[Federal Register Volume 69, Number 133 (Tuesday, July 13, 2004)]
[Rules and Regulations]
[Pages 41920-41923]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-15666]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-54-AD; Amendment 39-13729; AD 2004-14-20]
RIN 2120-AA64


Airworthiness Directives; The Cessna Aircraft Company Model 525 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA supersedes Airworthiness Directive (AD) 2003-21-07, 
which applies to certain The Cessna Aircraft Company (Cessna) Model 525 
airplanes. AD 2003-21-07 currently requires you to disengage the pitch 
trim circuit breaker and AP servo circuit breaker and then tie strap 
each of them to prevent them from being engaged. Not utilizing this 
equipment prevents a single-point failure. This AD is the result of 
Cessna having now developed and made changes in the design of the 
affected trim printed circuit board (PCB) assembly to allow the use of 
the assembly and the prevention of the single-point failure, and 
identification of additional airplanes that have the same unsafe 
condition. Consequently, this AD requires you to remove and replace an 
old trim PCB assembly with a new design assembly or modify an old trim 
PCB assembly to the new design. We are issuing this AD to correct this 
single-point failure in the electric pitch trim system, which will 
result in a runaway pitch trim condition where the pilot could not 
disconnect using the control wheel autopilot/trim disconnect switch. 
Failure of the electric trim system would result in a large pitch 
mistrim and would cause excessive control forces that the pilot could 
not overcome.

DATES: This AD becomes effective on August 23, 2004.
    As of August 23, 2004, the Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulation.

ADDRESSES: You may get the service information identified in this AD 
from The Cessna Aircraft Company, Product Support, P.O. Box 7706, 
Wichita, Kansas 67277; telephone: (316) 517-6000; facsimile: (316) 517-
8500.
    You may view the AD docket at FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2003-CE-54-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. 
to 4 p.m., Monday through Friday, except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Dan Withers, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Wichita, 
Kansas 67209; telephone: (316) 946-4196; facsimile: (316) 946-4107.

SUPPLEMENTARY INFORMATION:

Discussion

    What events have caused this AD? A report of an accident involving 
a Cessna Model 525 airplane where the pilot reported a problem with the 
pitch trim system, and later Cessna and FAA analysis that revealed the 
potential for a single-wire shorting caused us to issue AD 2003-21-07, 
Amendment 39-13342 (68 FR 60028, October 21, 2003). AD 2003-21-07 
currently requires you to do the following on Cessna Model 525 
airplanes:

--Disengage the pitch trim circuit breaker and AP servo circuit 
breaker; and
--Tie strap each of them to prevent them from being engaged.

    What has happened since AD 2003-21-07 to initiate this action? AD 
2003-21-07 is considered an interim action since compliance corrected 
the condition where the control wheel

[[Page 41921]]

autopilot/trim disconnect switch did not stop the runaway condition. 
However, AD 2003-21-07 did not correct the issue of the single-point 
failure while still utilizing the desired equipment. Cessna has now 
developed and made changes in the design of the affected trim printed 
circuit board (PCB) assembly to eliminate the single-point failure 
while allowing the use of the equipment, and identified additional 
airplanes that have the same unsafe condition.
    What is the potential impact if FAA took no action? Failure of the 
electric trim system would result in a large pitch mistrim and would 
cause excessive control forces that the pilot could not overcome.
    Has FAA taken any action to this point? We issued a proposal to 
amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to 
include an AD that would apply to certain Cessna Model 525 airplanes. 
This proposal was published in the Federal Register as a notice of 
proposed rulemaking (NPRM) on February 11, 2004 (69 FR 6585). The NPRM 
proposed to supersede AD 2003-21-07 with a new AD that would require 
you to:

--Remove any 6518351-3 or 6518351-5 trim PCB assembly and replace with 
a 6518351-10 (EX) trim PCB assembly; or
--Modify the 6518351-8 trim PCB assembly to a 6518351-10 trim PCB 
assembly.

Comments

    Was the public invited to comment? We provided the public the 
opportunity to participate in developing this AD. We received no 
comments on the proposal or on the determination of the cost to the 
public.

Conclusion

    What is FAA's final determination on this issue? We have carefully 
reviewed the available data and determined that air safety and the 
public interest require adopting the AD as proposed except for minor 
editorial corrections. We have determined that these minor corrections:

--Are consistent with the intent that was proposed in the NPRM for 
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already 
proposed in the NPRM.

Changes to 14 CFR Part 39--Effect on the AD

    How does the revision to 14 CFR part 39 affect this AD? On July 10, 
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, 
July 22, 2002), which governs the FAA's AD system. This regulation now 
includes material that relates to altered products, special flight 
permits, and alternative methods of compliance. This material 
previously was included in each individual AD. Since this material is 
included in 14 CFR part 39, we will not include it in future AD 
actions.

Costs of Compliance

    How many airplanes does this AD impact? We estimate that this AD 
affects 251 airplanes in the U.S. registry.
    What is the cost impact of this AD on owners/operators of the 
affected airplanes? We estimate the following costs to accomplish the 
modification of the 6518351-8 trim PCB assembly to a 6518351-10 trim 
PCB assembly. We have no way of determining the number of airplanes 
that may need this modification:

----------------------------------------------------------------------------------------------------------------
                 Labor cost                      Parts cost                  Total cost per airplane
----------------------------------------------------------------------------------------------------------------
4 workhours x $65 per hour = $260...........           $2,995   $2,995 + $260 = $3,255.
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    We estimate the following costs to accomplish the replacement of 
any 6518351-3 or 6518351-5 trim PCB assembly with a 6518351-10 (EX) 
trim PCB assembly. We have no way of determining the number of 
airplanes that may need this replacement:

----------------------------------------------------------------------------------------------------------------
                 Labor cost                      Parts cost                  Total cost per airplane
----------------------------------------------------------------------------------------------------------------
2 workhours x $65 per hour = $130...........           $2,995   $2,995 + $130 = $3,125.
----------------------------------------------------------------------------------------------------------------

    What is the difference between the cost impact of this AD and the 
cost impact of AD 2003-21-07? The estimated cost impact of AD 2003-21-
07 on each of the 116 airplanes in the U.S. registry affected by AD 
2003-21-07 is $65. This is to disengage the pitch trim circuit breaker 
and AP servo circuit breaker and then tie strap each of them to prevent 
them from being engaged.
    The estimated cost of this AD is $3,125 or $3,255 on each of 251 
airplanes in the U.S. registry to do the replacement or modification of 
the trim PCB assembly.

Compliance Time of This AD

    What is the compliance time of this AD? The compliance time of this 
AD is ``within the next 24 calendar months after the effective date of 
this AD or within 300 hours time-in-service (TIS) after the effective 
date of this AD, whichever occurs first.''
    Why is the compliance time of this AD presented in both hours TIS 
and calendar time? A single-wire shorting to 28 volts or a failure of a 
relay that results in the relay contacts remaining closed is a direct 
result of airplane operation. For example, either failure could occur 
on an affected airplane within a short period of airplane operation 
while you could operate another affected airplane for a considerable 
amount of time without experiencing either failure. Therefore, to 
assure that either failure is detected and corrected in a timely manner 
without inadvertently grounding any of the affected airplanes, we are 
using a compliance time based upon both hours TIS and calendar time.

Regulatory Findings

    Will this AD impact various entities? 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.
    Will this AD involve a significant rule or regulatory action? For 
the reasons discussed above, I certify that this AD:
    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

[[Page 41922]]

under the criteria of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2003-CE-54-AD'' in your request.

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 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. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2003-21-07, Amendment 39-13342 (68 FR 60028, October 21, 2003), and by 
adding a new AD to read as follows:

2004-14-20 The Cessna Aircraft Company: Amendment 39-13729; Docket 
No. 2003-CE-54-AD; Supersedes AD 2003-21-07; Amendment 39-13342.

When Does This AD Become Effective?

    (a) This AD becomes effective on August 23, 2004.

What Other ADs Are Affected by This Action?

    (b) This AD supersedes AD 2003-21-07.

What Airplanes Are Affected by This AD?

    (c) This AD affects Model 525 airplanes with the following 
serial numbers that are certificated in any category:
    (1) Group 1 (maintains the actions from AD 2003-21-07): 525-
0001, 525-0002, and 525-0004 through 525-0159.
    (2) Group 2: 525-0160 through 525-0359.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of Cessna having now developed and 
made changes in the design of the affected trim printed circuit 
board (PCB) assembly to allow the use of the assembly and the 
prevention of the single-point failure, and identification of 
additional airplanes that have the same unsafe condition. The 
actions specified in this AD are intended to correct this single-
point failure in the electric pitch trim system, which will result 
in a runaway pitch trim condition where the pilot could not 
disconnect using the control wheel autopilot/trim disconnect switch. 
Failure of the electric trim system would result in a large pitch 
mistrim and would cause excessive control forces that the pilot 
could not overcome.

What Must I Do To Address This Problem?

    (e) To address this problem, you must do the following:

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           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) For Group 1 airplanes     Within 5 calendar     Not Applicable.
 only: Disengage the PITCH     days or 10 hours
 TRIM circuit breaker          time-in-service
 located on the left circuit   after October 22,
 breaker panel. Install a      2003-21-07),
 tie strap (part number (P/    whichever occurs
 N) MS3367-1-4 or equivalent   first.
 part number) on the shaft
 of the PITCH TRIM circuit
 breaker to prevent the
 circuit breaker from being
 engaged.
(2) For Group 1 airplanes     Within 5 calendar     Not Applicable.
 only: Disengage the AP        days or 10 hours
 SERVOS circuit breaker        time-in-service
 located in the right          after October 22,
 circuit breaker panel.        2003 (the effective
 Install a tie strap (P/N      date of AD 2003-21-
 MS3367-1-4 or equivalent      07), whichever
 part number) on the shaft     occurs first.
 of the AP SERVOS circuit
 breaker from being engaged.
(3) The Minimum Crew portion  Not Applicable......  Not Applicable.
 of Section II--Operating
 Limitations of the Airplane
 Flight Manual (AFM)
 provides information on
 applicable operating
 limitations with the
 autopilot inoperable.
(4) All affected airplanes    Not Applicable......  Not Applicable.
 were originally equipped
 with a P/N 6518351-3 or P/N
 65138351-5 Trim PCB
 Assembly. If a P/N 6518351-
 8 Trim PCB Assembly is
 installed, contact the
 Wichita Aircraft
 Certification Office at the
 address in paragraph (f) of
 this AD to determine if the
 installed P/N 6518351-8
 Trim PCB assembly is an
 alternative method of
 compliance to this AD.
(5) Cessna Citation Alert     Not Applicable......  Not Applicable.
 Service Letter ASL525-27-
 02, dated October 10, 2003,
 contains information
 related to this subject.
(6) For both Group 1 and      Within the next 24    Follow the
 Group 2 airplanes: Do the     calendar months       ACCOMPLISHMENT
 trim PCB assembly change as   after August 23,      INSTRUCTIONS
 follows:                      2004 (the effective   paragraph of Cessna
(i) Modify the 6518351-8       date of this AD) or   Citation Service
 trim PCB assembly to a        within 300 hours      Bulletin No. SB525-
 6518351-10 trim PCB           time-in-service       27-17, dated
 assembly; or.                 (TIS) after August    December 9, 2003.
(ii) Replace any 6518351-3     23, 2004 (the
 or 6518351-5 trim PCB         effective date of
 assembly with a 6518351-10    this AD), whichever
 (EX) trim PCB assembly..      occurs first,
                               unless already done.
(7) For both Group 1 and      Before further        Follow the
 Group 2 airplanes: Remove     flight after the      ACCOMPLISHMENT
 any tie strap (P/N MS3367-1-  modification or       INSTRUCTIONS
 4 or equivalent part          replacement of the    paragraph of Cessna
 number) on the AP SERVOS      trim PCB assembly     Citation Service
 and PITCH TRIM circuit        required by           Bulletin No. SB525-
 breakers. (Required by AD     paragraph (e)(6)(i)   27-17, dated
 2003-21-07.).                 or (e)(6)(ii) of      December 9, 2003.
                               this AD.

[[Page 41923]]

 
(8) For both Group 1 and      As of August 23,      Not Applicable.
 Group 2 airplanes: Do not     2004 (the effective
 install any 6518351-8,        date of this AD).
 6518351-3, or 6518351-5
 trim PCB assembly.
------------------------------------------------------------------------

May I Request an Alternative Method of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.19. Unless FAA authorizes otherwise, send your request to 
your principal inspector. The principal inspector may add comments 
and will send your request to the Manager, Wichita Aircraft 
Certification Office (ACO), FAA.
    (1) For information on any already approved alternative methods 
of compliance, contact Dan Withers, Aerospace Engineer, Wichita ACO, 
FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-
4196; facsimile: (316) 946-4107.
    (2) Alternative methods of compliance approved for AD 2003-21-07 
are not approved as alternative methods of compliance for this AD.

Does This AD Incorporate Any Material by Reference?

    (g) You must do the actions required by this AD following the 
instructions in Cessna Citation Service Bulletin No. SB525-27-17, 
dated December 9, 2003. The Director of the Federal Register 
approved the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a 
copy from The Cessna Aircraft Company, Product Support, P.O. Box 
7706, Wichita, Kansas 67277; telephone: (316) 517-6000; facsimile: 
(316) 517-8500. You may review copies at FAA, Central Region, Office 
of the Regional Counsel, 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.

    Issued in Kansas City, Missouri, on July 1, 2004.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 04-15666 Filed 7-12-04; 8:45 am]
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