Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 43621 

The authority citation for these 

special conditions is as follows: 

Authority 49 U.S.C. 106(g), 40113, and 

44701; 14 CFR 21.16 and 21.17; 14 CFR 11.38 

and 11.19. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for Cessna Aircraft 

Company, model 525C (CJ4) airplanes. 

Cessna Aircraft Company, model 

525C (CJ4) Li-ion battery installation. 

In lieu of the requirements of 14 CFR 

part 23, § 23.1353 (a) through (e), Li-ion 

batteries and battery installations on the 

Cessna Aircraft Company, model 525C 

(CJ4) airplane must be designed and 

installed as follows: 

(1) Safe cell temperatures and 

pressures must be maintained during 

any probable charging or discharging 

condition, or during any failure of the 

charging or battery monitoring system 

not shown to be extremely remote. The 

Li-ion battery installation must be 

designed to preclude explosion or fire in 

the event of those failures. 

(2) Li-ion batteries must be designed 

to preclude the occurrence of selfsustaining, uncontrolled increases in 

temperature or pressure. 

(3) No explosive or toxic gasses 

emitted by any Li-ion battery in normal 

operation or as the result of any failure 

of the battery charging or monitoring 

system, or battery installation not 

shown to be extremely remote, may 

accumulate in hazardous quantities 

within the airplane. 

(4) Li-ion batteries that contain 

flammable fluids must comply with the 

flammable fluid fire protection 

requirements of 14 CFR part 23, 

§ 23.863(a) through (d). 

(5) No corrosive fluids or gasses that 

may escape from any Li-ion battery may 

damage surrounding airplane structure 

or adjacent essential equipment. 

(6) Each Li-ion battery installation 

must have provisions to prevent any 

hazardous effect on structure or 

essential systems that may be caused by 

the maximum amount of heat the 

battery can generate during a short 

circuit of the battery or of its individual 

cells. 

(7) Li-ion battery installations must 

have a system to control the charging 

rate of the battery automatically, so as 

to prevent battery overheating or 

overcharging, and 

(i) A battery temperature sensing and 

over-temperature warning system with a 

means for automatically disconnecting 

the battery from its charging source in 

the event of an over-temperature 

condition, or, 

(ii) A battery failure sensing and 

warning system with a means for 

automatically disconnecting the battery 

from its charging source in the event of 

battery failure. 

(8) Any Li-ion battery installation 

whose function is required for safe 

operation of the airplane, must 

incorporate a monitoring and warning 

feature that will provide an indication 

to the appropriate flight crewmembers, 

whenever the capacity and SOC of the 

batteries have fallen below levels 

considered acceptable for dispatch of 

the airplane. 

(9) The Instructions for Continued 

Airworthiness (ICAW) must contain 

recommended manufacturers 

maintenance and inspection 

requirements to ensure that batteries, 

including single cells, meet a safety 

function level essential to the aircraft’s 

continued airworthiness. 

(i) The ICAW must contain operating 

instructions and equipment limitations 

in an installation maintenance manual. 

(ii) The ICAW must contain 

installation procedures and limitation in 

a maintenance manual, sufficient to 

ensure that cells or batteries, when 

installed according to the installation 

procedures, still meet safety functional 

levels, essential to the aircraft’s 

continued airworthiness. The limitation 

must identify any unique aspects of the 

installation. 

(iii) The ICAW must contain 

corrective maintenance procedures to 

functionally check battery capacity at 

manufacturers recommended inspection 

intervals. 

(iv) The ICAW must contain 

scheduled servicing information to 

replace batteries at manufacturers 

recommended replacement time. 

(v) The ICAW must contain 

maintenance inspection requirements to 

visually check for a battery and/or 

charger degradation. 

(10) The ICAW must contain 

requirements that batteries in a rotating 

stock (spares) that have experienced 

degraded charge retention capability or 

other damage due to prolonged storage 

must be functionally checked at 

manufacturers recommended inspection 

intervals before installation. 

(11) The System Safety Assessment 

process must address the software and 

complex hardware levels for the 

sensing, monitoring and warning 

systems, if these systems contain 

complex devices. The functional hazard 

assessment (FHA) for the system is 

required based on the intended 

functions described. The criticality of 

the specific functions will be 

determined by the safety assessment 

process for compliance with 14 CFR 

part 23, § 23.1309, and Advisory 

Circular 23.1309–1D contains 

acceptable means for accomplishing this 

requirement. For determining the failure 

condition, the criticality of a function 

will include the mitigating factors. The 

failure conditions must address the loss 

of function and improper operations. 

These special conditions are not 

intended to replace 14 CFR part 23, 

§ 23.1353 in the certification basis of the 

Cessna Aircraft Company, model 525C 

(CJ4) airplanes. These special conditions 

apply only to Li-ion batteries and 

battery installations. The battery 

requirements of 14 CFR part 23, 

§ 23.1353 would remain in effect for 

batteries and battery installations on the 

Cessna Aircraft Company, model 525C 

(CJ4) airplane that do not use Li-ion 

chemistry. 

Issued in Kansas City, Missouri, on August 

19, 2009. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E9–20726 Filed 8–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28035; Directorate 

Identifier 2006–NM–293–AD; Amendment 

39–15998; AD 2009–18–02] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 767 airplanes. This AD 

requires sealing certain fasteners and 

stiffeners in the fuel tank, changing 

certain wire bundle clamp 

configurations on the fuel tank walls, 

inspecting certain fasteners in the fuel 

tanks and to determine the method of 

attachment of the vortex generators, and 

corrective action if necessary. This AD 

results from fuel system reviews 

conducted by the manufacturer. We are 

issuing this AD to prevent possible 

ignition sources in the auxiliary fuel 

tank, main fuel tanks, and surge tanks 

caused by a wiring short or lightning 

strike, which could result in fuel tank 


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43622 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 

explosions and consequent loss of the 

airplane. 

DATES: This AD becomes effective 

October 1, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 1, 2009. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Douglas Bryant, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6505; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that would apply to certain Boeing 

Model 767 airplanes. That supplemental 

NPRM was published in the Federal 

Register on October 16, 2008 (73 FR 

61378). That supplemental NPRM 

proposed to require sealing certain 

fasteners and stiffeners in the fuel tank, 

changing certain wire bundle clamp 

configurations on the fuel tank walls, 

inspecting additional fasteners in the 

fuel tanks and to determine the method 

of attachment of the vortex generators, 

and corrective action if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received on 

the supplemental NPRM. 

Support for the NPRM 

Boeing concurs with the contents of 

the NPRM. 

Request for Final Rule To Include 

Reference to Supplemental Type 

Certificate (STC) ST01920SE 

Delta requests that the final rule 

include a reference to STC ST01920SE, 

dated October 15, 2008, which installs 

winglets on certain Boeing 767 airplanes 

that have similar fastener sealing 

requirements in coincidental locations 

defined in the proposed AD. Delta states 

that including the specific common 

areas of the referenced STC in the final 

rule would simplify compliance if the 

STC has already been incorporated, and 

also preclude de-modification if the STC 

is incorporated after the AD. 

We partially agree with the 

commenter’s statement. The 

requirements for fasteners that penetrate 

the fuel tank are the same in both the 

STC and AD. We disagree with 

referencing the STC in the AD because 

there is insufficient information 

contained in the request to identify the 

specific areas that are common between 

the STC and AD. However, the 

commenter may formally request an 

approval for an alternative method of 

compliance, as provided by paragraph 

(h) of this AD, if the request includes 

more specific information to enable us 

to determine whether the proposed 

method would provide an adequate 

level of safety. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD as proposed in the supplemental 

NPRM. 

Costs of Compliance 

There are about 925 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. There are no U.S.- 

registered airplanes in Group 3 of 

Boeing Service Bulletin 767–57A0102. 

The average labor rate is $80 per work 

hour. 

ESTIMATED COSTS

Boeing Service Bulletin Group Work hours Parts Cost per 

airplane 

Number of 

U.S.-registered airplanes 

Fleet cost 

767–57A0100 ................................................................. 1 6 minimal .... $480 341 $163,680 

2 114 minimal .... 9,120 21 191,520 

3 1 none ........ 80 17 1,360 

767–57A0102 ................................................................. 1 246 1,632 ....... 21,312 341 7,267,392 

2 874 1,304 ....... 71,224 21 1,495,704 

3 24 338 ........... 2,258 0 0 

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 


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Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 43623 

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 

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): 

2009–18–02 Boeing: Amendment 39–15998. 

Docket No. FAA–2007–28035; 

Directorate Identifier 2006–NM–293–AD. 

Effective Date 

(a) This AD becomes effective October 1, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model 767–200, 

–300, –300F, and –400ER series airplanes; 

certificated in any category; as identified in 

Boeing Service Bulletin 767–57A0100, 

Revision 1, dated June 19, 2008; and Boeing 

Service Bulletin 767–57A0102, Revision 1, 

dated November 27, 2007. 

Unsafe Condition 

(d) This AD results from fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent possible 

ignition sources in the auxiliary fuel tank, 

main fuel tanks, and surge tanks caused by 

a wiring short or lightning strike, which 

could result in fuel tank explosions and 

consequent loss 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. 

Fastener Sealant Application 

(f) For airplanes identified in Boeing 

Service Bulletin 767–57A0100, Revision 1, 

dated June 19, 2008: Within 60 months after 

the effective date of this AD, do the actions 

in paragraphs (f)(1) and (f)(2) of this AD in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0100, Revision 1, dated June 19, 2008, as 

applicable. 

(1) For Groups 1 and 2 airplanes: Seal the 

ends of the fasteners on the brackets that 

hold the vortex generators, and seal the ends 

of the fasteners on certain stiffeners on the 

rear spar, as applicable. 

(2) For Group 3 airplanes: Do a detailed 

inspection to determine the method of 

attachment of the vortex generators and, 

before further flight, do all applicable 

specified corrective actions. 

Wire Bundle Sleeve and Clamp Installation 

and Fastener Sealant Application 

(g) For airplanes identified in Boeing 

Service Bulletin 767–57A0102, Revision 1, 

dated November 27, 2007: Within 60 months 

after the effective date of this AD, do the 

actions specified in paragraphs (g)(1), (g)(2), 

and (g)(3) of this AD, as applicable, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

57A0102, Revision 1, dated November 27, 

2007. 

(1) Change the wire bundle clamp 

configurations at specified locations on the 

fuel tank walls. 

(2) Seal the fasteners and certain stiffeners 

at specified locations in the fuel tank. 

(3) Do a detailed inspection of the sealant 

of the fasteners in the auxiliary tank center 

bay and rib 28 of the left and right main fuel 

tanks. Seal any unsealed fasteners before 

further flight. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Douglas Bryant, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6505; fax (425) 

917–6590. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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 

(i) You must use the service information 

contained in Table 1 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Boeing Service Bulletin 767–57A0102 .......................................................................................................... 01 November 27, 2007. 

Boeing Service Bulletin 767–57A0100 .......................................................................................................... 01 June 19, 2008. 

(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 Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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. 


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43624 Federal Register / Vol. 74, No. 165 / Thursday, August 27, 2009 / Rules and Regulations 

Issued in Renton, Washington, on August 

7, 2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–20274 Filed 8–26–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0489; Directorate 

Identifier 2009–CE–025–AD; Amendment 

39–16000; AD 2009–18–04] 

RIN 2120–AA64 

Airworthiness Directives; Air Tractor, 

Inc. Models AT–802 and AT–802A 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Air Tractor, Inc. Models AT–802 and 

AT–802A airplanes. This AD requires 

installing a rudder-aileron interconnect 

cable system shield kit and securing any 

items stowed in the baggage 

compartment, using tie downs and/or a 

cargo net until the cable shield kit is 

installed. We are issuing this AD to 

prevent jamming of the rudder-aileron 

interconnect cables by unsecured items 

in the baggage compartment, which 

could result in failure of the rudderaileron interconnect cable system. This 

failure could lead to loss of control. 

DATES: This AD becomes effective on 

October 1, 2009. 

On October 1, 2009, 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 Air 

Tractor, Inc., P.O. Box 485, Olney, Texas 

76374; telephone: (940) 564–5616; 

facsimile: (940) 564–5612; E-mail: 

parts@airtractor.com; Internet: http:// 

www.airtractor.com. 

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–2009–0489; Directorate 

Identifier 2009–CE–025–AD. 

FOR FURTHER INFORMATION CONTACT: 

Andy McAnaul, Aerospace Engineer, 

10100 Reunion Pl., Ste. 650, San 

Antonio, Texas 78216; telephone: (210) 

308–3365; fax: (210) 308–3370. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 20, 2009, 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 Models AT–802 and AT–802A 

airplanes. This proposal was published 

in the Federal Register as a notice of 

proposed rulemaking (NPRM) on May 

29, 2009 (74 FR 25684). The NPRM 

proposed to require installing a rudderaileron interconnect cable system shield 

kit and securing any items stowed in the 

baggage compartment, using tie downs 

and/or a cargo net until the cable shield 

kit is installed. 

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 210 

airplanes in the U.S. registry. 

We estimate the following costs to do 

the modification: 

Labor cost Parts 

cost Total cost per airplane 

Total cost 

on U.S. 

operators 

Cable Shield Kit SL#274: 4.5 work-hours × $80 per hour = $360 ...................... $860 affects 170 airplanes at $1,220 each ... $207,400 

Cable Shield Kit SL#274–2: 4.5 work-hours × $80 per hour = $360 .................. 540 affects 40 airplanes at $900 each ........ 36,000 

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 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–2009–0489; 

Directorate Identifier 2009–CE–025– 

AD’’ in your request. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 


srobinson on DSKHWCL6B1PROD with RULES