
            Service bulletin                         Date                  Airplane model(s)        Serial Nos.
----------------------------------------------------------------------------------------------------------------
SB500-28-12.............................  June 14, 2004.............  500 and 501...............       0001-0689
SBS550-28-08............................  May 7, 2004...............  S550......................       0001-0160
SB550-28-14.............................  December 2, 2003..........  550 and 551...............       0002-0733
SB550-28-15.............................  January 20, 2004..........  550.......................       0801-1075
SB560-28-10.............................  April 23, 2004............  560.......................       0001-0538
SB560-28-11.............................  March 12, 2004............  560.......................       0539-0648
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[[Page 20084]]

    The service bulletins describe procedures for:
     Revising the Limitations section of the airplane flight 
manual (AFM) to prohibit use of the wing fuel boost pumps for defueling 
if the individual fuel load in each wing is less than a specified 
weight;
     Installing a placard that advises the flightcrew of the 
minimum fuel weight requirements; and
     Inspecting the full length of the wiring of the wing fuel 
boost pumps to detect chafing through the outer jackets, through the 
wire braid (shielding), and into the wire insulation.
    The service bulletins also describe procedures for corrective and 
other specified actions, depending on the inspection results, as 
follows:
     Applying sealant to any damaged areas of the wing fuel 
boost pump wiring;
     Installing spiral wrap on fuel boost pump wiring; and
     Replacing the fuel boost pump with a new pump, if the wire 
conductor is exposed and chafing is found through the outer jacket, 
wire braid, and insulation.
    In addition, the service bulletins describe procedures for 
inspecting for damage of the fuel tube and wing structure, replacing 
damaged fuel tubes with new fuel tubes, and replacing or repairing 
damaged wing structure.
    The service bulletins also describe procedures for modifying the 
wing fuel boost pumps by installing clamps on certain tube assemblies 
and on the boost pump wiring, and ensuring that the wires will not 
contact any fuel lines or the airplane structure.
    The service bulletins specify removing the AFM revision and placard 
after doing the inspection, corrective and other specified actions, and 
modification.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. Therefore, we are proposing this AD, which 
would require the actions specified in the service information 
described previously, except as discussed under ``Differences Between 
the Proposed AD and the Service Information.''

Differences Between the Proposed AD and the Service Information

    This proposed AD specifies the placard text size, which is not 
provided in the service bulletins. We find it necessary to require this 
minimum standard on the placard to ensure its readability.
    The service bulletins specify revising the AFM immediately (after 
receipt of the service bulletin), but this proposed AD would allow up 
to 25 flight hours for this action. In developing an appropriate 
compliance time for this action, we considered the safety implications 
and operators' typical maintenance schedules and determined that 25 
flight hours will have minimal effect on operators, and no adverse 
effect on safety.
    Although the Accomplishment Instructions of the referenced service 
bulletins describe procedures for submitting a sheet recording 
compliance with the service bulletin, this proposed AD would not 
require that action. We do not need this information from operators.

Costs of Compliance

    This proposed AD would affect about 2,397 airplanes worldwide. The 
following table provides the estimated costs for U.S. operators to 
comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                 Applicable service bulletin                      Work     Average labor       Parts         Cost per       registered      Fleet cost
                                                                 hours     rate per hour                     airplane        airplanes
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SB500-28-12..................................................         20             $65          $2,229          $3,529             444      $1,566,876
SBS550-28-08.................................................         12              65             102             882             126         111,132
SB550-28-14..................................................          8              65           1,992           2,512             469       1,178,128
SB550-28-15..................................................          8              65           1,936           2,456             194         476,464
SB560-28-10..................................................         12              65           1,949           2,729             428       1,168,012
SB560-28-11..................................................          8              65           1,052           1,572             101         158,772
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

[[Page 20085]]

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Cessna Aircraft Company: Docket No. FAA-2005-20970; Directorate 
Identifier 2004-NM-53-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by June 2, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the Cessna airplanes listed in Table 1 of 
this AD, certificated in any category.

                         Table 1.--Applicability
------------------------------------------------------------------------
           Airplane model(s)                      Serial numbers
------------------------------------------------------------------------
500 and 501............................  0001 through 0689 inclusive.
S550...................................  0001 through 0160 inclusive.
550 and 551............................  0002 through 0733 inclusive.
550....................................  0801 through 1075 inclusive.
560....................................  0001 through 0648 inclusive.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD was prompted by a report of a chafed electrical 
wiring harness, which was arcing inside the fuel tank. We are 
issuing this AD to prevent potential fuel vapor ignition in a fuel 
tank, which could result in explosion and loss of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Information

    (f) The term ``service bulletin'' as used in this AD refers to 
the applicable service bulletin listed in Table 2 of this AD.

                                          Table 2.--Service Information
----------------------------------------------------------------------------------------------------------------
                                     Having serial  Use Cessna  Service Bulletin--
        For Cessna Model--             numbers--                                              Dated--
----------------------------------------------------------------------------------------------------------------
500 and 501 airplanes.............       0001-0689  SB500-28-12                    June 14, 2004.
S550 airplanes....................       0001-0160  SBS550-28-08                   May 7, 2004.
550 and 551 airplanes.............       0002-0733  SB550-28-14                    December 2, 2003.
550 airplanes.....................       0801-1075  SB550-28-15                    January 20, 2004.
560 airplanes.....................       0001-0538  SB560-28-10                    April 23, 2004.
560 airplanes.....................       0539-0648  SB560-28-11                    March 12, 2004.
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AFM Revision

    (g) Within 25 flight hours after the effective date of this AD: 
Revise the Limitations section of the applicable Cessna airplane 
flight manual (AFM) to prohibit use of the wing fuel boost pumps for 
defueling under certain conditions, by inserting the applicable 
temporary change identified in the service bulletin.

Placard Installation

    (h) Within 25 flight hours after the effective date of this AD: 
Install a placard close to the fuel quantity gauge, in accordance 
with the Accomplishment Instructions of the service bulletin. In 
addition to the specifications in the service bulletin, the letters 
on the placard must be at least \1/4\-inch tall.

Inspection and Modification

    (i) Within 300 flight hours after the effective date of this AD: 
Do the actions specified in paragraphs (i)(1) and (i)(2) of this AD 
in accordance with the Accomplishment Instructions of the service 
bulletin.
    (1) Do a detailed inspection for chafed wiring of the wing fuel 
boost pumps, and, before further flight thereafter, do all 
applicable corrective and other specified actions.
    (2) Modify the wing fuel boost pumps.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

    (j) Before further flight after the inspection and modification 
required by paragraph (i) of this AD, remove the AFM temporary 
change and placard required by paragraphs (g) and (h) of this AD.

Reporting Clarification

    (k) Although the service bulletin specifies to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

Alternative Methods of Compliance (AMOCs)

    (l) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.

    Issued in Renton, Washington, on April 11, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-7674 Filed 4-15-05; 8:45 am]
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