14726 Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 

APPENDIX 1 

AWL No. Task Interval Applicability Description 

28–AWL–101 .................... ALI 7,500 FH or 3 years, 

whichever is first.

ALL .................................. Engine Fuel Suction Feed Operational Test. 

An Engine Fuel Suction Feed Operational Test 

must be accomplished successfully on each engine 

individually. This test is required in order to protect 

against engine flameout during suction feed operations, and must meet the following requirements 

(refer to Boeing AMM 28–22–00): 

Fuel Tank Quantity Limitations: 

Engine No. 1 

a. The Center Tank Fuel Quantity must 

not exceed 5,000 lbs (2,270 kg). 

b. The Main Tank No. 1 Fuel Quantity 

must be between 1,400 lbs–1,600 lbs 

(600 kg–800 kg). 

NOTE: Excess fuel can be transferred 

to Main Tank No. 2. 

Engine No. 2 

a. The Center Tank Fuel Quantity must 

not exceed 5,000 lbs (2,270 kg). 

b. The Main Tank No. 2 Fuel Quantity 

must be between 1,400 lbs–1,600 lbs 

(600 kg–800 kg). 

NOTE: Excess fuel can be transferred 

to Main Tank No. 1. 

Test Procedural Limitations: 

1. The Fuel Cross-Feed Valve must be 

CLOSED. 

2. The APU Selector Switch must be OFF. 

3. Idle Engine Warm-up time of minimum two 

minutes with Boost Pump ON. 

4. Idle Engine Suction Feed (Boost Pump 

OFF) operation for a minimum of five minutes. 

NOTE: APU may be used to start the engines 

provided the Fuel Tank Quantity and Test 

Procedural Limitations are met. 

The test is considered a success if engine operation is maintained during the five-minute 

period and engine parameters (N1, N2, and 

Fuel Flow) do not decay relative to those observed with Boost Pump ON. 

A suction fee system that fails the operational 

test must be repaired or maintained, and 

successfully pass the Engine Suction Feed 

Operational Test prior to further flight. 

Directorate Identifier 2007–NM–355–AD 

Issued in Renton, Washington, on February 

15, 2013. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–05202 Filed 3–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1052; Directorate 

Identifier 2012–CE–014–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Cessna Aircraft Company 

(Cessna) Models 172R, 172S, 182S, 

182T, T182T, 206H, and T206H 

airplanes. That NPRM proposed to 

supersede an existing AD that currently 

requires an inspection of the engine oil 

pressure switch and, if applicable, 

replacement with an improved engine 

oil pressure switch. Since we issued the 

existing AD, we have received new 

reports of internal failure of the 

improved engine oil pressure switch, 

which could result in complete loss of 

engine oil with consequent partial or 

complete loss of engine power or fire. 

The NPRM proposed to increase the 

applicability of the AD and place a lifelimit of 3,000 hours time-in-service 

(TIS) on the engine oil pressure switch, 

requiring replacement when the engine 

oil pressure switch reaches its life limit. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 14727 

This action revises that NPRM by 

changing the applicable serial numbers 

ranges. Since these actions impose an 

additional burden over that proposed in 

the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. We are proposing this 

supplemental NPRM to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this supplemental NPRM by April 22, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Cessna 

Aircraft Company, Product Support, 

P.O. Box 7706, Wichita, Kansas 67277; 

telephone: (316) 517–5800; fax (316) 

942–9006; Internet: www.cessna.com/ 

customer-service/technicalpublications.html. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Jeff 

Janusz, Sr. Propulsion Engineer, Wichita 

Aircraft Certification Office, FAA, 1801 

Airport Road, Wichita, KS 67209; 

phone: (316) 946–4148; fax: (316) 946– 

4107; email: jeff.janusz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–1052; Directorate Identifier 

2012–CE–014–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Cessna Aircraft 

Company Models 172R, 172S, 182S, 

182T, T182T, 206H, and T206H 

airplanes. That NPRM published in the 

Federal Register on October 2, 2012 (77 

FR 60062). That NPRM proposed to 

supersede an existing AD that currently 

requires an inspection of the engine oil 

pressure switch and, if applicable, 

replacement with an improved engine 

oil pressure switch. Since we issued 

that AD, we received new reports of 

internal failure of the improved engine 

oil pressure switch, which could result 

in complete loss of engine oil with 

consequent partial or complete loss of 

engine power or fire. The NPRM 

proposed to increase the applicability of 

the existing AD and place a life-limit of 

3,000 hours time-in-service (TIS) on the 

engine oil pressure switch, requiring 

replacement when the engine oil 

pressure switch reaches its life limit. 

Actions Since Previous NPRM Was 

Issued 

Since we issued the previous NPRM 

(77 FR 60062, October 2, 2012), the 

serial number applicability has been 

changed for Cessna Aircraft Company 

Models 172R, 172S, 182T, T182T, and 

206H airplanes. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Stated Maintenance Activity 

Robert A. Hecht stated that he 

replaced the oil pressure switch on his 

2000 Cessna 206H at 1,006 hours TIS 

because of light oil leaking from the 

case. 

The commenter is making a 

pronouncement about maintenance 

activity on his airplane and offered no 

further explanation as to what his intent 

was. 

Request for Replacement at Next 

Inspection 

Stuart B. Harnden stated he believes 

the replacement of the oil switch should 

be mandatory at the next inspection, 

regardless of hours or condition of the 

oil pressure switch, since it cannot be 

predicted when a switch may fail. 

We do not agree because we would 

expect to see oil pressure switches 

removed from service on condition 

anyway at whatever TIS they become 

unairworthy. The goal of the AD action 

is to remove all switches with more than 

3,000 hours TIS, and, if they are 

removed earlier for condition, that is an 

acceptable maintenance practice and 

does not affect this rulemaking activity. 

FAA’s Determination 

We are proposing this supplemental 

NPRM because we evaluated all the 

relevant information and determined 

the unsafe condition described 

previously is likely to exist or develop 

in other products of the same type 

design. Certain changes described above 

expand the scope of the original NPRM. 

As a result, we have determined that it 

is necessary to reopen the comment 

period to provide additional 

opportunity for the public to comment 

on this supplemental NPRM. 

Proposed Requirements of the 

Supplemental NPRM 

This proposed AD would increase the 

applicability statement of the existing 

AD, require an inspection of the engine 

oil pressure switch and place a life limit 

of 3,000 hours TIS on the engine oil 

pressure switch. We are proposing this 

AD to correct the unsafe condition on 

these products. 

Costs of Compliance 

We estimate that this proposed AD 

affects 6,156 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
14728 Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product 

Cost on U.S. 

operators 

Inspection of the airplane or 

engine records.

.5 work-hour × $85 per hour = $42.50 .................................. Not applicable $42.50 $261,630 

Inspection of the engine oil 

pressure switch installation.

.5 work-hour × $85 per hour = $42.50 .................................. Not applicable 42.50 261,630 

Removal and replacement of 

the engine oil pressure 

switch and logbook entry.

.5 work-hour × $85 per hour = $42.50 .................................. $54 .................. 96.50 594,054 

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 determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing airworthiness directive (AD) 

2000–04–01, Amendment 39–11583 (65 

FR 8649, February 22, 2000), and adding 

the following new AD: 

Cessna Aircraft Company: Docket No. FAA– 

2012–1052; Directorate Identifier 2012– 

CE–014–AD. 

(a) Comments Due Date 

We must receive comments by April 22, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2000–04–01, 

Amendment 39–11583 (65 FR 8649, February 

22, 2000). 

(c) Applicability 

This AD applies to Cessna Aircraft 

Company Models 172R, serial numbers (S/N) 

17280001 through 17281618; 172S, S/N 

172S8001 through 172S11256; 182S, S/N 

18280001 through 18280944; 182T, S/N 

18280945 through 18282357; T182T, S/N 

T18208001 through T18209089; 206H, S/N 

20608001 through 20608349; and T206H, 

S/N T20608001 through T20609079; 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 7931, Engine Oil Pressure. 

(e) Unsafe Condition 

This AD was prompted by new reports of 

internal failure of the improved engine oil 

pressure switch, which could result in 

complete loss of engine oil with consequent 

partial or complete loss of engine power or 

fire. We are issuing this AD to increase the 

applicability of the AD and place a life-limit 

of 3,000 hours time-in-service (TIS) on the 

engine oil pressure switch, requiring 

replacement when the engine oil pressure 

switch reaches its life limit. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, following Cessna 

Service Bulletin SB 07–79–01, dated January 

29, 2007, unless already done. 

(g) Actions 

(1) At the next scheduled oil change, 

annual inspection, or 100-hour time-inservice (TIS) inspection after the effective 

date of this AD, whichever occurs later, but 

in no case later than 12 months after the 

effective date of this AD, inspect the engine 

oil pressure switch to determine if it is partnumber (P/N) 77041 or P/N 83278. 

(2) If after the inspection required in 

paragraph (g)(1) of this AD, P/N 77041 engine 

oil pressure switch is installed, before further 

flight, replace the engine oil pressure switch 

with a new, zero time, P/N 83278 engine oil 

pressure switch. Record the engine oil 

pressure switch part number, date, and 

airplane hours TIS in the airplane log book. 

The recorded engine oil pressure switch TIS 

will be used as the benchmark for calculation 

of the 3,000 hour TIS limit on the engine oil 

pressure switch. 

(3) After the effective date of this AD, do 

not install a P/N 77041 engine oil pressure 

switch on any affected airplane. 

(4) If after the inspection required in 

paragraph (g)(1) of this AD it is confirmed 

that P/N 83278 engine oil pressure switch is 

installed, through inspection of the airplane 

or engine logbooks determine the TIS of the 

engine oil pressure switch. 

(5) If after the inspection required in 

paragraph (g)(1) of this AD you cannot 

positively identify the hours TIS on the P/N 

83278 engine oil pressure switch, before 

further flight, replace the engine oil pressure 

switch with a new, zero time, P/N 83278 

engine oil pressure switch. Record the engine 

oil pressure switch part number, date, and 

airplane hours in the airplane log book. The 

recorded engine oil pressure switch TIS will 

be used as the benchmark for calculation of 

the 3,000 hour TIS limit on the engine oil 

pressure switch. 

(6) When the engine oil pressure switch is 

at or greater than 3,000 hours TIS or within 

50 hours TIS after the effective date of this 

AD, whichever occurs later, and repetitively 

thereafter at intervals not to exceed 3,000 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 45 / Thursday, March 7, 2013 / Proposed Rules 14729 

hours TIS on the P/N 83278 engine oil 

pressure switch, replace it with a new, zero 

time, P/N 83278 engine oil pressure switch. 

Record the engine oil pressure switch part 

number, date, and airplane hours in the 

airplane log book. The recorded engine oil 

pressure switch TIS will be used as the 

benchmark for calculation of the 3,000 hour 

TIS limit on the engine oil pressure switch. 

(h) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Jeff Janusz, Sr. Propulsion Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Wichita, KS 67209 phone: (316) 946–4148; 

fax: (316) 946–4107; email: 

jeff.janusz@faa.gov. 

(2) For service information identified in 

this AD, contact Cessna Aircraft Company, 

Product Support, P.O. Box 7706, Wichita, 

Kansas 67277; telephone: (316) 517–5800; fax 

(316) 942–9006; Internet: www.cessna.com/ 

customer-service/technical-publications. 

html. You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri, on 

February 27, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–05287 Filed 3–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0223; Directorate 

Identifier 2012–CE–049–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Pilatus 

Aircraft Ltd. Models PC–6, PC–6–H1, 

PC–6–H2, PC–6/350, PC–6/350–H1, PC– 

6/350–H2, PC–6/A, PC–6–A–H1, PC–6/ 

A–H2, PC–6/B–H2, PC–6/B1–H2, PC- 6/ 

B2–H2, PC–6/B2–H4, PC–6/C–H2, and 

PC–6/C1–H2 airplanes that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as failure to 

inspect and maintain stabilizer-trim 

attachment components and the flap 

actuator could result in loss of control. 

We are issuing this proposed AD to 

require actions to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by April 22, 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact PILATUS 

AIRCRAFT LTD., Customer Service 

Manager, CH–6371 STANS, 

Switzerland; telephone: +41 (0) 41 619 

65 01; fax: +41 (0) 41 619 65 76; 

Internet: http://www.pilatusaircraft.com/#32. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0223; Directorate Identifier 

2012–CE–049–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

regulations.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On December 28, 2010, we issued AD 

2011–01–14, Amendment 39–16571 (76 

FR 5647; February 1, 2011). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2011–01–14, (76 

FR 5647; February 1, 2011), the 

airworthiness limitations of the airplane 

maintenance manual has been updated 

to include the flap actuator, which was 

not included when the limitations were 

initially created. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No.: 

2012–0268, dated December 19, 2012 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

The mandatory instructions and 

airworthiness limitations applicable to the 

Structure and Components of the PC–6 are 

specified in the Aircraft Maintenance Manual 

(AMM) under Chapter 4 or in the 

Airworthiness Limitations Document (ALS), 

depending on the aeroplane model. 


emcdonald on DSK67QTVN1PROD with PROPOSALS