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