Airworthiness Directives; Cessna Model 650 Airplanes, 36472-36474 [05-12306]

Download as PDF 36472 Federal Register / Vol. 70, No. 121 / Friday, June 24, 2005 / Rules and Regulations Revision to Airworthiness Limitations (g) Within 12 months after the effective date of this AD, revise the Airworthiness Limitations section of the Instructions for Continued Airworthiness by inserting a copy of Dornier Temporary Revision ALD–080, dated October 15, 2003, into the Dornier 328 Airworthiness Limitations Document. Thereafter, except as provided in paragraph (h) of this AD, no alternative inspection intervals may be approved for this fuel tank system. Alternative Methods of Compliance (AMOCs) (h) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (i) German airworthiness directive D– 2005–001, dated January 26, 2005, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use the service information 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. To get copies of the service information, contact AvCraft Aerospace GmbH, P.O. Box 1103, D–82230 Wessling, Germany. 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 the NARA, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. TABLE 2.—MATERIAL INCORPORATED BY REFERENCE Service information Date AvCraft Service Bulletin SB–328–00–445, including Price Information Sheet ........................................................................... Dornier Temporary Revision ALD–080 ....................................................................................................................................... Issued in Renton, Washington, on June 15, 2005. Kevin Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–12304 Filed 6–23–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2002–NM–332–AD; Amendment 39–14158; AD 2005–13–21] RIN 2120–AA64 Airworthiness Directives; Cessna Model 650 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to all Cessna Model 650 airplanes, that requires inspecting to determine the part number of the actuator control unit (ACU) and replacing the ACU with a new, improved ACU if necessary. This AD also requires revising the Limitations section of the airplane flight manual. The actions specified by this AD are intended to prevent uncommanded movement of the horizontal stabilizer, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition. DATES: Effective July 29, 2005. VerDate jul<14>2003 16:42 Jun 23, 2005 Jkt 205001 The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of July 29, 2005. The service information referenced in this AD may be obtained from Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Robert P. Busto, Aerospace Engineer, Systems and Propulsion Branch, ACE– 116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946–4157; fax (316) 946–4107. A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to all Cessna Model 650 airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on April 22, 2005 (70 FR 20844). That action proposed to require inspecting to determine the part number of the actuator control unit (ACU) and replacing the ACU with a new, improved ACU if necessary. That action also proposed to require revising the Limitations section of the airplane flight manual. SUPPLEMENTARY INFORMATION: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 August 23, 2004. October 15, 2003. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. We did not receive any comments on the proposed AD. Conclusion After careful review of the available data, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. Cost Impact There are approximately 357 airplanes of the affected design in the worldwide fleet. The FAA estimates that 285 airplanes of U.S. registry will be affected by this AD. We estimate that it will take approximately 2 work hours per airplane to replace the ACU, and that the average labor rate is $65 per work hour. Required parts will cost approximately $3,000 per airplane, if the ACU is exchanged. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $892,050, or $3,130 per airplane. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by E:\FR\FM\24JNR1.SGM 24JNR1 Federal Register / Vol. 70, No. 121 / Friday, June 24, 2005 / Rules and Regulations other administrative actions. The manufacturer may cover the cost of replacement parts associated with this proposed AD, subject to warranty conditions. As a result, the costs attributable to the proposed AD may be less than stated above. 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 Impact The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this action (1) is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under 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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: I 36473 2005–13–21 Cessna Aircraft Company: Amendment 39–14158. Docket 2002– NM–332–AD. Applicability: All Model 650 airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent uncommanded movement of the horizontal stabilizer, which could result in reduced controllability of the airplane, accomplish the following: Inspection and Replacement if Necessary (a) Within 12 months after the effective date of this AD, inspect to determine the part number (P/N) of the actuator control unit (ACU), in accordance with the Accomplishment Instructions of Cessna Service Bulletin SB 650–27–53, dated March 11, 2004. If an ACU having P/N 9914197–7 is installed on the airplane, then no further action is required by this paragraph. If an ACU having P/N 9914197–3 or P/N 9914197– 4 is installed on the airplane, replace the existing ACU with a new, improved ACU having P/N 9914197–7, in accordance with the service bulletin. Although the service bulletin specifies to submit certain information to the manufacturer, this AD does not include that requirement. Airplane Flight Manual (AFM) Revision (b) Within 1 month after the effective date of this AD or concurrently with the replacement required by paragraph (a) of this AD, whichever is first: Revise the Limitations and Normal Procedures sections of the AFM by inserting into the AFM a copy of all the applicable Cessna temporary revisions (TRs) listed in Table 1 of this AD. Note 1: When a statement identical to that in the applicable TR(s) listed in Table 1 of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of the applicable TR may be removed from the AFM. TABLE 1.—AFM REVISION Applicable model 650 airplanes Cessna TR(s) Citation III, S/Ns 0001 through 0199 inclusive, and 0203 through 0206 inclusive; equipped with Honeywell SPZ–8000 integrated avionics system. 65C3FM TC–R02–01, dated May 12, 2004; and 65C3FM TC–R02–06, dated August 11, 2004. 65C3FM TC–R02–01, dated May 12, 2004; and 65C3FM TC–R02–07, dated August 11, 2004. 65C6FM TC–R04–01, dated May 12, 2004; and 65C6FM TC–R04–06, dated August 11, 2004. 65C7FM TC–R10–01, dated May 12, 2004. 65C7FM TC–R10–07, dated August 11, 2004. Citation III, S/Ns 0001 through 0199 inclusive, and 0203 through 0206 inclusive; not equipped with Honeywell SPZ–8000 integrated avionics system. Citation VI, S/Ns 0200 through 0202 inclusive, and 0207 and subsequent ................................... Citation VII, S/Ns 7001 and subsequent ........................................................................................ Citation VII, S/Ns 7001 and subsequent, equipped with Honeywell SPZ–8000 integrated avionics system. Parts Installation (c) As of the effective date of this AD, no person may install an ACU having P/N 9914197–3 or –4, on any airplane. Alternative Methods of Compliance (d) In accordance with 14 CFR 39.19, the Manager, Wichita Aircraft Certification VerDate jul<14>2003 16:42 Jun 23, 2005 Jkt 205001 Office, FAA, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (e) Unless otherwise specified in this AD, the actions must be done in accordance with the service information listed in Table 2 of this AD. This incorporation by reference was PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this service information, contact Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277. To inspect copies of this service information, go to the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or to the FAA, Wichita Aircraft E:\FR\FM\24JNR1.SGM 24JNR1 36474 Federal Register / Vol. 70, No. 121 / Friday, June 24, 2005 / Rules and Regulations Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. TABLE 2.—MATERIAL INCORPORATED BY REFERENCE Cessna Service Information Date Service Bulletin SB 650–27–53 .................................................................................................................................................... Temporary Revision 65C3FM TC–R02–01 .................................................................................................................................. Temporary Revision 65C3FM TC–R02–06 .................................................................................................................................. Temporary Revision 65C3FM TC–R02–07 .................................................................................................................................. Temporary Revision 65C6FM TC–R04–01 .................................................................................................................................. Temporary Revision 65C6FM TC–R04–06 .................................................................................................................................. Temporary Revision 65C7FM TC–R10–01 .................................................................................................................................. Temporary Revision 65C7FM TC–R10–07 .................................................................................................................................. Effective Date (f) This amendment becomes effective on July 29, 2005. Issued in Renton, Washington, on June 14, 2005. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–12306 Filed 6–23–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–18784; Directorate Identifier 2004–NM–59–AD; Amendment 39– 14157; AD 2005–13–20] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–400, –400D, –400F; 767– 200, –300, –300F; and 777–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747–400, –400D, –400F; 767–200, –300, –300F; and 777–200 and –300 series airplanes. This AD requires installing a jumper wire between the wiring of the fire extinguisher switch and the fuel shutoff switch for each engine, and other specified actions. This AD is prompted by a certain combination of conditions, which could cause the fuel spar shutoff valves to remain partially open. We are issuing this AD to prevent a latent open circuit that could leave the fuel spar shutoff valve in a partially open position when the engine fire switch is activated, which could result in fuel from the engine feeding an uncontrolled fire in the engine or the strut. VerDate jul<14>2003 16:42 Jun 23, 2005 Jkt 205001 This AD becomes effective July 29, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of July 29, 2005. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// 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 U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2004–18784; the directorate identifier for this docket is 2004–NM– 59–AD. FOR FURTHER INFORMATION CONTACT: Sulmo Mariano, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6501; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain Boeing Model 747– 400, –400D, –400F; 767–200, –300, –300F; and 777–200 and –300 series airplanes. That action, published in the Federal Register on August 6, 2004 (69 FR 47802), proposed to require installing a jumper wire between the wiring of the fire extinguisher switch and the fuel shutoff switch for each engine, and other specified actions. DATES: Comments We provided the public the opportunity to participate in the development of this AD. We have PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 March 11, 2004. May 12, 2004. August 11, 2004. August 11, 2004. May 12, 2004. August 11, 2004. May 12, 2004. August 11, 2004. considered the comments that have been submitted on the proposed AD. Supportive Comment One commenter states that they have accomplished the necessary airplane modifications on all affected Model 777–200 series airplanes in their fleet. In addition, the commenter states that no additional work is necessary to comply with Boeing Service Bulletin 777–28–0025, Revision 1, dated March 17, 2005. The commenter did not state any finding of service problems or errors in either the service bulletins or the AD, nor has the commenter suggested any change to the AD. We infer that the commenter has no objections to the AD. Request to Revise Service Bulletin References One commenter requests that we coordinate the release of this AD with the pending revisions to Boeing Special Attention Service Bulletins 747–28– 2238, dated October 18, 2001; and 777– 28–0025, dated January 10, 2002. The commenter states that several information notices describe changes to the work instructions that will be incorporated into pending service bulletin revisions. If this AD is released calling for the un-revised service bulletins, each airline would need to request an alternative method of compliance (AMOC) to allow the incorporation of the revised work instructions. We infer that the commenter wants the AD to reference the revised service bulletins. We agree with the commenter’s request to reference the revised service bulletins. We have reviewed Boeing Service Bulletins 747–28–2238, Revision 1; and 777–28–0025, Revision 1; both dated March 17, 2005. The revisions incorporate the changes described in the information notices. Paragraph (f) of this AD has been revised to refer to Revision 1 of Boeing Service Bulletins 747–28–2238 and 777–28–0025. Paragraph (g) of the E:\FR\FM\24JNR1.SGM 24JNR1

Agencies

[Federal Register Volume 70, Number 121 (Friday, June 24, 2005)]
[Rules and Regulations]
[Pages 36472-36474]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12306]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-332-AD; Amendment 39-14158; AD 2005-13-21]
RIN 2120-AA64


Airworthiness Directives; Cessna Model 650 Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Cessna Model 650 airplanes, that requires inspecting 
to determine the part number of the actuator control unit (ACU) and 
replacing the ACU with a new, improved ACU if necessary. This AD also 
requires revising the Limitations section of the airplane flight 
manual. The actions specified by this AD are intended to prevent 
uncommanded movement of the horizontal stabilizer, which could result 
in reduced controllability of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Effective July 29, 2005.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 29, 2005.

ADDRESSES: The service information referenced in this AD may be 
obtained from Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 
67277. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita 
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT: Robert P. Busto, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4157; fax (316) 
946-4107.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Cessna Model 650 airplanes was 
published as a supplemental notice of proposed rulemaking (NPRM) in the 
Federal Register on April 22, 2005 (70 FR 20844). That action proposed 
to require inspecting to determine the part number of the actuator 
control unit (ACU) and replacing the ACU with a new, improved ACU if 
necessary. That action also proposed to require revising the 
Limitations section of the airplane flight manual.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. We did not receive any comments on the 
proposed AD.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule as proposed.

Cost Impact

    There are approximately 357 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 285 airplanes of U.S. registry 
will be affected by this AD.
    We estimate that it will take approximately 2 work hours per 
airplane to replace the ACU, and that the average labor rate is $65 per 
work hour. Required parts will cost approximately $3,000 per airplane, 
if the ACU is exchanged. Based on these figures, the cost impact of the 
AD on U.S. operators is estimated to be $892,050, or $3,130 per 
airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by

[[Page 36473]]

other administrative actions. The manufacturer may cover the cost of 
replacement parts associated with this proposed AD, subject to warranty 
conditions. As a result, the costs attributable to the proposed AD may 
be less than stated above.

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 Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, pursuant to 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. Section 39.13 is amended by adding the following new airworthiness 
directive:

2005-13-21 Cessna Aircraft Company: Amendment 39-14158. Docket 2002-
NM-332-AD.

    Applicability: All Model 650 airplanes, certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent uncommanded movement of the horizontal stabilizer, 
which could result in reduced controllability of the airplane, 
accomplish the following:

Inspection and Replacement if Necessary

    (a) Within 12 months after the effective date of this AD, 
inspect to determine the part number (P/N) of the actuator control 
unit (ACU), in accordance with the Accomplishment Instructions of 
Cessna Service Bulletin SB 650-27-53, dated March 11, 2004. If an 
ACU having P/N 9914197-7 is installed on the airplane, then no 
further action is required by this paragraph. If an ACU having P/N 
9914197-3 or P/N 9914197-4 is installed on the airplane, replace the 
existing ACU with a new, improved ACU having P/N 9914197-7, in 
accordance with the service bulletin. Although the service bulletin 
specifies to submit certain information to the manufacturer, this AD 
does not include that requirement.

Airplane Flight Manual (AFM) Revision

    (b) Within 1 month after the effective date of this AD or 
concurrently with the replacement required by paragraph (a) of this 
AD, whichever is first: Revise the Limitations and Normal Procedures 
sections of the AFM by inserting into the AFM a copy of all the 
applicable Cessna temporary revisions (TRs) listed in Table 1 of 
this AD.

    Note 1: When a statement identical to that in the applicable 
TR(s) listed in Table 1 of this AD has been included in the general 
revisions of the AFM, the general revisions may be inserted into the 
AFM, and the copy of the applicable TR may be removed from the AFM.


                         Table 1.--AFM Revision
------------------------------------------------------------------------
        Applicable model 650 airplanes                Cessna TR(s)
------------------------------------------------------------------------
Citation III, S/Ns 0001 through 0199           65C3FM TC-R02-01, dated
 inclusive, and 0203 through 0206 inclusive;    May 12, 2004; and 65C3FM
 equipped with Honeywell SPZ-8000 integrated    TC-R02-06, dated August
 avionics system.                               11, 2004.
Citation III, S/Ns 0001 through 0199           65C3FM TC-R02-01, dated
 inclusive, and 0203 through 0206 inclusive;    May 12, 2004; and 65C3FM
 not equipped with Honeywell SPZ-8000           TC-R02-07, dated August
 integrated avionics system.                    11, 2004.
Citation VI, S/Ns 0200 through 0202            65C6FM TC-R04-01, dated
 inclusive, and 0207 and subsequent.            May 12, 2004; and 65C6FM
                                                TC-R04-06, dated August
                                                11, 2004.
Citation VII, S/Ns 7001 and subsequent.......  65C7FM TC-R10-01, dated
                                                May 12, 2004.
Citation VII, S/Ns 7001 and subsequent,        65C7FM TC-R10-07, dated
 equipped with Honeywell SPZ-8000 integrated    August 11, 2004.
 avionics system.
------------------------------------------------------------------------

Parts Installation

    (c) As of the effective date of this AD, no person may install 
an ACU having P/N 9914197-3 or -4, on any airplane.

Alternative Methods of Compliance

    (d) In accordance with 14 CFR 39.19, the Manager, Wichita 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance for this AD.

Incorporation by Reference

    (e) Unless otherwise specified in this AD, the actions must be 
done in accordance with the service information listed in Table 2 of 
this AD. This incorporation by reference was approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. To get copies of this service information, 
contact Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277. 
To inspect copies of this service information, go to the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or to the FAA, Wichita Aircraft

[[Page 36474]]

Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas; or to the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

              Table 2.--Material Incorporated by Reference
------------------------------------------------------------------------
         Cessna Service Information                      Date
------------------------------------------------------------------------
Service Bulletin SB 650-27-53...............  March 11, 2004.
Temporary Revision 65C3FM TC-R02-01.........  May 12, 2004.
Temporary Revision 65C3FM TC-R02-06.........  August 11, 2004.
Temporary Revision 65C3FM TC-R02-07.........  August 11, 2004.
Temporary Revision 65C6FM TC-R04-01.........  May 12, 2004.
Temporary Revision 65C6FM TC-R04-06.........  August 11, 2004.
Temporary Revision 65C7FM TC-R10-01.........  May 12, 2004.
Temporary Revision 65C7FM TC-R10-07.........  August 11, 2004.
------------------------------------------------------------------------

Effective Date

    (f) This amendment becomes effective on July 29, 2005.

    Issued in Renton, Washington, on June 14, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-12306 Filed 6-23-05; 8:45 am]
BILLING CODE 4910-13-P

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