Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / Rules and Regulations 32349 

A340–56–5002, Revision 01, including 

Appendix 01, dated February 8, 2012. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

applicable service information identified in 

paragraphs (i)(1) through (i)(4) of this AD, 

which are not incorporated by reference in 

this AD. 

(1) Airbus Service Bulletin A330–56–3009, 

dated May 4, 2010 (for Model A330–201, 

–202, –203, –223, –223F, –243, –243F, –301, 

–302, –303, –321, –322, –323, –341, –342, 

and –343 airplanes). 

(2) Airbus Service Bulletin A330–56–3009, 

Revision 01, dated January 27, 2011 (for 

Model A330–201, –202, –203, –223, –223F, 

–243, –243F, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes). 

(3) Airbus Service Bulletin A340–56–4008, 

dated May 4, 2010 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes). 

(4) Airbus Service Bulletin A340–56–5002, 

dated May 4, 2010 (for Model A340–541 and 

–642 airplanes). 

(j) Parts Installation Limitation 

As of the effective date of this AD, do not 

install on an airplane any affected 

windshield from SGS having a part number 

and serial number identified in the 

applicable service information identified in 

paragraphs (j)(1), (j)(2), and (j)(3) of this AD, 

unless a suffix ‘‘U’’ is present at the end of 

the serial number. 

(1) For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes: 

Airbus Mandatory Service Bulletin A330–56– 

3009, Revision 02, including Appendix 01, 

dated February 8, 2012. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Mandatory 

Service Bulletin A340–56–4008, Revision 01, 

including Appendix 01, dated February 8, 

2012. 

(3) For Model A340–541 and –642 

airplanes: Airbus Mandatory Service Bulletin 

A340–56–5002, Revision 01, including 

Appendix 01, dated February 8, 2012. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2011–0242, dated December 19, 

2011 (corrected February 15, 2012), and the 

service information identified in paragraphs 

(l)(1)(i) through (l)(1)(iii) of this AD, for 

related information. 

(i) Airbus Mandatory Service Bulletin 

A330–56–3009, Revision 02, including 

Appendix 01, dated February 8, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A340–56–4008, Revision 01, including 

Appendix 01, dated February 8, 2012. 

(iii) Airbus Mandatory Service Bulletin 

A340–56–5002, Revision 01, including 

Appendix 01, dated February 8, 2012. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

review copies of the referenced 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. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Airbus Mandatory Service Bulletin 

A330–56–3009, Revision 02, including 

Appendix 01, dated February 8, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A340–56–4008, Revision 01, including 

Appendix 01, dated February 8, 2012. 

(iii) Airbus Mandatory Service Bulletin 

A340–56–5002, Revision 01, including 

Appendix 01, dated February 8, 2012. 

(3) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on May 16, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–12519 Filed 5–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1001; Directorate 

Identifier 2012–NM–020–AD; Amendment 

39–17453; AD 2013–09–11] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company Model 500, 

501, 550, 551, S550, 560, 560XL, and 

650 airplanes. This AD was prompted 

by multiple reports of smoke and/or fire 

in the tailcone caused by sparking due 

to excessive wear of the brushes in the 

air conditioning (A/C) motor. This AD 

requires inspecting to determine if 

certain A/C compressor motors are 

installed and to determine the 

accumulated hours on certain A/C drive 

motor assemblies; repetitive 

replacement of the brushes in the drive 

motor assembly, or, as an option to the 

brush replacement, deactivation of the 

A/C system and placard installation; 

and return of replaced brushes to 

Cessna. We are issuing this AD to 

prevent the brushes in the A/C motor 

from wearing down beyond their limits, 

which could result in the rivet in the 

brush contacting the commutator 

causing sparks and consequent fire and/ 

or smoke in the tailcone with no means 

to detect or extinguish the fire and/or 

smoke. 

DATES: This AD is effective July 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Cessna 


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Aircraft Co., P.O. Box 7706, Wichita, KS 

67277; telephone 316–517–6215; fax 

316–517–5802; email 

citationpubs@cessna.textron.com; 

Internet https:// 

www.cessnasupport.com/newlogin.html. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

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 (phone: 800–647–5527) is 

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: 

Christine Abraham, Aerospace Engineer, 

Electrical Systems and Avionics Branch, 

ACE–119W, FAA, Wichita Aircraft 

Certification Office (ACO), 1801 Airport 

Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; phone: 

316–946–4165; fax: 316–946–4107; 

email: wichita-cos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on February 11, 2013 (78 FR 

9636). The original NPRM (77 FR 59146, 

September 26, 2012) proposed to require 

an inspection to determine if certain 

A/C compressor motors are installed 

and to determine the accumulated hours 

on certain A/C drive motor assemblies; 

repetitive replacement of the brushes in 

the drive motor assembly, or, as an 

option to the brush replacement, 

deactivation of the A/C system and 

placard installation; and return of 

replaced brushes to Cessna. The SNPRM 

proposed to revise the optional A/C 

system deactivation procedure. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(78 FR 9636, February 11, 2013) or on 

the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (78 FR 

9636, February 11, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (78 FR 9636, 

February 11, 2013). 

Interim Action 

We consider this AD interim action. 

The reporting data required by this AD 

will enable us to obtain better insight 

into brush wear. The reporting data will 

also indicate if the replacement 

intervals we established are adequate. 

After we analyze the reporting data 

received, we might consider further 

rulemaking. 

Model 525 airplanes are not subject to 

this AD. We are currently considering 

requiring similar actions for these 

airplanes. 

Costs of Compliance 

We estimate that this AD will affect 

1,987 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection, drive motor assembly brush replacement, parts return, and reporting.11 work-hours × $85 

per hour = $935 per 

replacement cycle.

$252 per replacement 

cycle.

$1,187 per replacement cycle.$2,358,569 per replacement cycle. 

Optional fabrication of placard for deactivation.1 work-hour × $85 per 

hour = $85.

$0 ............................... $85 ............................. $168,895. 

Optional deactivation or reactivation for 

Model 560XL airplanes (370 airplanes).

1 work-hour × $85 per 

hour = $85.

$0 ............................... $85 ............................. $31,450. 

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 

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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 


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Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / Rules and Regulations 32351 

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 FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2013–09–11 Cessna Aircraft Company: 

Amendment 39–17453; Docket No. 

FAA–2012–1001; Directorate Identifier 

2012–NM–020–AD. 

(a) Effective Date 

This AD is effective July 5, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Cessna 

Aircraft Company airplanes, certificated in 

any category. 

(1) Model 500 and 501 airplanes, serial 

numbers (S/N) 0001 through 0689 inclusive. 

(2) Model 550 and 551 airplanes, S/Ns 

0002 through 0733 inclusive, and 0801 

through 1136 inclusive. 

(3) Model S550 airplanes, S/Ns 0001 

through 0160 inclusive. 

(4) Model 560 airplanes, S/Ns 0001 

through 0707 inclusive, and 0751 through 

0815 inclusive. 

(5) Model 560XL airplanes, S/Ns 5001 

through 5300 inclusive. 

(6) Model 650 airplanes, S/Ns 0200 

through 0241 inclusive, and 7001 through 

7119 inclusive. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 21, Air Conditioning. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of smoke and/or fire in the tailcone caused 

by sparking due to excessive wear of the 

brushes in the air conditioning (A/C) motor. 

We are issuing this AD to prevent the brushes 

in the A/C motor from wearing down, which 

could result in the rivet in the brush 

contacting the commutator causing sparks 

and consequent fire and/or smoke in the 

tailcone with no means to detect or 

extinguish the fire and/or smoke. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection for Part Number (P/N) 

Within 30 days or 10 flight hours after the 

effective date of this AD, whichever occurs 

first: Inspect the A/C compressor motor to 

determine whether P/N 1134104–1 or P/N 

1134104–5 is installed. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the part number of the 

A/C compressor motor can be conclusively 

determined from that review. 

(h) Inspection of Compressor Hour Meter 

and Maintenance Records 

If, during the inspection required by 

paragraph (g) of this AD, any A/C compressor 

motor is found having P/N 1134104–1 or 

P/N 1134104–5: Within 30 days or 10 flight 

hours after the effective date of this AD, 

whichever occurs first, determine the hour 

reading on the A/C compressor hour meter as 

specified in paragraphs (h)(1) and (h)(2) of 

this AD. 

(1) Inspect the number of hours on the 

A/C compressor hour meter. And, 

(2) Check the airplane logbook for any 

entry for replacing the A/C compressor motor 

brushes with new brushes, or for replacing 

the compressor motor or compressor 

condenser module assembly (pallet) with a 

motor or assembly that has new brushes. 

(i) If the logbook contains an entry for 

replacement of parts, as specified in 

paragraph (h)(2) of this AD, determine the 

number of hours on the A/C compressor 

motor brushes by comparing the number of 

hours on the compressor motor since 

replacement and use this number in lieu of 

the number determined in paragraph (h)(1) of 

this AD. Or, 

(ii) If, through the logbook check you 

cannot positively determine the number of 

hours on the A/C compressor motor brushes, 

as specified in paragraph (h)(2) of this AD, 

use the number of hours on the A/C 

compressor hour meter determined in 

paragraph (h)(1) of this AD or presume the 

brushes have over 500 hours time-in-service. 

(i) Replacement 

Using the hour reading on the A/C 

compressor hour meter determined in 

paragraph (h) of this AD, replace the A/C 

compressor motor brushes with new brushes 

at the later of the times specified in 

paragraphs (i)(1) and (i)(2) of this AD. 

Thereafter, repeat the replacement of the 

A/C compressor motor brushes at intervals 

not to exceed 500 hours time-in-service on 

the A/C compressor motor. Do the 

replacement in accordance with the 

applicable Cessna maintenance manual 

subject specified in paragraphs (j)(1) through 

(j)(7) of this AD. 

(1) Before the accumulation of 500 total 

hours time-in-service on the A/C compressor 

motor. 

(2) Before further flight after doing the 

inspection required in paragraph (h) of this 

AD. 

(j) Replacement Maintenance Manual 

Information 

Use the instructions in the applicable 

Cessna maintenance manual subject specified 

in paragraphs (j)(1) through (j)(7) of this AD 

to do the replacement required by paragraph 

(i) of this AD. 

(1) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 10, dated April 23, 

2012, of the Cessna Model 550 Bravo 

Maintenance Manual. 

(2) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 8, dated April 23, 2012, 

of the Cessna Model 550Maintenance 

Manual. 

(3) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 20, dated April 23, 

2012, of the Cessna Model 560 Maintenance 

Manual. 

(4) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 13, dated April 23, 

2012, of the Cessna Model 

560XLMaintenance Manual. 

(5) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 30, dated April 23, 

2012, of the Cessna Model 650 Maintenance 

Manual. 

(6) Subject 4–11–00, Replacement Time 

Limits-General, of Chapter 4, Airworthiness 

Limitations, Revision 4, dated April 23, 2012, 

of the Cessna Model 500/501Maintenance 

Manual. 

(7) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 7, dated April 23, 2012, 

of the Cessna Model S550 Maintenance 

Manual. 

(k) Deactivation of A/C System 

In lieu of replacing the A/C compressor 

motor brushes as required by this AD, 

deactivate the A/C system as specified in 

paragraph (k)(1), (k)(2), or (k)(3) of this AD, 

as applicable. 

(1) For all airplanes except Model 560XL 

and 650 airplanes: Pull the vapor cycle A/C 

circuit breaker labeled ‘‘AIR COND,’’ do the 

actions specified in paragraphs (k)(1)(i) and 

(k)(1)(ii) of this AD, and document 

deactivation of the system in the airplane 

logbook, referring to this AD as the reason for 

deactivation. While the system is 

deactivated, the airplane operator must 

remain aware of operating temperature 

limitations specified in the applicable 

airplane flight manual. 

(i) Fabricate a placard that states: ‘‘A/C 

DISABLED’’ with 1⁄8-inch black lettering on 

a white background. 

(ii) Install the placard on the airplane 

instrument panel within 6 inches of the 

A/C selection switch. 

(2) For Model 650 airplanes: Pull the vapor 

cycle A/C circuit breaker labeled ‘‘FWD 

EVAP FAN,’’ do the actions specified in 

paragraphs (k)(1)(i) and (k)(1)(ii) of this AD, 

and document deactivation of the system in 

the airplane logbook, referring to this AD as 

the reason for deactivation. While the system 

is deactivated, the airplane operator must 

remain aware of operating temperature 

limitations specified in the applicable 

airplane flight manual. 

(3) For Model 560XL airplanes: Do the 

actions specified in paragraphs (k)(1)(i) and 

(k)(1)(ii) of this AD, and document 

deactivation of the system in the airplane 

logbook, referring to this AD as the reason for 


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deactivation. While the system is 

deactivated, the airplane operator must 

remain aware of operating temperature 

limitations specified in the applicable 

airplane flight manual. Remove the fuse 

limiter that supplies power to the A/C 

compressor motor by doing the actions 

specified in paragraphs (k)(3)(i) through 

(k)(3)(viii) of this AD, and return to the 

airplane to service by doing the actions 

specified in paragraphs (k)(3)(ix) through 

(k)(3)(xiii) of this AD. 

(i) Open the battery door. 

(ii) Disconnect the main battery connector 

and remove external electrical power. 

(iii) Tag the battery and external power 

receptacle with a warning tag that reads: 

‘‘WARNING: Do not connect the battery 

connector during the maintenance in 

progress.’’ 

(iv) Gain access to the J-Box through the 

tailcone access door. 

(v) Remove the wing nuts that attach the 

cover to the J-Box. 

(vi) Remove the J-Box cover. 

(vii) Remove nuts securing compressor fuse 

limiter (reference designator HZ116, P/N 

ANL130) to the bus bar. 

(viii) Remove the compressor motor fuse 

limiter from the terminals and retain for 

future reinstallation once the compressor 

motor brushes have been replaced. 

(ix) Install fuse limiter nuts on the 

terminals and torque to 100 inch-pounds 

+/– 5 inch-pounds. 

(x) Install the J-Box cover with wing nuts. 

(xi) Remove the warning tag on the battery 

and external power receptacle. 

(xii) Connect the battery and restore 

electrical power to the airplane. 

(xiii) Close the tailcone access door. 

(l) Reactivation of A/C System 

If an operator chooses to deactivate the 

A/C system, as specified in paragraph (k) of 

this AD, and then later chooses to return the 

A/C system to service: Before returning the 

A/C system to service and removing the 

placard, perform the inspection specified in 

paragraph (h) of this AD, and do the 

replacements specified in paragraph (i) of 

this AD, at the times specified in paragraph 

(i) of this AD. Return the A/C system to 

service by doing the actions specified in 

paragraph (l)(1), (l)(2), or (l)(3) of this AD, as 

applicable. 

(1) For all airplanes except Model 560XL 

and 650 airplanes: Push in the vapor cycle 

A/C circuit breaker labeled ‘‘AIR COND,’’ 

remove the placard by the A/C selection 

switch that states ‘‘A/C DISABLED,’’ and 

document reactivation of the system in the 

airplane logbook. 

(2) For Model 650 airplanes: Push in the 

vapor cycle A/C circuit breaker labeled 

‘‘FWD EVAP FAN,’’ remove the placard by 

the A/C selection switch that states ‘‘A/C 

DISABLED,’’ and document reactivation of 

the system in the airplane logbook. 

(3) For Model 560XL airplanes: Remove the 

placard by the A/C selection switch that 

states ‘‘A/C DISABLED,’’ and document 

reactivation of the system in the airplane 

logbook. Re-install the fuse limiter by doing 

the actions specified in paragraphs (l)(3)(i) 

through (l)(3)(viii) of this AD, and return to 

the airplane to service by doing the actions 

specified in paragraphs (l)(3)(ix) through 

(l)(3)(xiii) of this AD. 

(i) Open the battery door. 

(ii) Disconnect the main battery connector 

and remove external electrical power. 

(iii) Tag the battery and external power 

receptacle with a warning tag that reads: 

‘‘WARNING: Do not connect the battery 

connector during the maintenance in 

progress.’’ 

(iv) Gain access to the J-Box through the 

tailcone access door. 

(v) Remove the wing nuts that attach the 

cover to the J-Box. 

(vi) Remove the J-Box cover. 

(vii) Remove the fuse limiter nuts on the 

bus bar terminals for the fuse limiter. 

(viii) Install the compressor motor fuse 

limiter (reference designator HZ116, P/N 

ANL130). 

(ix) Install fuse limiter nuts on the 

terminals and torque to 100 inch-pounds 

+/– 5 inch-pounds. 

(x) Install the J-Box cover with wing nuts. 

(xi) Remove the warning tag on the battery 

and external power receptacle. 

(xii) Connect the battery and restore 

electrical power to the airplane. 

(xiii) Close the tailcone access door. 

(m) Parts Return and Reporting 

Requirements 

For the first two A/C compressor motor 

brush replacement cycles on each airplane, 

send the brushes that were removed to 

Cessna Aircraft Company, Cessna Service 

Parts and Programs, 7121 Southwest 

Boulevard, Wichita, KS 67215. Provide the 

brushes and the information specified in 

paragraphs (m)(1) through (m)(6) of this AD 

within 30 days after the replacement, if the 

replacement was done on or after the 

effective date of this AD, or within 30 days 

after the effective date of this AD, if the 

replacement was done before the effective 

date of this AD. 

(1) The model and serial number of the 

airplane. 

(2) The part number of the motor. 

(3) The part number of the brushes, if 

known. 

(4) The elapsed amount of motor hours 

since the last brush/motor replacement, if 

known. 

(5) If motor hours are unknown, report the 

elapsed airplane flight hours since the last 

brush/motor replacement and indicate that 

motor hours are unknown. 

(6) The number of motor hours currently 

displayed on the pallet hour meter. 

(n) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install an A/C compressor motor 

having P/N 1134104–1 or P/N 1134104–5, 

unless the inspection specified in paragraph 

(h) of this AD is done before further flight, 

and the replacements specified in paragraph 

(i) of this AD are done at the times specified 

in paragraph (i) of this AD. 

(o) Special Flight Permit Limitation 

Operation of the A/C system is prohibited 

while flying with a special flight permit 

issued for this AD. 

(p) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) 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. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(r) Related Information 

For more information about this AD, 

contact Christine Abraham, Aerospace 

Engineer, Electrical Systems and Avionics 

Branch, ACE–119W, FAA, Wichita Aircraft 

Certification Office (ACO), 1801 Airport 

Road, Room 100, Mid-Continent Airport, 

Wichita, Kansas 67209; phone: 316–946– 

4165; fax: 316–946–4107; email: wichitacos@faa.gov. 

(s) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 10, dated April 23, 

2012, of the Cessna Model 550 Bravo 

Maintenance Manual. The revision level of 

Chapter 4 is identified only on the title page 

of Chapter 4. 

(ii) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 8, dated April 23, 2012, 

of the Cessna Model 550 Maintenance 

Manual. The revision level of Chapter 4 is 


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Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / Rules and Regulations 32353 

identified only on the title page of Chapter 

4. 

(iii) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 20, dated April 23, 

2012, of the Cessna Model 560 Maintenance 

Manual. The revision level of Chapter 4 is 

identified only on the title page of Chapter 

4. 

(iv) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 13, dated April 23, 

2012, of the Cessna Model 560XL 

Maintenance Manual. The revision level of 

Chapter 4 is identified only on the title page 

of Chapter 4. 

(v) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 30, dated April 23, 

2012, of the Cessna Model 650 Maintenance 

Manual. The revision level of Chapter 4 is 

identified only on the title page of Chapter 

4. 

(vi) Subject 4–11–00, Replacement Time 

Limits-General, of Chapter 4, Airworthiness 

Limitations, Revision 4, dated April 23, 2012, 

of the Cessna Model 500/501Maintenance 

Manual. The revision level of Chapter 4 is 

identified only on the title page of Chapter 

4. 

(vii) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 7, dated April 23, 2012, 

of the Cessna Model S550 Maintenance 

Manual. The revision level of Chapter 4 is 

identified only on the title page of Chapter 

4. 

(3) For Cessna service information 

identified in this AD, contact Cessna Aircraft 

Co., P.O. Box 7706, Wichita, KS 67277; 

telephone 316–517–6215; fax 316–517–5802; 

email citationpubs@cessna.textron.com; 

Internet https://www.cessnasupport.com/ 

newlogin.html. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on April 26, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–12662 Filed 5–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0426; Directorate 

Identifier 2013–NM–084–AD; Amendment 

39–17463; AD 2013–11–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

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 certain 

Bombardier, Inc. Model CL–215–1A10 

and CL–215–6B11 (CL–215T Variant) 

airplanes. This AD requires repetitive 

detailed inspections for cracking of the 

left-hand (LH) and right-hand (RH) wing 

lower skin, and repair if necessary. This 

AD also provides terminating action for 

the repetitive detailed inspections. This 

AD was prompted by reports of a 

fractured wing lower rear spar cap and 

reinforcing strap. We are issuing this AD 

to detect and correct cracked wing 

structure, which could result in failure 

of the wing. 

DATES: This AD becomes effective June 

14, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 14, 2013. 

We must receive comments on this 

AD by July 15, 2013. 

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. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7331; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Emergency 

Canadian Airworthiness Directive CF– 

2013–11, dated April 17, 2013 (referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

While performing modifications on a CL– 

215–1A10 aeroplane, an operator discovered 

that the wing lower rear spar cap and 

reinforcing strap were fractured at Wing 

Stations (WS) 49.5 and 50 respectively and 

the rear spar web and wing lower skin were 

also cracked. It is suspected that a crack 

initiated at the wing lower spar cap, leading 

to its failure, the subsequent failure of the 

reinforcing strap and cracking of the spar 

web and wing lower skin. The damage was 

outside of the area addressed by the 

repetitive ultrasonic inspections required by 

AD CF–1992–26R2 [which corresponds to 

FAA AD 2012–11–04, Amendment 39–17067 

(77 FR 32892, June 4, 2012)] and was found 

95 hours air time after the last ultrasonic 

inspection. 

Failure and cracking of the above-noted 

wing structure, if not detected, could result 

in failure of the wing. In order to mitigate the 

unsafe condition, this [Canadian] AD 

mandates a repetitive [detailed] visual 

inspection [for cracking] of the wing lower 

skin until an eddy current inspection [for 

cracking] of the [LH and RH wing lower front 

and rear] spar cap[s] is performed or a 

[detailed] visual inspection [for cracking] of 

the wing structures [i.e., the LH and RH wing 

lower skin, front and rear spar caps, front and 

rear spar webs, and reinforcing straps] is 

performed by removing the fuel bladder[, and 

repair if any cracking is found during any 

inspection]. Transport Canada may mandate 

additional corrective actions pending the 

outcome of the failure investigation and fleet 

findings. The requirements of AD CF–1992– 

26R2 remain applicable. 

The terminating action is doing either a 

detailed inspection for cracking of the 

LH and RH wing lower skin, front and 

rear spar caps, front and rear spar webs, 


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