[Federal Register Volume 70, Number 71 (Thursday, April 14, 2005)]
[Rules and Regulations]
[Pages 19682-19685]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-7379]



[[Page 19682]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20916; Directorate Identifier 2005-NM-027-AD; 
Amendment 39-14055; AD 2005-08-03]
RIN 2120-AA64


Airworthiness Directives; Cessna Model 680 Airplanes

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Cessna Model 680 airplanes. This AD requires revising the 
airplane flight manual (AFM) to add procedures to facilitate recovery 
of the cockpit display units in the event that the cockpit display 
units go blank, and to add flight crew briefings on the use of standby 
instruments in case the cockpit display units go blank and do not 
recover. This AD also requires repetitive tests of the avionics 
standard communication bus (ASCB) for any failures, and corrective 
action if any failure is found. This AD also requires installing 
hardware and avionics software upgrades; installing the upgrades will 
allow removal of AFM revisions and will end the repetitive inspections 
of the ASCB. This AD is prompted by a report indicating that analysis 
of the Honeywell Primus Epic systems installed on Cessna Model 680 
airplanes revealed that all four of the cockpit display units could go 
blank simultaneously. We are issuing this AD to prevent a simultaneous 
loss of data from all four cockpit display units, and loss of primary 
navigation instruments, autopilot, flight director, master caution/
warning lights, aural warnings, global positioning system position 
information, and air data and altitude information to non-avionics 
systems. These losses could reduce the flightcrew's situational 
awareness, increase flightcrew workload, and consequently reduce the 
ability to maintain safe flight of the airplane.

DATES: Effective April 29, 2005.
    The incorporation by reference of certain publications listed in 
the AD are approved by the Director of the Federal Register as of April 
29, 2005.
    We must receive comments on this AD by June 13, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this 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.
     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 service information identified in this 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 in person 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-2005-20916; the directorate identifier for this docket is 
2005-NM-027-AD.

Examining the Dockets

    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 located 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.

FOR FURTHER INFORMATION CONTACT: Bryan Easterwood, Aerospace Engineer, 
Electrical and Avionics Systems, 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: We have received reports indicating that, on 
airplanes equipped with the Honeywell Primus Epic system, all 
information on all cockpit display units may be lost (blank screens) or 
may become simultaneously invalid during flight. On Cessna Model 680 
airplanes, this condition has been attributed to a failure of the 
master network interface controller (NIC) in the Honeywell Primus Epic 
system to synchronize with NICs that control the avionics system 
communication bus (ASCB). Attempts by all of the NICs to re-synchronize 
disables all ASCB data. The synchronization process can be delayed or 
worsened by a failure of any ASCB. This condition, if not corrected, 
could result in the simultaneous loss of data from all four cockpit 
display units, and loss of primary navigation instruments, autopilot, 
flight director, master caution/warning lights, aural warnings, global 
positioning system position information, and air data and altitude 
information to non-avionics systems. These losses could reduce the 
flightcrew's situational awareness, increase flightcrew workload, and 
consequently reduce the ability to maintain safe flight of the 
airplane.

Other Relevant Rulemaking

    We have determined that, since the Honeywell Primus Epic system is 
also installed on Dassault Model Falcon 2000EX and 900EX series 
airplanes, Gulfstream Model GV-SP series airplanes, and Empresa 
Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 series 
airplanes, those airplanes are subject to an unsafe condition similar 
to that addressed in this AD. In light of that determination, we issued 
the ADs listed in the following table to address the unsafe condition 
on those airplane models.

                               Related ADs
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                Airplane                           AD citation
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Dassault Model Falcon 2000EX and 900EX   AD 2005-04-15, amendment 39-
 series airplanes.                        13987 (70 FR 9853, March 1,
                                          2005).
Gulfstream Model GV-SP series airplanes  AD 2005-04-06, amendment 39-
                                          13978 (70 FR 7847, February
                                          16, 2005).
EMBRAER Model ERJ 170 series airplanes.  AD 2004-26-12, amendment 39-
                                          13924 (69 FR 78300, December
                                          30, 2004).
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Relevant Service Information

    We have reviewed Cessna Service Bulletin SB680-34-03, including 
Attachment, Revision 1, dated March 18, 2005. The service bulletin 
describes procedures for performing repetitive tests of the avionics 
standard communication bus (ASCB) for any failures; accomplishing 
corrective action if any failure is found during the ASCB test; and 
installing hardware and avionics software upgrades. The corrective 
action for ASCB test failures includes fixing any wiring problems, 
replacing parts, and correcting computer configurations. The hardware 
and avionics software upgrades include:
     Installing a software upgrade of the Honeywell Primus Epic 
system;
     Replacing the horizontal stabilizer trim actuator with a 
new, improved actuator;
     Modifying certain wiring associated with the actuator; and
     Replacing two printed circuit boards (PCBs) with new, 
improved PCBs.
    We have also reviewed Cessna Temporary Changes (TC) 68FM TC-R03-01; 
68FM TC-R03-02; 68FM TC-R03-03; and 68FM TC-R03-04; all dated March 18, 
2005; to the Cessna Model 680 Citation Airplane Flight Manual (AFM). 
The TCs describe procedures to recover the cockpit display units in the 
event that all four cockpit display units go blank during flight. 
Additionally, these TCs advise the flight crew that, during the use of 
Taxi, Before Takeoff, Approach, and Before Landing checklists, the 
briefings (takeoff and approach) should include the possibility of the 
loss of all cockpit display units and the subsequent transition to 
standby instruments.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design. Therefore, we are 
issuing this AD to prevent the simultaneous loss of data from all four 
cockpit display units, and loss of primary navigation instruments, 
autopilot, flight director, master caution/warning lights, aural 
warnings, global positioning system position information, and air data 
and altitude information to non-avionics systems. These losses could 
reduce the flightcrew's situational awareness, increase flightcrew 
workload, and consequently reduce the ability to maintain safe flight 
of the airplane. This AD requires accomplishing the actions specified 
in the service bulletin described previously, except as discussed under 
``Difference Between the AD and the Service Bulletin.'' This AD also 
requires revising the AFM to include the information in the TCs 
described previously.

Difference Between the AD and the Service Bulletin

    Operators should note that, although the Accomplishment 
Instructions of the referenced service bulletin describe procedures for 
submitting a maintenance transaction report recording compliance with 
the service bulletin, this AD does not require that action. The FAA 
does not need this information from operators.

Clarification of Actions Beyond What Is Necessary To Prevent the Unsafe 
Condition

    The Cessna service bulletin was being developed for Honeywell Epic 
Phase 2 certification before the unsafe condition was reported to the 
FAA. The software upgrade that is necessary for preventing the unsafe 
condition is included with software upgrades that were developed for 
the Phase 2 certification. Hardware upgrades that were also developed 
for the Phase 2 certification are included in the service bulletin. 
While it is theoretically possible to separate the upgrades and then 
issue a service bulletin that specifies only the software upgrades 
necessary to prevent the unsafe conditions, it is impractical to do the 
service bulletin revision before the effective date of this AD. 
Therefore, we find it necessary to require accomplishment of all the 
software upgrades and hardware upgrades specified in the service 
bulletin.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed under ADDRESSES. Include ``Docket No. FAA-2005-20916; 
Directorate Identifier 2005-NM-027-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the 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 AD. Using the search function of our docket 
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 the 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.

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 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

[[Page 19684]]

    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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-08-03 Cessna Aircraft Company: Amendment 39-14055. Docket No. 
FAA-2005-20916; Directorate Identifier 2005-NM-027-AD.

Effective Date

    (a) This AD becomes effective April 29, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Cessna Model 680 airplanes, certificated 
in any category; with serial numbers -0001 through -0021 inclusive.

Unsafe Condition

    (d) This AD was prompted by a report indicating that analysis of 
the Honeywell Primus Epic systems installed on Cessna Model 680 
airplanes revealed that all four of the cockpit display units could 
go blank simultaneously. The FAA is issuing this AD to prevent a 
simultaneous loss of data from all four cockpit display units, and 
loss of primary navigation instruments, autopilot, flight director, 
master caution/warning lights, aural warnings, global positioning 
system (GPS) position information, and air data and altitude 
information to non-avionics systems. These losses could reduce the 
flightcrew's situational awareness, increase flightcrew workload, 
and consequently reduce the ability to maintain safe flight 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.

Airplane Flight Manual (AFM) Revisions

    (f) Within 72 hours after the effective date of this AD, revise 
the applicable sections of the Cessna Model 680 Citation Airplane 
Flight Manual 68FM by inserting a copy of the procedures contained 
in the temporary changes listed in Table 1 of this AD.

                   Table 1.--Cessna Temporary Changes
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        Cessna temporary changes                       Date
------------------------------------------------------------------------
68FM TC-R03-01.........................  March 18, 2005.
68FM TC-R03-02.........................  March 18, 2005.
68FM TC-R03-03.........................  March 18, 2005.
68FM TC-R03-04.........................  March 18, 2005.
------------------------------------------------------------------------

Initial and Repetitive Tests

    (g) Within 30 days after the effective date of this AD, do a 
test of the avionics system communication bus for any failure 
indication in accordance with the Attachment of Cessna Service 
Bulletin SB680-34-03, Revision 1, dated March 18, 2005. If any 
failure indications are found during the test, do applicable 
corrective actions before further flight in accordance with the 
service bulletin. Repeat the test thereafter at intervals not to 
exceed 30 days until the actions required by paragraph (h) of this 
AD are done.

Terminating Actions

    (h) Within 90 days after the effective date of this AD, do 
hardware and avionics software upgrades in accordance with the 
Accomplishment Instructions of Cessna Service Bulletin SB680-34-03, 
including Attachment, Revision 1, dated March 18, 2005. Doing the 
requirements of this paragraph ends the requirements of paragraph 
(g) of this AD, and the AFM revisions required by paragraph (f) of 
this AD may be removed from the AFM.

No Reporting Required

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

Previous Actions

    (j) Hardware and avionics software upgrades done before the 
effective date of this AD in accordance with the Accomplishment 
Instructions of Cessna Service Bulletin SB680-34-03, dated February 
2, 2005, is acceptable for compliance with the requirements of 
paragraph (h) of this AD.

Alternative Methods of Compliance (AMOCs)

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

Material Incorporated by Reference

    (l) You must use the service information that is specified in 
Table 2 of this AD to perform the actions that are required by this 
AD, unless the AD specifies otherwise. The Director of the Federal 
Register approves the incorporation by reference of these documents 
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of 
the service information, contact Cessna Aircraft Co., P.O. Box 7706, 
Wichita, Kansas 67277. To view the AD docket, go to the Docket 
Management Facility, U.S. Department of Transportation, 400 Seventh 
Street SW., room PL-401, Nassif Building, Washington, DC. To review 
copies of the service information, go to the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

              Table 2.--Material Incorporated by Reference
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   Cessna service information     Revision level           Date
------------------------------------------------------------------------
Cessna Service Bulletin SB680-   1..............  March 18, 2005
 34-03, including Attachment.
Cessna Temporary Change 68FM TC- Original.......  March 18, 2005.
 R03-01.
Cessna Temporary Change 68FM TC- Original.......  March 18, 2005.
 R03-02.
Cessna Temporary Change 68FM TC- Original.......  March 18, 2005.
 R03-03.
Cessna Temporary Change 68FM TC- Original.......  March 18, 2005.
 R03-04.
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    Issued in Renton, Washington, on April 5, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-7379 Filed 4-13-05; 8:45 am]
BILLING CODE 4910-13-P