Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations 65921 

12 5 U.S.C. 553(d)(3). 13 12 U.S.C. 3311. 14Public Law 104–121 (Mar. 29, 1996), as 

amended by Public Law 110–28 (May 25, 2007). 

15Public Law 96–354 (Sept. 19, 1980). 

16 5 U.S.C. 601(2). 

the FDIC invokes this good cause 

exception to Section 553 of the APA. 

The FDIC believes that good cause 

exists for issuing a final rule without 

providing notice and an opportunity for 

public comment because such an 

exercise is ‘‘unnecessary.’’ By the 

express terms of both regulations, the 

underlying programs described in part 

370 and § 330.16 have expired, and, 

because of that, the rescission of these 

rules can have no effect on the banking 

industry or the public. Moreover, the 

rescission of part 370, § 330.1(s), and 

§ 330.16 is not ‘‘substantive’’ as the 

programs that these regulations 

implemented have expired and they 

affect no substantive rights or 

obligations. 

2. Effective Date 

In addition, section 553(d)(3) of the 

APA provides that an agency, for good 

cause found and published with the 

rule, does not have to comply with the 

requirement that a substantive rule be 

published not less than 30 days before 

its effective date. The FDIC invokes this 

good cause exception because the 

rescission of part 370, § 330.1(s), and 

§ 330.16 is not ‘‘substantive’’ as the 

programs that these regulations 

implemented have expired and they 

affect no substantive rights or 

obligations.12

B. The Economic Growth and 

Regulatory Paperwork Reduction Act 

Under section 2222 of the Economic 

Growth and Regulatory Paperwork 

Reduction Act of 1996 (EGRPRA),13 the 

FDIC is required to review all of its 

regulations, at least once every 10 years, 

in order to identify any outdated or 

otherwise unnecessary regulations 

imposed on insured institutions. The 

FDIC completed the last comprehensive 

review of its regulations under EGRPRA 

in 2006 and has commenced the next 

decennial review. Rescission of part 370 

and § 330.16 is consistent with the 

required regulatory response to the 

EGRPRA review process: To eliminate 

unnecessary regulations to the extent 

such action is appropriate. 

C. Small Business Regulatory 

Enforcement Fairness Act 

The Office of Management and Budget 

has determined that the Final Rule is 

not a ‘‘major rule’’ within the meaning 

of the relevant sections of the Small 

Business Regulatory Enforcement Act of 

1996 (SBREFA).14 As required by law, 

the FDIC will file the appropriate 

reports with Congress and the General 

Accounting Office so that the Final Rule 

may be reviewed. 

D. Paperwork Reduction Act 

Existing collections of information 

shall be discontinued or modified, as 

appropriate, to the extent that this rule 

obviates or alters any collection of 

information. 

E. Regulatory Flexibility Act 

The Regulatory Flexibility Act 15

(RFA) applies only to rules for which an 

agency publishes a general notice of 

proposed rulemaking pursuant to 5 

U.S.C. 553(b), or any other law.16 As 

discussed above, consistent with section 

553(b)(3)(B) of the APA, the FDIC has 

determined for good cause that general 

notice and opportunity for public 

comment would be unnecessary. 

Therefore, pursuant to 5 U.S.C. 601(2), 

the RFA does not apply. 

List of Subjects 

12 CFR Part 330 

Bank deposit insurance, Banks, 

Banking, Reporting and recordkeeping 

requirements, Savings and loan 

associations, Trusts and trustees. 

12 CFR Part 370 

Banks, Banking, Bank deposit 

insurance, Holding companies, National 

banks, Reporting and recordkeeping 

requirements, Savings associations. 

Authority and Issuance 

For the reasons set forth in the 

preamble above, under the authority of 

12 U.S.C. 1821, the Board of Directors 

of the Federal Deposit Insurance 

Corporation amends chapter III of title 

12 of the Code of Federal Regulations as 

follows: 

PART 330—DEPOSIT INSURANCE 

COVERAGE 

■ 1. The authority citation for part 330 

continues to read as follows: 

Authority: 12 U.S.C. 1813(l), 1813(m), 

1817(i), 1818(q), 1819(a)(Tenth), 1820(f), 

1820(g), 1821(a), 1821(d), 1822(c). 

§ 330.1 [Amended] 

■ 2. Remove and reserve § 330.1(s). 

§ 330.16 [Removed and Reserved] 

■ 3. Remove and reserve § 330.16. 

PART 370—[Removed and Reserved] 

■ 4. Remove and reserve part 370. 

Dated at Washington, DC, this 22nd day of 

October 2015. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2015–27294 Filed 10–27–15; 8:45 am] 

BILLING CODE 6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4205; Directorate 

Identifier 2015–NM–149–AD; Amendment 

39–18301; AD 2015–21–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. This AD requires 

repetitive eddy current inspections for 

any cracking in the inspar upper skin, 

and related investigative and corrective 

actions if necessary. This AD was 

prompted by a report that an operator 

discovered a crack in a certain section 

of the inspar upper skin, just forward of 

the rear spar on the right wing. We are 

issuing this AD to detect and correct any 

cracking in the inspar upper skin and 

rear spar upper chord, which could 

result in the inability of the structure to 

carry limit load, or result in a fuel leak, 

which could prevent continued safe 

flight and landing. 

DATES: This AD is effective November 

12, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 12, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of April 9, 2014 (79 FR 

12368, March 5, 2014). We must receive 

comments on this AD by December 14, 

2015. 

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. 


Lhorne on DSK5TPTVN1PROD with RULES
65922 Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations 

• 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 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 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–2015– 

4205. 

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–2015– 

4205; 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 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: 

Jennifer Tsakoumakis, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5264; fax: 562–627– 

5210; email: jennifer.tsakoumakis@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received a report that an 

operator discovered a crack in the 

inspar upper skin at wing buttock line 

157, just forward of the rear spar on the 

right wing. The crack measured 2.375 

inches long. Two additional cracks were 

found in the skin at two holes common 

to the rear spar in the same area. 

Subsequent inspections specified in 

Boeing Special Attention Service 

Bulletin 737–57–1318, dated May 15, 

2013, revealed that the rear spar upper 

chord was almost completely severed. 

Web cracks were also discovered on 

both wings. This condition, if not 

corrected, could result in the inability of 

the structure to carry limit load, or 

result in a fuel leak, which could 

prevent continued safe flight and 

landing. We are issuing this AD to 

correct the unsafe condition on these 

products. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–57A1326, dated September 

22, 2015. The service information 

describes procedures for repetitive eddy 

current inspections for any cracking in 

the inspar upper skin, and applicable 

related investigative and corrective 

actions. 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. 

Other Relevant Rulemaking 

AD 2014–12–13, Amendment 39– 

17874 (79 FR 39300, July 10, 2014), was 

issued for all The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. AD 

2014–12–13 requires repetitive 

inspections for cracking of the aft 

support fitting for the main landing gear 

beam, and the rear spar upper chord and 

rear spar web in the area of rear spar 

station 224.14; and repair if necessary. 

AD 2014–12–13 refers to Boeing Special 

Attention Service Bulletin 737–57– 

1318, dated May 15, 2013, as the 

appropriate source of service 

information for accomplishing the 

required actions. 

For those airplanes that have not yet 

done the high frequency eddy current 

open-hole inspection specified in 

Boeing Special Attention Service 

Bulletin 737–57–1318, dated May 15, 

2013, this AD specifies using Boeing 

Alert Service Bulletin 737–57A1326, 

dated September 22, 2015, to do the 

eddy current inspections for any 

cracking in the inspar upper skin area 

near the rear spar at wing buttock line 

157. The eddy current inspections 

specified in Boeing Alert Service 

Bulletin 737–57A1326, dated September 

22, 2015, are intended to ensure there 

are no undetected cracks in the inspar 

upper skin area near the rear spar at 

wing buttock 157 prior to the 

accomplishment of the inspections 

specified in Boeing Special Attention 

Service Bulletin 737–57–1318, dated 

May 15, 2013. 

FAA’s Determination 

We are issuing 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. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Between the AD and the Service 

Information.’’ 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary action, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this AD. ‘‘Corrective actions’’ 

correct or address any condition found. 

Corrective actions in an AD could 

include, for example, repairs. 

Differences Between the AD and the 

Service Information 

Boeing Alert Service Bulletin 737– 

57A1326, dated September 22, 2015, 

specifies to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this AD requires 

repairing those conditions in one of the 

following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

The effectivity of Boeing Alert Service 

Bulletin 737–57A1326, dated September 

22, 2015, includes Group 1, 

configuration 1, airplanes. Those 

airplanes have been inspected using a 

high frequency eddy current open-hole 

inspection, in accordance with Boeing 

Special Attention Service Bulletin 737– 

57–1318, dated May 15, 2013. We have 

determined that only those airplanes 

that have not done the high frequency 

eddy current open-hole inspection, in 

accordance with Boeing Special 

Attention Service Bulletin 737–57– 

1318, dated May 15, 2013, are affected 

by the identified unsafe condition 

addressed in this AD. Therefore, we 

have excluded Group 1, configuration 1, 

airplanes from the applicability of this 

AD. 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations 65923 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as 

Required for Compliance (RC) in any 

service information identified 

previously have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

For service information that contains 

steps that are labeled as RC, the 

following provisions apply: (1) The 

steps labeled as RC, including substeps 

under an RC step and any figures 

identified in an RC step, must be done 

to comply with the AD, and an AMOC 

is required for any deviations to RC 

steps, including substeps and identified 

figures; and (2) steps not labeled as RC 

may be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an AMOC, provided the RC steps, 

including substeps and identified 

figures, can still be done as specified, 

and the airplane can be put back in an 

airworthy condition. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because cracking in the inspar 

upper skin and rear spar upper chord 

could result in the inability of the 

structure to carry limit load, or result in 

a fuel leak, which could prevent 

continued safe flight and landing. 

Therefore, we find that notice and 

opportunity for prior public comment 

are impracticable and that good cause 

exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2015–4205 and Directorate 

Identifier 2015–NM–149–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Costs of Compliance 

We estimate that this AD affects 495 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection ...... 1 work-hour × $85 per hour = $85 per inspection 

cycle.

$0 $85 per inspection cycle .. $42,075 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

One-time inspection ......................... 86 work-hours × $85 per hour = $7,310 ................................................... $0 $7,310 

Repair .............................................. 3,700 work-hours × $85 per hour = $314,500 .......................................... 0 314,500 

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 


Lhorne on DSK5TPTVN1PROD with RULES
65924 Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations 

(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): 

2015–21–08 The Boeing Company: 

Amendment 39–18301; Docket No. 

FAA–2015–4205; Directorate Identifier 

2015–NM–149–AD. 

(a) Effective Date 

This AD is effective November 12, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–100, –200, –200C, –300, –400, 

and –500 series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 737–57A1326, dated 

September 22, 2015; except for Group 1, 

configuration 1, airplanes identified in 

Boeing Alert Service Bulletin 737–57A1326, 

dated September 22, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report that an 

operator discovered a crack in the inspar 

upper skin at wing buttock line 157, just 

forward of the rear spar on the right wing. We 

are issuing this AD to detect and correct any 

cracking in the inspar upper skin and rear 

spar upper chord, which could result in the 

inability of the structure to carry limit load, 

or result in a fuel leak, which could prevent 

continued safe flight and landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Actions 

Except as provided by paragraph (h) of this 

AD, at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–57A1326, dated 

September 22, 2015: Do an eddy current 

inspection for any cracking in the inspar 

upper skin, and repair doublers and repair 

triplers, as applicable, and do all applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–57A1326, dated September 22, 2015; 

except as provided by paragraph (h) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the inspection thereafter at the 

applicable intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–57A1326, dated September 22, 

2015. 

(h) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

737–57A1326, dated September 22, 2015, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) The ‘‘Condition’’ column of table 2 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–57A1326, dated 

September 22, 2015, refers to total flight 

cycles ‘‘as of the original issue date of this 

service bulletin.’’ However, for this 

condition, this AD applies to the airplanes 

with the specified total flight cycles as of the 

effective date of this AD. 

(3) Although Boeing Alert Service Bulletin 

737–57A1326, dated September 22, 2015, 

specifies to contact Boeing for certain repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (j) of this 

AD. 

(i) Terminating Actions for Certain 

Airplanes 

For Group 1, configurations 5 through 7, 

airplanes specified in Boeing Alert Service 

Bulletin 737–57A1326, dated September 22, 

2015, accomplishment of any applicable high 

frequency eddy current inspection, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–57–1318, dated May 15, 

2013 (which was incorporated by reference 

in AD 2014–03–06, Amendment 39–17743 

(79 FR 12368, March 5, 2014), and continues 

to be incorporated by reference in AD 2014– 

12–13, Amendment 39–17874 (79 FR 39300, 

July 10, 2014)), terminates the repetitive 

inspections in paragraph (g) of this AD for 

those airplanes, provided if any cracking is 

found, repair is done before further flight 

using a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD. 

Note 1 to paragraph (i) of this AD: AD 

2014–12–13, Amendment 39–17874 (79 FR 

39300, July 10, 2014), refers to Boeing 

Special Attention Service Bulletin 737–57– 

1318, dated May 15, 2013, as the appropriate 

source of service information for 

accomplishing the actions required in that 

AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (k) of this AD. Information may be 

emailed to: 9-ANM-LAACO-AMOCRequests@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) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (h) of 

this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (j)(4)(i) and (j)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with this AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

For more information about this AD, 

contact Jennifer Tsakoumakis, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles ACO, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5264; fax: 562–627–5210; 

email: jennifer.tsakoumakis@faa.gov. 

(l) 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. 

(3) The following service information was 

approved for IBR on November 12, 2015. 

(i) Boeing Alert Service Bulletin 737– 

57A1326, dated September 22, 2015. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on April 9, 2014 (79 FR 

12368, March 5, 2014). 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 208 / Wednesday, October 28, 2015 / Rules and Regulations 65925 

(i) Boeing Special Attention Service 

Bulletin 737–57–1318, dated May 15, 2013. 

(ii) Reserved. 

(5) For Boeing 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. 

(6) 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. 

(7) 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 October 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26993 Filed 10–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0593; Directorate 

Identifier 2015–NE–08–AD; Amendment 39– 

18254; AD 2015–17–21] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce plc (RR) RB211–535E4–37, 

RB211–535E4–B–37, and RB211– 

535E4–C–37 turbofan engines. This AD 

requires reducing the cyclic life limits 

for certain high-pressure turbine (HPT) 

disks, removing those disks that have 

exceeded the new life limit, and 

replacing them with serviceable parts. 

This AD was prompted by RR updating 

the life limits for certain HPT disks. We 

are issuing this AD to prevent failure of 

the HPT disk, which could result in 

uncontained disk release, damage to the 

engine, and damage to the airplane. 

DATES: This AD becomes effective 

December 2, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 2, 2015. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, Corporate Communications, 

P.O. Box 31, Derby, England, DE24 8BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–249936; email: http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp; Internet: https:// 

www.aeromanager.com. You may view 

this service information at the FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, 

MA. For information on the availability 

of this material at the FAA, call 781– 

238–7125. It is also available on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0593. 

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–2015– 

0593; 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 mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7134; fax: 781–238– 

7199; email: wego.wang@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 the specified products. The 

NPRM was published in the Federal 

Register on April 29, 2015 (80 FR 

23737). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An engineering analysis, carried out by RR, 

of the lives of critical parts of the RB211– 

535E4–37 engine, has resulted in reduced 

cyclic life limits for certain high pressure 

(HP) turbine discs. The reduced limits are 

published in the RR RB211–535E4–37 Time 

Limits Manual (TLM): 05–10–01–800–000, 

current Revision dated July 2014. 

Operation of critical parts beyond these 

reduced cyclic life limits may result in part 

failure, possibly resulting in the release of 

high-energy debris, which may cause damage 

to the aeroplane and/or injury to the 

occupants. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 23737, April 29, 2015). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Task 05–00–01–800– 

000, ‘‘Recording and Control of the 

Lives of Parts’’, dated July 1, 2015, of 

the RR RB211–535E4–37/23 TLM, 

publication reference T–211(535)–6RR, 

Revision 49, dated July 1, 2015; and 

Task 05–10–01–800–000, ‘‘Group A 

Parts Lives—CONFIG–1’’, dated July 1, 

2014, of the RR RB211–535E4–37/23 

TLM, publication reference T–211(535)– 

6RR, Revision 49, dated July 1, 2015. 

This service information provides 

revised life limits for the affected HPT 

disks. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or see ADDRESSES for other ways to 

access this service information. 

Related Service Information 

We reviewed RR Non-Modification 

Service Bulletin (NMSB) No. RB.211– 

72–G188, Revision No. 1, dated October 

30, 2013. The NMSB describes the 

updated lifing analysis of the affected 

HPT disks. 

Costs of Compliance 

We estimate that this AD affects 650 

engines installed on airplanes of U.S. 

registry. We also estimate that it would 

take about 0 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. The pro-rated cost of 

required parts would be about $12,213 

per engine. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $7,938,450. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 


Lhorne on DSK5TPTVN1PROD with RULES