Federal Register / Vol. 78, No. 20 / Wednesday, January 30, 2013 / Proposed Rules 6247 

with a scale with an accuracy as indicated in 

section 2.9.5 of this appendix. 

* * * * * 

2.7.2 Small test block for conventional 

cooking top. The small test block shall 

comprise a body and separate base. The small 

test block body, W2, shall be 6.25±0.05 inches 

(158.8±1.3 mm) in diameter, approximately 

2.5 inches (64 mm) high and shall weigh 

7.5±0.1 lbs (3.40±0.05 kg). The small test 

block base, W3, shall be 6.25±0.05 inches 

(158.8±1.3 mm) in diameter, approximately 

0.25 inches (6.4 mm) high and shall weigh 

2.2±0.1 lbs (1.00±0.05 kg). The small test 

block body shall not be fixed to the base, and 

shall be centered over the base for testing. 

2.7.3 Large test block for conventional 

cooking top. The large test block shall 

comprise a body and separate base. The large 

test block body for the conventional cooking 

top, W4, shall be 9±0.05 inches (228.6±1.3 

mm) in diameter, approximately 2.7 inches 

(69 mm) high and shall weigh 16.9±0.1 lbs 

(7.67±0.05 kg). The large test block base, W5, 

shall be 9±0.05 inches (228.6±1.3 mm) in 

diameter, approximately 0.25 inches (6.4 

mm) high and shall weigh 4.3±0.1 lbs 

(1.95±0.05 kg). The large test block body shall 

not be fixed to the base, and shall be centered 

over the base for testing. 

* * * * * 

3. Test Methods and Measurements 

* * * * * 

3.1.2 Conventional cooking top. Establish 

the test conditions set forth in section 2, Test 

Conditions, of this appendix. Turn off the gas 

flow to the conventional oven(s), if so 

equipped. The temperature of the 

conventional cooking top shall be its normal 

nonoperating temperature as defined in 

section 1.12 and described in section 2.6 of 

this appendix. Set the test block in the center 

of the surface unit under test. The small test 

block, W2 and W3, shall be used on electric 

surface units with a smallest dimension of 7 

inches (178 mm) or less. The large test block, 

W4 and W5, shall be used on electric surface 

units with a smallest dimension over 7 

inches (178 mm) and on all gas surface units. 

Turn on the surface unit under test and set 

its energy input rate to the maximum setting. 

When the test block reaches 144 °F (80 °C) 

above its initial test block temperature, 

immediately reduce the energy input rate to 

25±5 percent of the maximum energy input 

rate. After 15±0.1 minutes at the reduced 

energy setting, turn off the surface unit under 

test. 

* * * * * 

3.3.2 Record measured test block, test 

block body, and test block base weights W1, 

W2, W3, W4, and W5 in pounds (kg). 

* * * * * 

4. Calculation of Derived Results From Test 

Measurements 

* * * * * 

4.2 * * * 

4.2.1 * * * 

4.2.1.1 Electric surface unit cooking 

efficiency. Calculate the cooking efficiency, 

EffSU, of the electric surface unit under test, 

defined as: 

Where: 

WTB = measured weight of test block body, 

W2 or W4, expressed in pounds (kg). 

Cp,TB = 0.23 Btu/lb-°F (0.96 kJ/kg ÷ °C), 

specific heat of test block body. 

WB = measured weight of test block base, 

W3 or W5, expressed in pounds (kg). 

Cp,B = 0.11 Btu/lb-°F (0.46 kJ/kg ÷ °C), 

specific heat of test block base. 

TSU = temperature rise of the test block: 

Final test block temperature, TCT, as 

determined in section 3.2.2 of this 

appendix, minus the initial test block 

temperature, TI, expressed in °F (°C) as 

determined in section 2.7.5 of this 

appendix. 

Ke = 3.412 Btu/Wh (3.6 kJ/Wh), conversion 

factor of watt-hours to Btu’s. 

ECT = measured energy consumption, as 

determined according to section 3.2.2 of 

this appendix, expressed in watt-hours 

(kJ). 

4.2.1.2 Gas surface unit cooking 

efficiency. Calculate the cooking 

efficiency, EffSU, of the gas surface unit 

under test, defined as: 

Where: 

WTB = measured weight of test block body 

as measured in section 3.3.2 of this 

appendix, expressed in pounds (kg). 

WB = measured weight of test block base 

as measured in section 3.3.2 of this 

appendix, expressed in pounds (kg). 

Cp,TB, Cp,B, and TSU are the same as defined 

in section 4.2.1.1 of this appendix. 

and, 

E = (VCT × H) + (EIC × Ke), 

Where: 

VCT = total gas consumption in standard 

cubic feet (L) for the gas surface unit test 

as measured in section 3.2.2.1 of this 

appendix. 

EIC = electrical energy consumed in watthours (kJ) by an ignition device of a gas 

surface unit as measured in section 

3.2.2.1 of this appendix. 

Ke = 3.412 Btu/Wh (3.6 kJ/Wh), conversion 

factor of watt-hours to Btu’s. 

H = either Hn or Hp, the heating value of 

the gas used in the test as specified in 

sections 2.2.2.2 and 2.2.2.3 of this 

appendix, expressed in Btu’s per 

standard cubic foot (kJ/L) of gas. 

* * * * * 

[FR Doc. 2013–01526 Filed 1–29–13; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1319; Directorate 

Identifier 2012–NM–179–AD] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise an 

existing airworthiness directive (AD) 

that applies to all The Boeing Company 

Model 757 airplanes. The existing AD 

currently requires revising the 

maintenance program by incorporating 

new and revised fuel tank system 

limitations in the Airworthiness 

Limitations (AWLs) section of the 

Instructions for Continued 

Airworthiness; and requires the initial 

inspection of certain repetitive AWL 

inspections to phase-in those 

inspections, and repair if necessary. 

Since we issued that AD, we have found 

errors in paragraph references in the 

existing AD. This proposed AD would 

revise those paragraph references to 

refer to the correct paragraphs. We are 

proposing this AD to prevent the 

potential for ignition sources inside fuel 

tanks caused by latent failures, 

alterations, repairs, or maintenance 

actions, which in combination with 

flammable fuel vapors, could result in a 


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fuel tank explosion and consequent loss 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 18, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https:// 

www.myboeingfleet.com. 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 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: 

Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6501; fax: 425–917–6590; email: 

kevin.nguyen@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–2012–1319; Directorate Identifier 

2012–NM–179–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 

On June 6, 2012, we issued AD 2012– 

12–15, Amendment 39–17095 (77 FR 

42964, July 23, 2012), for all The Boeing 

Company Model 757 airplanes. That AD 

superseded AD 2008–10–11, 

Amendment 39–15517 (73 FR 25974, 

May 8, 2008). AD 2012–12–15 requires 

revising the maintenance program by 

incorporating new and revised fuel tank 

system limitations in the Airworthiness 

Limitations (AWLs) section of the 

Instructions for Continued 

Airworthiness to satisfy Special Federal 

Aviation Regulation No. 88 

requirements; and requires the initial 

inspection of certain repetitive AWL 

inspections to phase-in those 

inspections, and repair if necessary. 

That AD resulted from a report that an 

AWL required by a previous AD must be 

revised. We issued that AD to prevent 

the potential for ignition sources inside 

fuel tanks caused by latent failures, 

alterations, repairs, or maintenance 

actions, which in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, 

July 23, 2012), we have found errors in 

paragraph references in the existing AD. 

The second sentence in paragraph (h)(1) 

of the existing AD refers to paragraph 

(n) of that AD, which is a compliance 

time for AWL No. 28–AWL–26. The 

correct reference should be to paragraph 

(l) of that AD, which is a compliance 

time for AWL No. 28–AWL–03. The last 

sentence in paragraph (l) of the existing 

AD refers to paragraph (h)(2) of that AD, 

which is a definition of a detailed 

inspection. The correct reference should 

be to paragraph (h)(1)(ii) of that AD, 

which references a specific AWL and 

compliance time. 

FAA’s Determination 

We are proposing this AD 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. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, 

July 23, 2012). This proposed AD would 

revise certain paragraph references. 

Costs of Compliance 

We estimate that this proposed AD 

affects 639 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

AWLs revisions [retained actions from existing AD (AD 

2012–12–15, Amendment 39–17095 (77 FR 42964, 

July 23, 2012))].

9 work-hours × $85 per 

hour = $765.

None ............ $765 $488,835 

Inspections [retained actions from existing AD (AD 

2012–12–15, Amendment 39–17095 (77 FR 42964, 

July 23, 2012))].

8 work-hours × $85 per 

hour = $680.

None ............ 680 434,520 

The new requirements of this 

proposed AD add no additional 

economic burden. 

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, 

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Federal Register / Vol. 78, No. 20 / Wednesday, January 30, 2013 / Proposed Rules 6249 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

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 that the 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 adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2012–1319; Directorate Identifier 2012– 

NM–179–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by March 18, 2013. 

(b) Affected ADs 

This AD revises AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, July 23, 

2012). Certain requirements of this AD 

terminate certain requirements of AD 2008– 

11–07, Amendment 39–15529 (73 FR 30755, 

May 29, 2008); AD 2008–06–03, Amendment 

39–15415 (73 FR 13081, March 12, 2008); 

and AD 2009–06–20, Amendment 39–15857 

(74 FR 12236, March 24, 2009). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 757–200, –00PF, –200CB, 

and –300 series airplanes, certificated in any 

category. 

(2) This AD requires revisions to certain 

operator maintenance documents to include 

new actions (e.g., inspections) and/or critical 

design configuration control limitations 

(CDCCLs). Compliance with these actions 

and/or CDCCLs is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

actions described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval of an 

alternative method of compliance (AMOC) 

according to paragraph (s) of this AD. The 

request should include a description of 

changes to the required actions that will 

ensure the continued operational safety of 

the airplane. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 28: Fuel. 

(e) Unsafe Condition 

This AD results from a design review of the 

fuel tank systems. The Federal Aviation 

Administration is issuing this AD to prevent 

the potential for ignition sources inside fuel 

tanks caused by latent failures, alterations, 

repairs, or maintenance actions, which, in 

combination with flammable fuel vapors, 

could result in a fuel tank explosion and 

consequent loss of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Revision of Airworthiness 

Limitations (AWLs) Section 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, July 23, 

2012). Before December 16, 2008, revise the 

AWLs section of the Instructions for 

Continued Airworthiness (ICA) by 

incorporating the information in the 

subsections specified in paragraphs (g)(1) 

through (g)(3) of this AD into the 

maintenance planning data (MPD) document; 

except that the initial inspections specified 

in table 1 to paragraph (h)(1) of this AD must 

be done at the compliance times specified in 

table 1 to paragraph (h)(1) of this AD. 

Accomplishing the requirements of 

paragraph (k) of this AD terminates the 

requirements of this paragraph. 

(1) Subsection E, ‘‘AIRWORTHINESS 

LIMITATIONS—FUEL SYSTEMS,’’ of Boeing 

Temporary Revision (TR) 09–008, dated 

March 2008, to Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of the 

Boeing 757 MPD Document, D622N001–9. 

(2) Subsection F, ‘‘PAGE FORMAT: 

SYSTEMS AIRWORTHINESS 

LIMITATIONS,’’ of Boeing TR 09–008, dated 

March 2008, to Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of the 

Boeing 757 MPD Document, D622N001–9. 

(3) Subsection G, ‘‘AIRWORTHINESS 

LIMITATIONS—FUEL SYSTEM AWLs,’’ 

AWLs No. 28–AWL–01 through No. 28– 

AWL–24 inclusive, of Boeing TR 09–008, 

dated March 2008, to Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9. As an optional action, AWLs 

No. 28–AWL–25 and No. 28–AWL–26, as 

identified in Subsection G of Boeing TR 09– 

008, dated March 2008, to Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9, also may be incorporated into 

the AWLs section of the ICA. 

(h) Retained Initial Inspections and Repair, 

With Revised Service Information 

(1) This paragraph restates the 

requirements of paragraph (h) of AD 2012– 

12–15, Amendment 39–17095 (77 FR 42964, 

July 23, 2012), with a revised paragraph 

reference. Do the inspections specified in 

table 1 to paragraph (h)(1) of this AD at the 

compliance time identified in table 1 to 

paragraph (h)(1) of this AD, and repair any 

discrepancy, in accordance with Subsection 

G of Boeing TR 09–008, dated March 2008, 

to Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of the Boeing 757 

MPD Document, D622N001–9; Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9, Revision December 2008; 

Boeing TR 09–010, dated July 2010, to 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 757 MPD 

Document, D622N001–9; or Boeing TR 09– 

011, dated November 2010, to Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9; except as required by 

paragraph (l) of this AD. The repair must be 

done before further flight. Accomplishing the 

inspections identified in table 1 to paragraph 

(h)(1) of this AD as part of a maintenance 

program before the applicable compliance 

time specified in table 1 to paragraph (h)(1) 

of this AD constitutes compliance with the 

requirements of this paragraph. As of 6 

months after August 27, 2012 (the effective 

date of AD 2012–12–15), only Section 9, 

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6250 Federal Register / Vol. 78, No. 20 / Wednesday, January 30, 2013 / Proposed Rules 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9, Revision December 2008; 

Boeing TR 09–010, dated July 2010, to 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 757 MPD 

Document, D622N001–9; or Boeing TR 09– 

011, dated November 2010, to Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9; may be used. 

TABLE 1 TO PARAGRAPH (H)(1) OF THIS AD—INITIAL INSPECTIONS

AWL No. Description 

Compliance time 

(whichever occurs later) 

Threshold Grace period 

(i) 28–AWL–01 ........... A detailed inspection of external wires 

over the center fuel tank for damaged clamps, wire chafing, and wire 

bundles in contact with the surface 

of the center fuel tank.

Within 120 months since the date of 

issuance of the original standard 

airworthiness certificate or the date 

of issuance of the original export 

certificate of airworthiness.

Within 72 months after June 12, 2008 

(the effective date of AD 2008–10– 

11, Amendment 39-15517 (73 FR 

25974, May 8, 2008)). 

(ii) 28–AWL–03 .......... A special detailed inspection of the 

lightning shield to ground termination on the out-of-tank fuel quantity indicating system to verify functional integrity.

Within 120 months since the date of 

issuance of the original standard 

airworthiness certificate or the date 

of issuance of the original export 

certificate of airworthiness.

Within 24 months after June 12, 2008 

(the effective date of AD 2008–10– 

11, Amendment 39-15517 (73 FR 

25974, May 8, 2008)). 

(iii) 28-AWL-14 ........... A special detailed inspection of the 

fault current bond of the fueling 

shutoff valve actuator of the center 

wing tank to verify electrical bond.

Within 120 months since the date of 

issuance of the original standard 

airworthiness certificate or the date 

of issuance of the original export 

certificate of airworthiness.

Within 60 months after June 12, 2008 

(the effective date of AD 2008–10– 

11, Amendment 39-15517 (73 FR 

25974, May 8, 2008)). 

(2) For the purposes of this AD, a detailed 

inspection is: ‘‘An intensive examination of 

a specific item, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at an 

intensity deemed appropriate. Inspection 

aids such as mirror, magnifying lenses, etc., 

may be necessary. Surface cleaning and 

elaborate procedures may be required.’’ 

(3) For the purposes of this AD, a special 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. The examination is likely to 

make extensive use of specialized inspection 

techniques and/or equipment. Intricate 

cleaning and substantial access or 

disassembly procedure may be required.’’ 

(i) No Alternative Inspections, Inspection 

Intervals, or CDCCLs for Paragraphs (g) and 

(h) of This AD 

This paragraph restates the requirements of 

paragraph (i) of AD 2012–12–15, Amendment 

39–17095 (77 FR 42964, July 23, 2012). 

Except as required by paragraph (k) of this 

AD, after accomplishing the actions specified 

in paragraphs (g) and (h) of this AD, no 

alternative inspections, inspection intervals, 

or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (s) of 

this AD. 

(j) Terminating Action for AD 2008–06–03, 

Amendment 39–15415 (73 FR 13081, March 

12, 2008) 

This paragraph restates the requirements of 

paragraph (j) of AD 2012–12–15, Amendment 

39–17095 (77 FR 42964, July 23, 2012). 

Incorporating AWLs No. 28–AWL–23, No. 

28–AWL–24, and No. 28–AWL–25 into the 

AWLs section of the ICA in accordance with 

paragraph (g)(3) of this AD or the 

maintenance program in accordance with 

paragraph (k)(3) of this AD terminates the 

action required by paragraph (h)(2) of AD 

2008–06–03, Amendment 39–15415 (73 FR 

13081, March 12, 2008). 

(k) Additional Revision of Airworthiness 

Limitations (AWLs) Section 

This paragraph restates the requirements of 

paragraph (k) of AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, July 23, 

2012). Within 6 months after August 27, 2012 

(the effective date of AD 2012–12–15), revise 

the maintenance program by incorporating 

the information in the subsections specified 

in paragraphs (k)(1) through (k)(3) of this AD. 

Accomplishing the actions required by this 

paragraph terminates the requirements of 

paragraph (g) of this AD. 

(1) Subsection E, ‘‘AIRWORTHINESS 

LIMITATIONS—FUEL SYSTEMS,’’ of 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of the Boeing 757 

MPD Document, D622N001–9, Revision 

December 2008; Boeing TR 09–010, dated 

July 2010, to Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of 

Boeing 757 MPD Document, D622N001–9; or 

Boeing TR 09–011, dated November 2010, to 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of the Boeing 757 

MPD Document, D622N001–9. 

(2) Subsection F, ‘‘PAGE FORMAT: FUEL 

SYSTEMS AIRWORTHINESS 

LIMITATIONS,’’ of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9, Revision December 2008; 

Boeing TR 09–010, dated July 2010, to 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 757 MPD 

Document, D622N001–9; or Boeing TR 09– 

011, dated November 2010, to Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9. 

(3) Subsection G, ‘‘AIRWORTHINESS 

LIMITATIONS—FUEL SYSTEM AWLs,’’ 

AWLs No. 28–AWL–01 through No. 28– 

AWL–26 inclusive, of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9, Revision December 2008; 

Boeing TR 09–010, dated July 2010, to 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 757 MPD 

Document, D622N001–9; or Boeing TR 09– 

011, dated November 2010, to Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9. 

(4) Notwithstanding any other maintenance 

or operational requirements, components that 

have been identified as airworthy or installed 

on the affected airplanes before the revision 

of the maintenance program, as required by 

paragraph (g) of this AD, do not need to be 

reworked in accordance with the CDCCLs. 

However, once the maintenance program has 

been revised, future maintenance actions on 

these components must be done in 

accordance with the CDCCLs. 

(l) Compliance Time for AWL No. 28–AWL– 

03 

This paragraph restates the requirements of 

paragraph (l) of AD 2012–12–15, Amendment 

39–17095 (77 FR 42964, July 23, 2012), with 

a revised paragraph reference. The initial 

compliance time for AWL No. 28–AWL–03 of 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of the Boeing 757 

mstockstill on DSK4VPTVN1PROD with 

Federal Register / Vol. 78, No. 20 / Wednesday, January 30, 2013 / Proposed Rules 6251 

MPD Document, D622N001–9, Revision 

December 2008; Boeing TR 09–010, dated 

July 2010, to Section 9, ‘‘Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs),’’ of 

Boeing 757 MPD Document, D622N001–9; or 

Boeing TR 09–011, dated November 2010, to 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of the Boeing 757 

MPD Document, D622N001–9; is within 120 

months since the date of issuance of the 

original standard airworthiness certificate or 

the date of issuance of the original export 

certificate of airworthiness, or within 24 

months after August 27, 2012 (the effective 

date of AD 2012–12–15), whichever occurs 

later. Accomplishing the actions required by 

this paragraph terminates the requirements of 

paragraph (h)(1)(ii) of this AD. 

(m) Initial Inspection Compliance Times for 

AWL No. 28–AWL–25 

This paragraph restates the requirements of 

paragraph (m) of AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, July 23, 

2012). The initial inspection compliance time 

for AWL No. 28–AWL–25 of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9, Revision December 2008; 

Boeing TR 09–010, dated July 2010, to 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 757 MPD 

Document, D622N001–9; or Boeing TR 09– 

011, dated November 2010, to Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9; is within 72 months after 

accomplishing the actions specified in 

Boeing Service Bulletin 757–28A0088 (which 

is not incorporated by reference in this AD). 

(n) Initial Inspection Compliance Times for 

AWL No. 28–AWL–26 

This paragraph restates the requirements of 

paragraph (n) of AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, July 23, 

2012). The initial inspection compliance time 

for AWL No. 28–AWL–26 of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9, Revision December 2008; 

Boeing TR 09–010, dated July 2010, to 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ of Boeing 757 MPD 

Document, D622N001–9; or Boeing TR 09– 

011, dated November 2010, to Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9; is within 12 months after 

accomplishing the actions specified in 

Boeing Service Bulletin 757–28A0105 (which 

is not incorporated by reference in this AD). 

(o) No Alternative Inspections, Inspection 

Intervals, or CDCCLs After the Actions 

Required by Paragraph (k) of This AD Are 

Done 

This paragraph restates the requirements of 

paragraph (o) of AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, July 23, 

2012). After accomplishing the actions 

specified in paragraph (k) of this AD, no 

alternative inspections, inspection intervals, 

or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (s) of 

this AD. 

(p) Terminating Action for AD 2008–11–07, 

Amendment 39–15529 (73 FR 30755, May 

29, 2008) 

This paragraph restates the requirements of 

paragraph (p) of AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, July 23, 

2012). Incorporating AWLs No. 28–AWL–20 

and No. 28–AWL–26 into the maintenance 

program in accordance with paragraph (k)(3) 

of this AD terminates the actions required by 

paragraphs (j) and (m) of AD 2008–11–07, 

Amendment 39–15529 (73 FR 30755, May 29, 

2008). 

(q) Terminating Action for AD 2009–06–20, 

Amendment 39–15857 (74 FR 12236, March 

24, 2009) 

This paragraph restates the requirements of 

paragraph (q) of AD 2012–12–15, 

Amendment 39–17095 (77 FR 42964, July 23, 

2012). Incorporating AWL No. 28–AWL–22 

into the maintenance program in accordance 

with paragraph (k)(3) of this AD terminates 

the actions required by paragraph (h) of AD 

2009–06–20, Amendment 39–15857 (74 FR 

12236, March 24, 2009). 

(r) Credit for Previous Actions 

This paragraph restates the credit given for 

previous actions specified in paragraph (r) of 

AD 2012–12–15, Amendment 39–17095 (77 

FR 42964, July 23, 2012). 

(1) This paragraph provides credit for 

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

this AD, if those actions were done before 

June 12, 2008 (the effective date of AD 2008– 

10–11, Amendment 39–15517 (73 FR 25974, 

May 8, 2008)), using Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9, Revision March 2006; Revision 

October 2006; Revision January 2007; or 

Revision November 2007 (which are not 

incorporated by reference in this AD). 

(2) This paragraph provides credit for 

actions required by paragraphs (m) and (n) of 

this AD, if those actions were done before 

August 27, 2012 (the effective date of AD 

2012–12–15, Amendment 39–17095 (77 FR 

42964, July 23, 2012)), using Boeing TR 09– 

008, dated March 2008, to Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ of the Boeing 757 MPD Document, 

D622N001–9 (which was incorporated by 

reference in AD 2008–10–11, Amendment 

39–15517 (73 FR 25974, May 8, 2008)). 

(s) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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. 

(3) AMOCs approved previously for AD 

2008–10–11, Amendment 39–15517 (73 FR 

25974, May 8, 2008); or for 2012–12–15, 

Amendment 39–17095 (77 FR 42964, July 23, 

2012); are approved as AMOCs for the 

corresponding provisions of this AD. 

(t) Related Information 

(1) For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6501; fax: 425–917–6590; email: 

kevin.nguyen@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 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. 

Issued in Renton, Washington, on January 

17, 2013. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–01953 Filed 1–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1320; Directorate 

Identifier 2012–NM–095–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767 

airplanes. This proposed AD was 

prompted by reports of cracks and heat 

damage on pivot joint components 

found during main landing gear (MLG) 

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