43972 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Proposed Rules 

(i) Visually inspect the hoist control 

pendant wiring harness (wiring harness) for 

chafing. The wiring harness is shown in 

Figure 1 of Airbus Helicopters Alert Service 

Bulletin (ASB) MBB–BK117 C–2–88A–009, 

Revision 0, dated June 18, 2014 (MBB–BK117 

C–2–88A–009). If there is chafing on the 

wiring harness protection sleeve such that 

any internal wiring is visible, or if there is 

chafing on any internal wire, replace the 

wiring harness. 

(ii) Install each wiring harness cable tie so 

that the cable tie heads do not contact any 

adjacent parts or wiring harnesses, as shown 

in Figure 3 of ASB MBB–BK117 C–2–88A– 

009. 

(2) Within the next 100 hours time-inservice, install a protection sleeve on the 

wiring harness and inspect each cable tie by 

following the Accomplishment Instructions, 

paragraph 3.B.3, of ASB MBB–BK117 C–2– 

88A–009. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Regulations Group, FAA, 

may approve AMOCs for this AD. Send your 

proposal to: George Schwab, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 10101 Hillwood 

Pkwy., Fort Worth, TX 76177; telephone 

(817) 222–5110; email george.schwab@

faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

(1) For service information identified in 

this 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 the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

TX 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2014–0211, dated September 19, 2014. 

You may view the EASA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2015–2994. 

(h) Subject 

Joint Aircraft System Component (JASC) 

Code: 5397 Fuselage Wiring. 

Issued in Fort Worth, Texas, on July 15, 

2015. 

Bruce E. Cain, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18049 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2959; Directorate 

Identifier 2015–NM–008–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 787–8 

airplanes. This proposed AD was 

prompted by reports indicating that the 

ram air turbine (RAT) assembly may fail 

to operate if deployed at low airspeeds. 

This proposed AD would require 

replacing either the RAT pump and 

control module assembly or the entire 

RAT assembly. We are proposing this 

AD to prevent failure of the RAT 

assembly to operate at low air speeds. 

The volume fuse on the RAT assembly 

may be activated in-flight before the 

RAT is deployed. This may lead to 

improper pump hydraulic pressure 

offloading when the RAT is needed. 

Failure of the RAT to operate in an all 

engine out event would result in loss of 

control of the airplane. 

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; 

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– 

2959. 

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– 

2959; 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: 

Sean J. Schauer, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6479; fax: 425–917–6590; email: 

sean.schauer@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– 

2015–2959; Directorate Identifier 2015– 

NM–008–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 

An engineering review by Boeing’s 

RAT supplier discovered that the RAT 

assembly may fail to operate if deployed 

at low airspeeds. A hydraulic fuse in the 

RAT control module is intended to 

remain open to enable RAT spin-up at 

low air speeds by off-loading the RAT 

hydraulic pump. After the RAT is 

spinning, the fuse sets and the pump 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Proposed Rules 43973 

output supplies power to the center 

hydraulic system. The supplier found 

that the fuse may prematurely set as a 

result of nominal leakage through the 

hydraulic pump and/or check valve, 

preventing the RAT from spinning up 

when deployed below 160 knots. This 

has been attributed to a design defect in 

the fuse. A RAT in service will spin up 

if deployed above 160 knots and remain 

operational as the airplane decelerates 

through the minimum RAT design 

speed of 130 knots. The premature 

setting of the RAT fuse can prevent the 

RAT from spinning up and providing 

emergency hydraulic power when 

deployed below 160 knots. In an all 

engine out event, an inoperative RAT 

would result in loss of control of the 

airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin B787–81205–SB290015–00, 

Issue 002, dated November 25, 2014. 

The service information describes 

procedures for replacing either the RAT 

pump and control module assembly or 

the RAT assembly including an 

installation test and corrective actions 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. Refer to this service 

information for details on the 

procedures and compliance times. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 12 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 

Replacement ................................... 7 work-hours × $85 per hour = 

$595.

N/A ................................................. $595 $7,140 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
43974 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Proposed Rules 

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– 

2015–2959; Directorate Identifier 2015– 

NM–008–AD. 

(a) Comments Due Date 

We must receive comments by September 

8, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 787–8 airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin B787–81205–SB290015–00, 

Issue 002, dated November 25, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic Power. 

(e) Unsafe Condition 

This AD was prompted by reports 

indicating that the ram air turbine (RAT) 

assembly may fail to operate if deployed at 

low airspeeds. We are issuing this AD to 

prevent failure of the RAT assembly to 

operate at low air speeds. The volume fuse 

on the RAT assembly may be activated inflight before the RAT is deployed. This may 

lead to improper pump hydraulic pressure 

offloading when the RAT is needed. Failure 

of the RAT to operate in an all engine out 

event would result in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

Within 36 months after the effective date 

of this AD, replace the RAT pump and 

control module assembly or the RAT 

assembly, including an installation test and 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin B787–81205– 

SB290015–00, Issue 002, dated November 25, 

2014. Do all applicable corrective actions 

before further flight. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Alert Service 

Bulletin B787–81205–SB290015–00, Issue 

001, dated September 4, 2014, which is not 

incorporated by reference in this AD. 

(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 

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) 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 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 Sean J. Schauer, Aerospace Engineer, 

Systems and Equipment Branch, ANM 130S, 

FAA, Seattle Aircraft Certification Office 

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

98057–3356; phone: 425–917–6479; fax: 425– 

917–6590; email: sean.schauer@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 16, 

2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18151 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2961; Directorate 

Identifier 2014–NM–145–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 supersede 

Airworthiness Directive (AD) 2012–15– 

13, which applies to certain The Boeing 

Company Model 747–100B SUD, 747– 

300, 747–400, and 747–400D series 

airplanes; and Model 747–200B series 

airplanes having a stretched upper deck. 

AD 2012–15–13 currently requires 

inspections for cracking and 

discrepancies of certain fasteners; 

modification of the frame-to-tension-tie 

joints; repetitive post-modification 

inspections; related investigative and 

corrective actions if necessary; and 

repetitive inspections for cracking in the 

tension tie channels, and repair if 

necessary. For certain airplanes, AD 

2012–15–13 also requires an inspection 

to determine if the angle is installed 

correctly, and re-installation if 

necessary; and an inspection at the 

fastener locations where the tension tie 

previously attached to the frame prior to 

certain modifications, and repair if 

necessary. Since we issued AD 2012– 

15–13, an evaluation indicated that the 

upper deck is subject to widespread 

fatigue damage (WFD). This proposed 

AD would add a new inspection for 

cracking in the tension tie channels and 

post-modification inspections of the 

modified tension ties for cracking, and 

repair if necessary. We are proposing 

this AD to prevent fatigue cracking of 

the tension ties, shear webs, and frames 

of the upper deck, which could result in 

rapid decompression and reduced 

structural integrity of the airplane. 

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 


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