43642 Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules 

(2) The analysis will include an 

assessment of the projected losses, net 

income, and pro forma capital levels 

and regulatory capital ratios and other 

capital ratios for the covered company 

and use such analytical techniques that 

the Board determines are appropriate to 

identify, measure, and monitor risks of 

the covered company that may affect the 

financial stability of the United States. 

* * * * * 

■ 10. Section 252.45 is amended by 

revising paragraph (b)(2) to read as 

follows: 

§ 252.45 Data and information required to 

be submitted in support of the Board’s 

analyses. 

* * * * * 

(b) * * * 

(2) Project a company’s pre-provision 

net revenue, losses, provision for loan 

and lease losses, and net income; and, 

pro forma capital levels, regulatory 

capital ratios, and any other capital ratio 

specified by the Board under the 

scenarios described in § 252.44(b). 

* * * * * 

■ 11. Section 252.52 is amended by: 

■ a. Revising paragraph (n); and 

■ b. removing paragraph (t). 

The revision to read as follows: 

§ 252.52 Definitions. 

* * * * * 

(n) Regulatory capital ratio means a 

capital ratio for which the Board 

established minimum requirements for 

the company by regulation or order, 

including the company’s tier 1 and 

supplementary leverage ratios as 

calculated under 12 CFR part 217, 

including the deductions required 

under 12 CFR 248.12, as applicable, and 

the company’s common equity tier 1, 

tier 1, and total risk-based capital ratios 

as calculated under 12 CFR part 217, 

including the deductions required 

under 12 CFR 248.12 and the transition 

provisions at 12 CFR 217.1(f)(4) and 12 

CFR 217.300, or any successor 

regulation; except that, the company 

shall not use the advanced approaches 

to calculate its regulatory capital ratios. 

* * * * * 

■ 12. Section 252.53 is amended by 

revising paragraph (b)(3) to read as 

follows: 

§ 252.53 Applicability. 

* * * * * 

(b) * * * 

(3) Transition periods for covered 

companies subject to the supplementary 

leverage ratio. Notwithstanding 

§ 252.52(n) of this subpart, only for 

purposes of the stress test cycle 

beginning on January 1, 2016, a bank 

holding company shall not include an 

estimate of its supplementary leverage 

ratio. 

* * * * * 

■ 13. Section 252.56 is amended by 

revising paragraphs (a)(2), (b)(2)(i), and 

(b)(2)(iv) to read as follows: 

§ 252.56 Methodologies and practices. 

(a) * * * 

(2) The potential impact on pro forma 

regulatory capital levels and pro forma 

capital ratios (including regulatory 

capital ratios and any other capital 

ratios specified by the Board), 

incorporating the effects of any capital 

actions over the planning horizon and 

maintenance of an allowance for loan 

losses appropriate for credit exposures 

throughout the planning horizon. 

(b) * * * 

(2) * * * 

(i) Common stock dividends equal to 

the quarterly average dollar amount of 

common stock dividends that the 

company paid in the previous year (that 

is, the first quarter of the planning 

horizon and the preceding three 

calendar quarters) plus common stock 

dividends attributable to issuances 

related to expensed employee 

compensation; 

* * * * * 

(iv) An assumption of no issuances of 

common stock or preferred stock, except 

for issuances related to expensed 

employee compensation or in 

connection with a planned merger or 

acquisition to the extent that the merger 

or acquisition is reflected in the covered 

company’s pro forma balance sheet 

estimates. 

* * * * * 

■ 14. Section 252.58 is amended by 

revising paragraphs (b)(3)(v), (b)(4), and 

(c)(2) to read as follows: 

§ 252.58 Disclosure of stress test results. 

* * * * * 

(b) * * * 

(3) * * * 

(v) Pro forma regulatory capital ratios 

and any other capital ratios specified by 

the Board; 

(4) An explanation of the most 

significant causes for the changes in 

regulatory capital ratios; and 

* * * * * 

(c) * * * 

(2) The disclosure of pro forma 

regulatory capital ratios and any other 

capital ratios specified by the Board that 

is required under paragraph (b) of this 

section must include the beginning 

value, ending value, and minimum 

value of each ratio over the planning 

horizon. 

* * * * * 

By order of the Board of Governors of the 

Federal Reserve System, July 17, 2015. 

Margaret McCloskey Shanks, 

Deputy Secretary of the Board. 

[FR Doc. 2015–18038 Filed 7–22–15; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2958; Directorate 

Identifier 2014–NM–248–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 all The 

Boeing Company Model 787 airplanes. 

This proposed AD was prompted by the 

disclosure that the inner diameters of 

some batches of landing gear pins were 

not shot peened in accordance with 

design specifications and need to be 

replaced. This proposed AD would 

require inspection for improperly 

manufactured landing gear pins, and 

replacement if necessary. We are 

proposing this AD to detect and correct 

insufficient shot peening that could lead 

to stress corrosion cracking and failure 

of the landing gear pin, and cause 

landing gear collapse and inability to 

control the airplane at high speeds on 

the ground. 

DATES: We must receive comments on 

this proposed AD by September 8, 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. 

• 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 proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

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Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules 43643 

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– 

2958. 

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– 

2958; 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: 

Melanie Violette, Senior Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6422; fax: 425–917–6590; email: 

melanie.violette@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–2958; Directorate Identifier 2014– 

NM–248–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 have received a report indicating 

that the inner diameters of some batches 

of landing gear pins were not shot 

peened and need to be replaced. On 

high strength steel parts, shot peening 

increases fatigue life and reduces the 

likelihood of stress corrosion cracking. 

Stress corrosion cracking, if not 

corrected, could result in failure of the 

landing gear pin, and consequent 

landing gear collapse and the inability 

to control the airplane at high speeds on 

the ground. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin B787–81205–SB320022–00, 

Issue 001, dated November 14, 2014. 

The service information describes 

procedures for the inspection for 

improperly manufactured landing gear 

pins (parts that were not shot peened), 

and replacement if necessary. 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 NPRM. 

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 require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ Refer to 

this service information for details on 

the procedures and compliance times. 

Differences Between This Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin B787– 

81205–SB320022–00, Issue 001, dated 

November 14, 2014, limits the 

effectivity in Group 2 to airplanes 

delivered prior to the publication of 

Boeing Alert Service Bulletin B787– 

81205–SB320022–00, Issue 001, dated 

November 14, 2014. However, this 

NPRM does not propose to include that 

limitation. The applicability of this 

proposed AD includes all The Boeing 

Company Model 787 airplanes. Because 

the affected landing gear pins are rotable 

parts, we have determined that these 

parts could later be installed on 

production airplanes, thereby subjecting 

those airplanes to the unsafe condition. 

This difference has been coordinated 

with Boeing. 

Costs of Compliance 

We estimate that this proposed AD 

affects 13 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 

Inspection ........................................................ 3 work-hours × $85 per hour = $255 ............. $0 $255 $3,315 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replacement ............................................ Up to 19 work-hours × $85 per hour = 

$1,615.

$35,569 Up to $37,184 

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43644 Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules 

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 RC 

(required for compliance) 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 Required for 

Compliance (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. 

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 adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2015–2958; Directorate Identifier 2014– 

NM–248–AD. 

(a) Comments Due Date 

We must receive comments by September 

8, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 787 airplanes, certificated in 

any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Unsafe Condition 

This AD was prompted by the disclosure 

that the inner diameters of some batches of 

landing gear pins were not shot peened in 

accordance with design specifications and 

need to be replaced. We are issuing this AD 

to detect and correct insufficient shot 

peening that could lead to stress corrosion 

cracking and failure of the landing gear pin, 

and cause landing gear collapse and inability 

to control the airplane at high speeds on the 

ground. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Replacement 

At the applicable time specified in 

paragraph 5, ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin B787–81205–SB320022–00, 

Issue 001, dated November 14, 2014, do a 

landing gear pin part number and serial 

number inspection, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin B787–81205–SB320022–00, 

dated November 14, 2014. A review of 

airplane maintenance or delivery records is 

acceptable in lieu of this inspection if the 

part number and serial number of the 

installed landing gear pins can be 

conclusively determined from that review. 

(1) If no part number or serial number is 

found that matches the list of affected pin 

numbers: No further action is required by 

this paragraph at that pin location. 

(2) If any part number or serial number is 

found that matches the list of affected pin 

numbers: At the applicable time specified in 

paragraph 5, ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin B787–81205–SB320022–00, 

Issue 001, dated November 14, 2014, replace 

the affected pin with a pin that does not have 

an affected part number and serial number, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

B787–81205–SB320022–00, Issue 001, dated 

November 14, 2014. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install on any airplane a landing 

gear pin having an affected part or serial 

number identified in Boeing Alert Service 

Bulletin B787–81205–SB320022–00, Issue 

001, dated November 14, 2014. 

(i) 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 

paragraph (j)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-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 

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Federal Register / Vol. 80, No. 141 / Thursday, July 23, 2015 / Proposed Rules 43645 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

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) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) 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 the 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Melanie Violette, Senior Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6422; fax: 425– 

917–6590; email: melanie.violette@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 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. 

Issued in Renton, Washington, on July 14, 

2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–17955 Filed 7–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2568; Directorate 

Identifier 2014–SW–026–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2014–07– 

52 for certain Airbus Helicopters 

(previously Eurocopter France) Model 

AS350B, AS350BA, AS350B1, 

AS350B2, AS350B3, AS350C, AS350D, 

AS350D1, AS355E, AS355F, AS355F1, 

AS355F2, AS355N, and AS355NP 

helicopters. AD 2014–07–52 currently 

requires repetitively inspecting certain 

reinforcement angles of the rear 

structure to tailboom junction frame 

(reinforcement angles) for a crack at 10 

hour time-in-service (TIS) intervals, 

repairing any cracked reinforcement 

angle, and allows an optional repetitive 

inspection with a 165 hour TIS 

inspection interval as a terminating 

action for the 10 hour TIS inspections. 

This proposed AD would retain the 

inspection requirements of AD 2014– 

07–52 and require the inspection of the 

area around each reinforcement angle 

screw hole as terminating action to the 

10 hour TIS inspections. These 

proposed actions are intended to detect 

a crack in the reinforcement angle, 

which if not corrected, could result in 

loss of the tailboom and subsequent loss 

of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by September 21, 

2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

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

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

European Aviation Safety Agency 

(EASA) AD, the economic evaluation, 

any comments received and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this proposed AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On May 21, 2014, we issued AD 

2014–07–52, Amendment 39–17858, 79 

FR 33054, June 10, 2014) for Airbus 

Helicopters Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350B3, AS350C, 

AS350D, AS350D1, AS355E, AS355F, 

AS355F1, AS355F2, AS355N, and 

AS355NP helicopters with Modification 

(MOD) 07 3215 installed or with a 

reinforcement angle, part-number (P/N) 

350A08.2493.21 or 350A08.2493.23, 

installed. AD 2014–07–52 requires, for 

helicopters with 640 or more hours TIS, 

within 10 hours TIS and thereafter at 

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