49164 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations 

warning that an engine has failed, a 

warning system that is independent of 

the ATTCS must be provided to give the 

pilot a clear warning of any engine 

failure during go-around. 

Protection From Effects of HIRF 

Each electrical and electronic system 

that performs critical functions must be 

designed and installed to ensure that the 

operation and operational capability of 

these systems to perform critical 

functions are not adversely affected 

when the airplane is exposed to highintensity radiated fields external to the 

airplane. 

For the purpose of this special 

condition, the following definition 

applies: 

Critical Functions: Functions whose 

failure would contribute to or cause a 

failure condition that would prevent the 

continued safe flight and landing of the 

airplane.

Issued in Renton, Washington, on August 

12, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–16728 Filed 8–22–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2005–22145; Directorate 

Identifier 2005–NM–148–AD; Amendment 

39–14223; AD 2005–17–12] 

RIN 2120–AA64

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD requires inspecting 

to identify the wing anti-ice ducts 

(piccolo tubes) in the wing leading edge. 

For airplanes with affected piccolo 

tubes, this AD requires revising the 

airplane flight manual (AFM) to 

introduce new procedures for operation 

in icing conditions. The optional 

implementation of repetitive 

inspections for cracks of affected 

piccolo tubes, and corrective actions if 

necessary, terminates the operational 

limitations. The optional installation of 

certain new piccolo tubes terminates 

both the AFM revision and the 

inspections. This AD was prompted by 

reports of failed piccolo tubes. We are 

issuing this AD to prevent cracked 

piccolo tubes, which could result in air 

leakage, a possible adverse effect on the 

anti-ice air distribution pattern and antiice capability without annunciation to 

the flight crew, and consequent reduced 

controllability of the airplane.

DATES: This AD becomes effective 

September 7, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 7, 2005. 

We must receive comments on this 

AD by October 24, 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 Bombardier, Inc., 

Canadair, Aerospace Group, P.O. Box 

6087, Station Centre-ville, Montreal, 

Quebec H3C 3G9, Canada.

FOR FURTHER INFORMATION CONTACT: Dan 

Parrillo, Aerospace Engineer, Systems 

and Flight Test Branch, ANE–172, FAA, 

New York Aircraft Certification Office, 

1600 Stewart Avenue, suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7305; fax (516) 794–5531.

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the airworthiness 

authority for Canada, notified us that an 

unsafe condition may exist on certain 

Bombardier Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. TCCA advises that it has 

received reports of failed wing anti-ice 

ducts (piccolo tubes) located in the wing 

leading edge. De-icing capability was 

degraded on the wing that had the 

piccolo tube damage. Upon 

investigation, it has been determined 

that piccolo tubes manufactured since 

June 2000 are susceptible to cracking 

due to the process used to drill the air 

distribution holes. Such cracking may 

cause air leakage, a possible adverse 

effect on the anti-ice air distribution 

pattern and anti-ice capability without 

annunciation to the flight crew, and 

consequent reduced controllability of 

the airplane. 

Relevant Service Information 

Bombardier has issued Canadair 

Temporary Revision (TR) RJ/155, dated 

July 5, 2005, to the Canadair Regional 

Jet Airplane Flight Manual (AFM), CSP 

A–012. The TR introduces new 

procedures for operation in icing 

conditions. The TR revises the 

Operating Limitations and Abnormal 

Procedures sections of AFM CSP A–012 

to include new procedures for operation 

in icing conditions. 

Accomplishing the actions specified 

in the TR is intended to adequately 

address the unsafe condition. TCCA 

mandated the TR and issued Canadian 

airworthiness directive CF–2005–26, 

dated July 11, 2005, to ensure the 

continued airworthiness of these 

airplanes in Canada. 

Bombardier has also issued Service 

Bulletin 601R–30–029, Revision A, 

dated July 7, 2005. The service bulletin 

describes procedures for: 

• Repetitively inspecting, using 

fluorescent dye penetrant methods, the 

piccolo tubes to detect cracks. 

• Replacing cracked piccolo tubes 

with acceptable parts, or reinstalling 

cracked piccolo tubes under certain 

conditions. 

• Reporting the inspection results to 

the manufacturer. 

FAA’s Determination and Requirements 

of the Proposed AD 

This airplane model is manufactured 

in Canada and is type certificated for 

operation in the United States under the 

provisions of section 21.29 of the 

Federal Aviation Regulations (14 CFR 

21.29) and the applicable bilateral 

airworthiness agreement. Pursuant to 

this bilateral airworthiness agreement, 

TCCA has kept the FAA informed of the 

situation described above. We have 

examined TCCA’s findings, evaluated 

all pertinent information, and 

determined that we need to issue an AD 

for airplanes of this type design that are 

certificated for operation in the United 

States. 

Therefore, we are issuing this AD, 

which requires identifying the part and 

serial numbers of the piccolo tubes 

installed on the airplane. For airplanes 

Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations 49165

with affected piccolo tubes, the AD 

requires revising the AFM as specified 

previously. In addition, the optional 

implementation of the repetitive 

inspection program described 

previously terminates the operational 

limitations, provided operators comply 

with the exception described under 

‘‘Differences Between the AD and the 

Service Bulletin/Canadian 

Airworthiness Directive.’’ The optional 

installation of certain new piccolo tubes 

terminates both the AFM revision and 

the repetitive inspections. 

Differences Between the AD and the 

Service Bulletin/Canadian 

Airworthiness Directive 

The service bulletin specifies 

contacting the manufacturer for 

instructions on how to repair certain 

conditions, but this AD requires repair 

of those conditions using a method 

approved by the FAA or TCCA (or its 

delegated agent). In light of the type of 

repair required to address the unsafe 

condition, and consistent with existing 

bilateral airworthiness agreements, we 

have determined that, for this AD, a 

repair approved by the FAA or TCCA is 

acceptable for compliance with this AD.

The applicability of the Canadian 

airworthiness directive specifies serial 

numbers 7417 through 7990 inclusive, 

and 8000 and subsequent. However, this 

AD expands that applicability to 

include additional airplanes that have 

been recently identified as having the 

affected piccolo tube installed. We have 

been informed that the Canadian 

airworthiness directive and the service 

bulletin will be revised in the near 

future to incorporate this change. 

These differences have been 

coordinated with TCCA. 

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 in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2005–22145; Directorate Identifier 

2005–NM–148–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

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 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 may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov.

Examining the Docket 

You may 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 Docket 

Management System receives them. 

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 

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 and placed it in the AD docket. 

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

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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.

§ 39.13 [Amended]

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 by 

adding the following new airworthiness 

directive (AD):

2005–17–12 Bombardier, Inc. (Formerly 

Canadair): Amendment 39–14233. 

Docket No. FAA–2005–22145; 

Directorate Identifier 2005–NM–148–AD. 

Effective Date 

(a) This AD becomes effective September 7, 

2005.

Affected ADs 

(b) None. 

Applicability: (c) This AD applies to 

Bombardier Model CL–600–2B19 (Regional 

Jet Series 100 & 440) airplanes, certificated in 

any category, having the serial numbers 

listed below: 7013, 7017, 7037, 7046, 7059, 

7076, 7105, 7127, 7151, 7157, 7163, 7174, 

7179, 7203, 7204, 7228, 7271, 7347, 7362, 

7378, 7417 through 7990 inclusive, 8000 and 

subsequent. 

Unsafe Condition 

(d) This AD was prompted by reports of 

failed wing anti-ice ducts (piccolo tubes) in 

the leading edge of the wing. We are issuing 

this AD to prevent cracked piccolo tubes, 

49166 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations 

which could result in air leakage, a possible 

adverse effect on the anti-ice air distribution 

pattern and anti-ice capability without 

annunciation to the flight crew, and 

consequent reduced controllability 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 Bulletin References 

(f) For purposes of this AD, any reference 

to ‘‘the service bulletin’’ means the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–30–029, Revision A, 

dated July 7, 2005. 

Identification of Affected Piccolo Tubes 

(g) Before the airplane accumulates 3,000 

total flight hours, or within 14 days after the 

effective date of this AD, whichever occurs 

later: Determine whether any affected piccolo 

tube is installed on the airplane. Affected 

piccolo tubes are identified in paragraph 1.A. 

of the service bulletin. 

Revision to Aircraft Flight Manual (AFM) 

(h) For airplanes with an affected or 

unidentifiable piccolo tube: Before the 

airplane accumulates 3,000 total flight hours, 

or within 14 days after the effective date of 

this AD, whichever occurs later, revise the 

Operating Limitations and Abnormal 

Procedures sections of the Canadair Regional 

Jet AFM, CSP A–012, to include the 

information in Canadair Temporary Revision 

(TR) RJ/155, dated July 5, 2005, as specified 

in the TR. This may be done by inserting a 

copy of the TR into the AFM. This TR 

introduces new procedures for operation in 

icing conditions. Operate the airplane 

according to the limitations and procedures 

in the TR. When this TR has been included 

in general revisions of the AFM, the general 

revisions may be inserted in the AFM, 

provided the relevant information in the 

general revision is identical to that in the TR. 

Optional Inspections 

(i) For airplanes with an affected or 

unidentifiable piccolo tube: The operating 

limitations and abnormal procedures 

specified in the TR, as required by paragraph 

(h) of this AD, may be removed from the 

AFM, provided all requirements of this 

paragraph have been satisfied. 

(1) A fluorescent dye penetrant inspection 

for cracks of the piccolo tubes is done and 

repeated thereafter within 2,000-flight-hour 

intervals in accordance with the service 

bulletin. An inspection done before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 601R–30–029, 

dated June 17, 2005, is acceptable for 

compliance with the requirements of 

paragraph (i)(1) of this AD. 

(2) All applicable corrective actions are 

done as specified in paragraph (k) of this AD. 

(3) Applicable inspection reports are 

submitted as specified in paragraph (o) of 

this AD. 

AFM Limitations Required for Exceeding 

Inspection Interval 

(j) During any period in which the 

inspection interval exceeds 2,000 flight hours 

after the initial inspection specified in 

paragraph (i)(1) of this AD, the airplane must 

be operated under the limitations and 

abnormal procedures specified in paragraph 

(h) of this AD. 

Corrective Action 

(k) If any crack is found during any 

inspection required by paragraph (i) of this 

AD: Before further flight, do the actions 

specified in paragraph (k)(1), (k)(2), (k)(3), 

(k)(4), or (k)(5) of this AD, except as required 

by paragraph (l) of this AD.

(1) Replace the cracked piccolo tube, in 

accordance with the service bulletin, with a 

new piccolo tube that has the same part 

number as identified in paragraph 1.A. of the 

service bulletin but that does not have a 

serial number listed in that paragraph. 

(2) Replace the cracked piccolo tube, in 

accordance with the service bulletin, with a 

new piccolo tube that has a part number 

identified in the applicable Bombardier 

illustrated parts catalog but not identified in 

paragraph 1.A. of the service bulletin, or with 

a new piccolo tube identified in paragraph 

(m) of this AD. 

(3) Replace the cracked piccolo tube, in 

accordance with the service bulletin, with a 

piccolo tube that has been inspected in 

accordance with the service bulletin, is not 

cracked, and has not accumulated any air 

time (hours time-in-service) since inspection. 

(4) Replace the cracked piccolo tube with 

a piccolo tube that has been repaired in 

accordance with a method approved by 

either the Manager, New York Aircraft 

Certification Office (ACO), ANE–172, FAA; 

or Transport Canada Civil Aviation (TCCA) 

(or its delegated agent); and has not 

accumulated any air time (hours time-inservice) since the repair. 

(5) Reinstall the cracked piccolo tube and 

operate the airplane in accordance with a 

method approved by either the Manager, 

New York ACO, or TCCA (or its delegated 

agent). Operation in accordance with the 

provisions of Master Minimum Equipment 

List (MMEL) entry 30–12–03 is one 

acceptable method. 

Exception to Service Bulletin Procedures 

(l) Where the service bulletin specifies that 

Bombardier may be contacted for information 

regarding repair, this AD requires repair 

according to a method approved by either the 

Manager, New York ACO, or TCCA (or its 

delegated agent). 

Optional Terminating Action 

(m) Installation, in accordance with the 

service bulletin, of a complete set of new 

inboard, center, and outboard piccolo tubes, 

as identified in paragraphs (m)(1), (m)(2), and 

(m)(3) of this AD terminates the requirements 

of paragraphs (g), (h), (i), (j), and (k) of this 

AD. When these piccolo tubes have been 

installed, remove the Operating Limitations 

and Abnormal Procedures, if inserted in 

accordance with paragraph (h) of this AD, 

from the AFM. 

(1) For the inboard piccolo tube: P/N 601–

80032–7 (14432–107) and 601–80032–8 

(14432–108). 

(2) For the center piccolo tube: P/N 14464–

105 and 14464–106. 

(3) For the outboard piccolo tube: P/N 

14463–109 and 14463–110. 

Parts Installation 

(n) As of the effective date of this AD, no 

person may install, on any airplane, a piccolo 

tube having a P/N listed in listed in 

paragraph 1.A. of the service bulletin, unless 

the requirements of this AD have been 

accomplished for that piccolo tube. 

Report 

(o) For any inspection done in accordance 

with paragraph (i) of this AD: Submit a report 

of the inspection results (both positive and 

negative findings) in accordance with 

Appendix B of the service bulletin. 

Information collection requirements 

contained in this AD have been approved by 

the Office of Management and Budget (OMB) 

under the provisions of the Paperwork 

Reduction Act of 1980 (44 U.S.C. 3501 et 

seq.) and have been assigned OMB Control 

Number 2120–0056. 

(1) If the most recent inspection was done 

after the effective date of this AD: Submit the 

report within 10 days after the inspection. 

(2) If the most recent inspection was 

accomplished prior to the effective date of 

this AD: Submit the report within 10 days 

after the effective date of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(p) The Manager, New York ACO, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

Related Information 

(q) Canadian airworthiness directive CF–

2005–26, dated July 11, 2005, also addresses 

the subject of this AD. 

Material Incorporated by Reference 

(r) You must use Canadair Temporary 

Revision RJ/155, dated July 5, 2005, to the 

Canadair Regional Jet Airplane Flight 

Manual, CSP A–012; and Bombardier Service 

Bulletin 601R–30–029, Revision A, dated 

July 7, 2005, including Appendix A, dated 

June 17, 2005, and Appendix B, Revision A, 

dated July 7, 2005; to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. For 

a copy of this service information, contact 

Bombardier, Inc., Canadair, Aerospace 

Group, P.O. Box 6087, Station Centre-ville, 

Montreal, Quebec H3C 3G9, Canada. You 

may review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., Room PL–401, 

Nassif Building, Washington, DC; on the 

Internet at http://dms.dot.gov; or at 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 http://

www.archives.gov/federal_register/

Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations 49167

code_of_federal_regulations/

ibr_locations.html.

Issued in Renton, Washington, on August 

11, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–16533 Filed 8–22–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2005–21109; Directorate 

Identifier 2005–CE–21–AD; Amendment 39–

14232; AD 2005–17–11] 

RIN 2120–AA64

Airworthiness Directives; The Cessna 

Aircraft Company Models 525, 525A, 

and 525B Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

The Cessna Aircraft Company (Cessna) 

Models 525, 525A, and 525B airplanes. 

This AD requires you to install 

identification sleeves on the wiring for 

both engine fire extinguisher bottles. 

This AD results from reports of 

incorrectly connecting wires to the 

engine fire extinguisher bottles. We are 

issuing this AD to prevent incorrect 

installation of the wires to the engine 

fire extinguisher bottles, which could 

result in failure of the engine fire 

extinguisher bottles to discharge when 

activated. This failure could lead to the 

inability to control an engine fire.

DATES: This AD becomes effective on 

October 7, 2005. 

As of October 7, 2005, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation.

ADDRESSES: To get the service 

information identified in this AD, 

contact The Cessna Aircraft Company, 

Citation Marketing Division, Product 

Support, P.O. Box 7706, Wichita, 

Kansas 67277; telephone: (316) 517–

6000; facsimile: (316) 517–8500. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http://

dms.dot.gov. The docket number is 

FAA–2005–21109; Directorate Identifier 

2005–CE–21–AD.

FOR FURTHER INFORMATION CONTACT:

James P. Galstad, Aerospace Engineer, 

FAA, Wichita ACO, 1801 Airport Road, 

Mid-Continent Airport, Wichita, Kansas 

67209; telephone: (316) 946–4135; 

facsimile: (316) 946–4107.

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD?

Wires connected to the engine fire 

extinguisher bottles on Cessna Models 

525B and 560XL airplanes were found 

reversed. Installing the wiring in an 

incorrect configuration resulted from a 

lack of clarity in the wiring schematics 

for connecting the wires and testing the 

connections. 

The same lack of clarity in the wiring 

schematics for connecting the wires and 

testing the connections also exists for 

Cessna Models 525 and 525A airplanes. 

An incorrect wiring configuration 

installation could go undetected 

because the existing circuit checks 

appear normal during routine checks. 

However, the engine fire extinguisher 

bottles will not discharge when 

activated. 

What is the potential impact if FAA 

took no action? If not detected and 

corrected, incorrect wiring of the engine 

fire extinguisher bottles could result in 

failure of the engine fire extinguisher 

bottles to discharge when activated. 

This failure could lead to the inability 

to control an engine fire. 

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 Models 525, 525A, and 525B 

airplanes. This proposal was published 

in the Federal Register as a notice of 

proposed rulemaking (NPRM) on May 

19, 2005 (70 FR 28857). The NPRM 

proposed to require you to do the 

following:

—Install identification sleeves on wires 

connecting to the engine fire 

extinguisher bottles; 

—Reconnect the wires to the engine fire 

extinguisher bottles; and 

—Test the wiring for correct 

installation. 

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 

578 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 do the modification:

Labor cost Parts cost Total cost 

per airplane 

Total cost on U.S.

operators 

4 workhours × $65 per hour = $260 ................................................................... Not applicable ....... $260 $260 × 578 = $150,280. 

Cessna will provide warranty credit 

for the modification to the extent stated 

in the supplemental data to the service 

information. 

Authority for This Rulemaking 

What authority does FAA have for 

issuing this rulemaking action? Title 49