6582 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations 

or at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on January 

24, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–1813 Filed 2–4–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28956; Directorate 

Identifier 2007–CE–068–AD; Amendment 

39–15360; AD 2008–03–10] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Models 525, 525A, 

and 525B Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Cessna) 

Models 525, 525A, and 525B airplanes. 

This AD requires you to inspect the 

lower wing skin structure, forward wing 

spar, lower fuselage skin, fairings, and 

the external fairing frames for corrosion; 

repair any damage found; apply a 

corrosion inhibitive sealant to the 

fuselage fairings before reinstalling; and 

disable the cockpit mounted pilot relief 

tube. This AD results from leaking of the 

cockpit mounted pilot relief tube, which 

caused corrosion of the airplane 

structure. We are issuing this AD to 

detect and correct any damage from 

corrosion of the airplane structure. 

Corrosion of the airplane structure 

could cause structural degradation and 

lead to structural failure of the airplane 

with consequent loss of control. 

DATES: This AD becomes effective on 

March 11, 2008. 

On March 11, 2008, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: For service information 

identified in this AD, contact Cessna 

Aircraft Company, Citation Marketing 

Division, P.O. Box 7706, Wichita, 

Kansas 67277; telephone: 1–800–835–

4090; fax: 1–800–517–8500. 

To view the AD docket, go to U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590, or on the Internet at http:// 

www.regulations.gov. The docket 

number is FAA–2007–28956; 

Directorate Identifier 2007–CE–068–AD. 

FOR FURTHER INFORMATION CONTACT: T.N. 

Baktha, Aerospace Engineer,1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946–

4155; fax: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On October 22, 2007, 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 October 26, 2007 (72 FR 60790). The 

NPRM proposed to require you to 

inspect the lower wing skin structure, 

forward wing spar, lower fuselage skin, 

fairings, and the external fairing frames 

for corrosion; repair any damage found; 

apply a corrosion inhibitive sealant to 

the fuselage fairings before reinstalling; 

and disable the cockpit mounted pilot 

relief tube. 

Comments 

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 

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. 

Costs of Compliance 

We estimate that this AD affects 261 

airplanes in the U.S. registry. 

We estimate the following costs to do 

the inspection: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

80 work-hours × $80 per hour = $6,400 ................................................... Not applicable .................................. $6,400 $1,670,400 

We have no way of determining the 

number of airplanes that may need 

repair or further inspection based on the 

results of the inspection, or the costs 

associated with such repair or 

inspection. 

We estimate the following costs to 

disable the cockpit mounted pilot relief 

tube: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

.5 work-hour × $80 per hour = $40 ........................................................... Not applicable .................................. $40 $10,440 

Cessna will provide warranty credit to 

the extent specified in Cessna Citation 

Service Bulletin SB525–53–20, dated 

April 30, 2007; Cessna Citation Service 

Bulletin SB525A–53–01, dated April 30, 

2007; Cessna Citation Service Bulletin 

SB525B–53–01, dated April 30, 2007; 

Cessna Citation Alert Service Letter 

ASL525–53–04, Revision 2, dated 

August 19, 2007; Cessna Citation Alert 

Service Letter ASL525A–53–05, 

Revision 2, dated July 25, 2007; and 

Cessna Citation Alert Service Letter 

ASL525B–53–02, Revision 2, dated July 

25, 2007. 

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 


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Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations 6583 

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 AD. 

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 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 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD (and other 

information as included in the 

Regulatory Evaluation) 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 ‘‘Docket No. FAA–2007–28956; 

Directorate Identifier 2007-CE–068-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 

■ 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 

■ 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. FAA amends § 39.13 by adding the 

following new AD: 

2008–03–10 Cessna Aircraft Company: 

Amendment 39–15360; Docket No. 

FAA–2007–28956; Directorate Identifier 

2007-CE–068-AD. 

Effective Date 

(a) This AD becomes effective on March 11, 

2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following 

airplane models and serial numbers that have 

a cockpit mounted pilot relief tube installed 

and are certificated in any category: 

Models Serial No. 

(1) 525 .......................... 0001 through 0637. 

(2) 525A ....................... 0001 through 0347. 

(3) 525B ....................... 0001 through 0152. 

Unsafe Condition 

(d) This AD results from leaking of the 

pilot relief tube, which caused corrosion of 

the airplane structure. We are issuing this AD 

to detect and correct any damage from 

corrosion on the airplane structure. Corrosion 

of the airplane structure could cause 

structural degradation and lead to structural 

failure of the airplane with consequent loss 

of control. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

TABLE 1.—ACTIONS, COMPLIANCE, AND PROCEDURES

Actions Compliance Procedures 

(1) Inspect the lower wing skin structure, forward wing spars, lower fuselage skin, fairings, and external fairing frames for corrosion.Within the next 90 days after March 11, 2008 

(the effective date of this AD).

Follow Cessna Citation Alert Service Letter 

ASL525–53–04, Revision 2, dated August 

19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 

25, 2007; or Cessna Citation Alert Service 

Letter ASL525B–53–02, Revision 2, dated 

July 25, 2007. 

(2) If corrosion damage is found in the lower 

wing skin structure, forward wing spars, 

lower fuselage skin, fairings, or external fairing frames during the inspection required in 

paragraph (e)(1) of this AD, repair as specified in the applicable service information. If 

the corrosion damage cannot be repaired 

within the limits specified in the applicable 

service information, contact the manufacturer 

at 1–800–835–4090 for an FAA-approved repair scheme and incorporate this repair.

Before further flight after the inspection required in paragraph (e)(1) of this AD.Follow Cessna Citation Alert Service Letter 

ASL525–53–04, Revision 2, dated August 

19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 

25, 2007; or Cessna Citation Alert Service 

Letter ASL525B–53–02, Revision 2, dated 

July 25, 2007. 

(3) If corrosion on the lower wing skin structure, forward wing spars, and lower fuselage 

skin was repaired by blending within the limits specified in the service information, do a 

surface eddy current inspection or a dyepenetrant inspection for cracks.

Before further flight after the repair by blending was done as specified in paragraph 

(e)(2) of this AD.

Follow Cessna Citation Alert Service Letter 

ASL525–53–04, Revision 2, dated August 

19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 

25, 2007; or Cessna Citation Alert Service 

Letter ASL525B–53–02, Revision 2, dated 

July 25, 2007. 

(4) If cracks are found during the surface eddy 

current inspection or the dye-penetrant inspection required in paragraph (e)(3) of this 

AD, contact the manufacturer for an FAA-approved repair scheme and incorporate this 

repair.

Before further flight after the inspection required in paragraph (e)(3) of this AD.Contact Cessna Aircraft Company, Citation 

Customer Support at 1–800–835–4090. 


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6584 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Rules and Regulations 

TABLE 1.—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued 

Actions Compliance Procedures 

(5) Install the fuselage fairings and apply corrosion inhibitive sealant.Before further flight after the inspection required in paragraph (e)(1) of this AD if no 

corrosion was found; or before further flight 

after doing the repairs and inspections required in paragraphs (e)(2), (e)(3), and 

(e)(4) of this AD if corrosion or cracks were 

found.

Follow Cessna Citation Alert Service Letter 

ASL525–53–04, Revision 2, dated August 

19, 2007; Cessna Citation Alert Service Letter ASL525A–53–05, Revision 2, dated July 

25, 2007; or Cessna Citation Alert Service 

Letter ASL525B–53–02, Revision 2, dated 

July 25, 2007. 

(6) Determine the type of installation of the 

cockpit mounted pilot relief tube and disable 

the relief tube.

Before further flight after the inspection required in paragraph (e)(1) of this AD.Cessna Citation Service Bulletin SB525–53–

20, dated April 30, 2007; Cessna Citation 

Service Bulletin SB525A–53–01, dated April 

30, 2007; or Cessna Citation Service Bulletin SB525B–53–01, dated April 30, 2007. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: T.N. 

Baktha, Wichita ACO, Aerospace Engineer, 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946–4155; 

fax: (316) 946–4107. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

Material Incorporated by Reference 

(g) You must use the service information 

specified in Table 2 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Cessna Aircraft Company, 

Citation Marketing Division, P.O. 7706, 

Wichita, Kansas 67277; telephone: 1–800–

835–4090; fax: 1–800–517–8500. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 2.—MATERIAL INCORPORATED BY REFERENCE

Service Bulletin No. Revision Date 

Cessna Citation Alert Service Letter ASL525–53–04 ..................................................................................... 2 August 19, 2007. 

Cessna Citation Alert Service Letter ASL525A–53–05 ................................................................................... 2 July 25, 2007. 

Cessna Citation Alert Service Letter ASL525B–53–02 ................................................................................... 2 July 25, 2007. 

Cessna Citation Service Bulletin SB525A–53–20 ........................................................................................... .................... April 30, 2007

Cessna Citation Service Bulletin SB525A–53–01 ........................................................................................... .................... April 30, 2007. 

Cessna Citation Service Bulletin SB525B–53–01 ........................................................................................... .................... April 30, 2007. 

Issued in Kansas City, Missouri, on January 

24, 2008. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–1821 Filed 2–4–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0100; Directorate 

Identifier 2007–SW–41–AD; Amendment 39–

15356; AD 2008–03–07] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Model AS 332 L2 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Model AS 332 L2 

helicopters. This AD results from 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority to identify and 

correct an unsafe condition on an 

aviation product. The European 

Aviation Safety Agency (EASA), the 

Technical Agent of France, with which 

we have a bilateral agreement, states in 

the MCAI: 

A borescope inspection during scheduled 

maintenance revealed wear on the internal 

skin of a Life Raft Inflation Cylinder, P/N 

41918001, that had been installed on a 

Eurocopter AS 332 L2 helicopter. The 

plunger tube end is fitted with a metal endfitting that presses against the internal 

surface of the cylinder due to its installation 

horizontally aboard the aircraft. Vibrations 

generated by helicopter operation are 

therefore causing such wear, which may 

result in a drop of internal pressure of the 

cylinder. This internal damage, if not 

corrected, could lead to functional failure of 

the cylinder, making the life raft inflation no 

longer possible. 

This AD requires actions that are 

intended to address the failure of a life 

raft to inflate during an emergency 

landing on water (ditching), which 

could result in loss of the crew and 

passengers. 

DATES: This AD becomes effective on 

February 20, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of Eurocopter Alert Service Bulletin No. 

05.00.71, dated July 31, 2007, as of 

February 20, 2008. 

We must receive comments on this 

AD by April 7, 2008. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 


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