Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 51443 

(D) Test switch-selectable singlevoltage external power supplies twice— 

once at the highest nameplate output 

voltage and once at the lowest. 

(E) Test adaptive external power 

supplies twice—once at the highest 

achievable output voltage and once at 

the lowest. 

(F) In order to load the power supply 

to produce all four active-mode load 

conditions, use a set of variable resistive 

or electronic loads. Although these 

loads may have different characteristics 

than the electronic loads power supplies 

are intended to power, they provide 

standardized and readily repeatable 

references for testing and product 

comparison. Note that resistive loads 

need not be measured precisely with an 

ohmmeter; simply adjust a variable 

resistor to the point where the ammeter 

confirms that the desired percentage of 

nameplate output current is flowing. For 

electronic loads, adjust the desired 

output current in constant current (CC) 

mode rather than adjusting the required 

output power in constant power (CP) 

mode. 

(G) As noted in IEC 62301 

(incorporated by reference; see § 430.3), 

instantaneous measurements are 

appropriate when power readings are 

stable in a particular load condition. 

Operate the UUT at 100% of nameplate 

current output for at least 30 minutes 

immediately prior to conducting 

efficiency measurements. After this 

warm-up period, monitor AC input 

power for a period of 5 minutes to 

assess the stability of the UUT. If the 

power level does not drift by more than 

5% from the maximum value observed, 

the UUT is considered stable and the 

measurements should be recorded at the 

end of the 5-minute period. Measure 

subsequent load conditions under the 

same 5-minute stability parameters. 

Note that only one warm-up period of 

30 minutes is required for each UUT at 

the beginning of the test procedure. If 

the AC input power is not stable over 

a 5-minute period, follow the guidelines 

established by IEC 62301 for measuring 

average power or accumulated energy 

over time for both AC input and DC 

output. Conduct efficiency 

measurements in sequence from Load 

Condition 1 to Load Condition 5 as 

indicated in Table 1. If testing of 

additional, optional load conditions is 

desired, that testing should be 

conducted in accordance with this test 

procedure and subsequent to 

completing the sequence described 

above. 

(H) Calculate efficiency by dividing 

the UUT’s measured DC output power at 

a given load condition by the true AC 

input power measured at that load 

condition. Calculate average efficiency 

as the arithmetic mean of the efficiency 

values calculated at Test Conditions 1, 

2, 3, and 4 in Table 1, and record this 

value. Average efficiency for the UUT is 

a simple arithmetic average of activemode efficiency values, and is not 

intended to represent weighted average 

efficiency, which would vary according 

to the duty cycle of the product 

powered by the UUT. 

(I) Power consumption of the UUT at 

each Load Condition 1–4 is the 

difference between the DC output power 

(W) at that Load Condition and the AC 

input power (W) at that Load Condition. 

The power consumption of Load 

Condition 5 (no load) is equal to the AC 

input power (W) at that Load Condition. 

(ii) Off-Mode Measurement—If the 

external power supply UUT 

incorporates manual on-off switches, 

place the UUT in off-mode, and measure 

and record its power consumption at 

‘‘Load Condition 5’’ in Table 1. The 

measurement of the off-mode energy 

consumption must conform to the 

requirements specified in paragraph 

4(a)(i) of this appendix, except that all 

manual on-off switches must be placed 

in the ‘‘off’’ position for the off-mode 

measurement. The UUT is considered 

stable if, over 5 minutes with samples 

taken at least once every second, the AC 

input power does not drift from the 

maximum value observed by more than 

1 percent or 50 milliwatts, whichever is 

greater. Measure the off-mode power 

consumption of a switch-selectable 

single-voltage external power supply 

twice—once at the highest nameplate 

output voltage and once at the lowest. 

* * * * * 

■ 7. Section 430.32 is amended by 

adding paragraph (w)(1)(iii) to read as 

follows: 

§ 430.32 Energy and water conservation 

standards and their compliance dates. 

(w) * * * 

(1)* * * 

(iii) Except as provided in paragraphs 

(w)(5), (w)(6), and (w)(7) of this section, 

all external power supplies 

manufactured on or after February 10, 

2016, shall meet the following 

standards: 

Class A EPS Non-Class A EPS 

Direct Operation EPS ................................................... Level VI: 10 CFR 430.32(w)(1)(ii) ................................ Level VI: 10 CFR 

430.32(w)(1)(ii). 

Indirect Operation EPS ................................................. Level IV: 10 CFR 430.32(w)(1)(i) ................................. No Standards. 

* * * * * 

[FR Doc. 2015–20717 Filed 8–24–15; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1044; Directorate 

Identifier 2014–NM–148–AD; Amendment 

39–18245; AD 2015–17–12] 

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, and 650 

airplanes. This AD was prompted by 

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 inspections to determine if 

certain A/C compressor motors are 

installed and to determine the 

accumulated hours on certain A/C 

compressor motor assemblies; and 

repetitive replacement of the brushes in 

the A/C compressor motor assembly, or, 

as an option to the brush replacement, 

deactivation of the A/C system and 


Lhorne on DSK5TPTVN1PROD with RULES
51444 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 

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 September 

29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 29, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Cessna 

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

67277; phone: 316–517–6215; fax: 316– 

517–5802; email: citationpubs@

cessna.textron.com; Internet https://

www.cessnasupport.com/newlogin.html. 

You may view this 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

1044. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

1044; 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 

Docket 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: 

Craig Henrichsen, Aerospace Engineer, 

Electrical Systems and Avionics Branch, 

ACE–119W, FAA, Wichita Aircraft 

Certification Office (ACO), 1801 Airport 

Road, Room 100, Mid-Continent 

Airport, Wichita, KS 67209; phone: 

316–946–4110; fax: 316–946–4107; 

email: Craig.Henrichsen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Cessna Aircraft 

Company Model 500, 501, 550, 551, 

S550, 560, and 650 airplanes. The 

NPRM published in the Federal 

Register on January 23, 2015 (80 FR 

3516). The NPRM was prompted by 

reports of smoke and/or fire in the 

tailcone caused by sparking due to 

excessive wear of the brushes in the 

A/C motor. The NPRM proposed to 

require inspections to determine if 

certain A/C compressor motors are 

installed and to determine the 

accumulated hours on certain A/C 

compressor motor assemblies; and 

repetitive replacement of the brushes in 

the A/C compressor 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 3516, January 23, 2015) 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 this 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 NPRM (80 FR 3516, 

January 23, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 3516, 

January 23, 2015). 

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. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information, which describes 

procedures for replacement of lifelimited components, including part 

number FWA1134104–1 or 

FWA1134104–5 A/C compressor motor 

brushes. 

• Subject 4–11–00, Replacement 

Time Limits, of Chapter 4, 

Airworthiness Limitations, Revision 6, 

dated June 23, 2014, of the Cessna 

Model 500/501 Maintenance Manual. 

• Subject 4–11–00, Replacement 

Time Limits, of Chapter 4, 

Airworthiness Limitations, Revision 10, 

dated June 23, 2014, of the Cessna 

Model 550/551 Maintenance Manual. 

• Subject 4–11–00, Replacement 

Time Limits, of Chapter 4, 

Airworthiness Limitations, Revision 12, 

dated June 23, 2014, of the Cessna 

Model 550 Bravo Maintenance Manual. 

• Subject 4–11–00, Replacement 

Time Limits, of Chapter 4, 

Airworthiness Limitations, Revision 9, 

dated June 23, 2014, of the Cessna 

Model S550 Maintenance Manual. 

• Subject 4–11–00, Replacement 

Time Limits, of Chapter 4, 

Airworthiness Limitations, Revision 22, 

dated June 23, 2014, of the Cessna 

Model 560 Maintenance Manual. 

• Subject 4–11–00, Replacement 

Time Limits, of Chapter 4, 

Airworthiness Limitations, Revision 32, 

dated June 23, 2014, of the Cessna 

Model 650 Maintenance Manual. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 333 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 51445 

ESTIMATED COSTS—BRUSH REPLACEMENT

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection and replacement ... 11 work-hours × $85 per hour 

= $935 per replacement 

cycle.

$252 $1,187 per replacement cycle $395,271 per replacement 

cycle. 

Reporting/return parts ............ 1 work-hour × $85 per hour = 

$85 per return.

0 85 ........................................... $28,305 per return (2 returns 

required). 

ESTIMATED COSTS—A/C DEACTIVATION

Action Labor cost Parts cost Cost per 

product 

Fabrication of placard for A/C deactivation .................. 1 work-hour × $85 per hour = $85 ............................... $0 $85 

Deactivation/reactivation of A/C ................................... 1 work-hour × $85 per hour = $85 ............................... 0 85 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to 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 control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is 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. 

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. 

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): 

2015–17–12 Cessna Aircraft Company: 

Amendment 39–18245; Docket No. 

FAA–2014–1044; Directorate Identifier 

2014–NM–148–AD. 

(a) Effective Date 

This AD is effective September 29, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Cessna Aircraft 

Company airplanes, certificated in any 

category, identified in table 1 to paragraph (c) 

of this AD, that have an air conditioning 

(A/C) system installed via a Cessna Aircraft 

Company supplemental type certificate (STC) 

identified in paragraph (c)(1), (c)(2), (c)(3), or 

(c)(4) of this AD. 

(1) SA3849SW (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rgstc.nsf/

0/029C5719AD18E79C86257C1A0069742C?

OpenDocument&Highlight=sa3849sw). 

(2) SA7580SW (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rgstc.nsf/

0/7C9B0FB7D5923D4986257C1A0069E2C0?

OpenDocument&Highlight=sa7580sw). 

(3) SA7753SW (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rgstc.nsf/

0/A78233CBB3314BAF86257C1A0069D128?

OpenDocument&Highlight=sa7753sw). 

(4) SA8918SW (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rgstc.nsf/

0/5FAD7ABA3EAA464C86257C

1A0069F239?OpenDocument&Highlight=

sa8918sw). 


Lhorne on DSK5TPTVN1PROD with RULES
51446 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 

TABLE 1 TO PARAGRAPH (c) OF THIS AD—AFFECTED AIRPLANE MODELS AND SERIAL NUMBERS (S/NS) 

Cessna aircraft company airplane models S/Ns 

Model 500 and 501 airplanes ................................................................... 0001 through 0689 inclusive. 

Model 550 and 551 airplanes ................................................................... 0002 through 0733 inclusive, and 0801 through 1136 inclusive. 

Model S550 airplanes ............................................................................... 0001 through 0160 inclusive.

Model 560 airplanes ................................................................................. 0001 through 0707 inclusive, and 0751 through 0815 inclusive. 

Model 650 airplanes ................................................................................. 0200 through 0241 inclusive, and 7001 through 7119 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 21, Air Conditioning. 

(e) Unsafe Condition 

This AD was prompted by reports of smoke 

and/or fire in the tailcone caused by sparking 

due to excessive wear of the brushes in the 

A/C motor. 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. 

(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 FWA1134104–1 or P/ 

N FWA1134104–5 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 having P/N FWA1134104–1 or P/N 

FWA1134104–5 is found: 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 

accumulated on the A/C compressor hour 

meter. 

(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 accumulated 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. 

(ii) If, through the logbook check, a 

determination cannot be made regarding the 

number of hours accumulated on the A/C 

compressor motor brushes, as specified in 

paragraph (h)(2) of this AD, use the number 

of hours accumulated 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)(6) 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) Maintenance Manual Information for 

Replacement 

Use the instructions in the applicable 

Cessna maintenance manual subject specified 

in paragraphs (j)(1) through (j)(6) 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 6, dated June 23, 2014, 

of the Cessna Model 500/501 Maintenance 

Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 10, dated June 23, 

2014, of the Cessna Model 550/551 

Maintenance Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 12, dated June 23, 

2014, of the Cessna Model 550 Bravo 

Maintenance Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 9, dated June 23, 2014, 

of the Cessna Model S550 Maintenance 

Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 22, dated June 23, 

2014, of the Cessna Model 560 Maintenance 

Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 32, dated June 23, 

2014, of the Cessna Model 650 Maintenance 

Manual. 

(k) Deactivation of the 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) or (k)(2) of this AD, as 

applicable. 

(1) For all airplanes except Model 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. 

(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. 

Note 1 to paragraph (k) of this AD: While 

the A/C system is deactivated, it is 

recommended that airplane operators remain 

aware of the operating temperature 

limitations specified in the applicable 

airplane flight manual. 

(l) Reactivation of the A/C System 

If the A/C system is deactivated, as 

specified in paragraph (k) of this AD, prior 

to the A/C system being reactivated: 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) or (l)(2) 

of this AD, as applicable. 

(1) For all airplanes except Model 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. 

(m) Parts Return and Reporting 

Requirements 

For the first two A/C compressor motor 

brush replacement cycles on each airplane, 

send the removed brushes to Cessna Aircraft 

Company, Cessna Service Parts and 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 51447 

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 time, in 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, if 

installed. 

(n) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install an A/C compressor motor 

having P/N FWA1134104–1 or P/N 

FWA1134104–5, unless the inspection 

specified in paragraph (h) of this AD is done 

before installation, and the replacements 

specified in paragraph (i) of this AD are 

subsequently done in accordance with the 

applicable service information identified in 

paragraphs (j)(1) through (j)(6) of this AD at 

the times specified in paragraph (i) of this 

AD. 

(o) Special Flight Permit Limitation 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) with the following 

limitation: Operation of the A/C system is 

prohibited. 

(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 

paragraph (r) 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 Craig Henrichsen, Aerospace 

Engineer, Electrical Systems and Avionics 

Branch, ACE–119W, FAA, Wichita ACO, 

1801 Airport Road, Room 100, Mid-Continent 

Airport, Wichita, KS 67209; phone: 316–946– 

4110; fax: 316–946–4107; email: 

Craig.Henrichsen@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 6, dated June 23, 2014, 

of the Cessna Model 500/501 Maintenance 

Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 10, dated June 23, 

2014, of the Cessna Model 550/551 

Maintenance Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 12, dated June 23, 

2014, of the Cessna Model 550 Bravo 

Maintenance Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 9, dated June 23, 2014, 

of the Cessna Model S550 Maintenance 

Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 22, dated June 23, 

2014, of the Cessna Model 560 Maintenance 

Manual. 

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

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 32, dated June 23, 

2014, of the Cessna Model 650 Maintenance 

Manual. 

(3) For service information identified in 

this AD, contact Cessna Aircraft Co., P.O. Box 

7706, Wichita, KS 67277; phone: 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 August 

10, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20692 Filed 8–24–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0242; Directorate 

Identifier 2014–NM–100–AD; Amendment 

39–18240; AD 2015–17–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A300 B4–603, B4–605R, 

B4–620, B4–622, B4–622R airplanes; all 

Airbus Model A300 C4–605R Variant F 

airplanes; and certain Airbus Model 

A300 F4–605R airplanes. This AD was 

prompted by the manufacturer’s review 

of all repairs accomplished using the 

structural repair manual. This review 

was done using revised fatigue and 

damage tolerance calculations. This AD 

requires an inspection of the 

surrounding panels of the left and right 

forward passenger doors, and corrective 

actions if necessary. We are issuing this 

AD to detect and correct previous 

incomplete or inadequate repairs to the 

surrounding panels of the left and right 

forward passenger doors and the failsafe ring, which could negatively affect 

the structural integrity of the airplane. 

DATES: This AD becomes effective 

September 29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 29, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0242 or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 


Lhorne on DSK5TPTVN1PROD with RULES