72390 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 

standard rating of 95 °F dry bulb 

outdoor temperature) not less than the 

following: 

Product class 

Energy 

efficiency 

ratio 

(EER) 

(i) Split-system rated cooling 

capacity less than 45,000 

Btu/hr ................................. 12.2 

(ii) Split-system rated cooling 

capacity equal to or greater than 45,000 Btu/hr ........ 11.7 

(iii) Single-package systems 11.0 

Any outdoor unit model that has a 

certified combination with a rating 

below 14 SEER or the applicable EER 

cannot be installed in this region. An 

outdoor unit model certified below 14 

SEER or the applicable EER by the 

outdoor unit manufacturer cannot be 

installed in this region even with an 

independent coil manufacturer’s indoor 

unit that may have a certified rating at 

or above 14 SEER and the applicable 

EER. 

(5) Each basic model of single-package 

central air conditioners and central air 

conditioning heat pumps and each 

individual combination of split-system 

central air conditioners and central air 

conditioning heat pumps manufactured 

on or after January 1, 2015, shall have 

an average off mode electrical power 

consumption not more than the 

following: 

Product class 

Average 

off mode 

power 

consumption 

PW,OFF

(watts) 

(i) Split-system air conditioners ............................... 30 

(ii) Split-system heat pumps 33 

(iii) Single-package air conditioners ............................... 30 

(iv) Single-package heat 

pumps ............................... 33 

(v) Small-duct, high-velocity 

systems ............................. 30 

(vi) Space-constrained air 

conditioners ....................... 30 

(vii) Space-constrained heat 

pumps ............................... 33 

* * * * * 

[FR Doc. 2015–29435 Filed 11–18–15; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5914; Directorate 

Identifier 2014–SW–056–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Formerly Eurocopter 

France) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Airbus 

Helicopters Model SA341G and SA342J 

helicopters. This proposed AD would 

require repetitive inspections of a 

certain part-numbered main rotor hub 

torsion bar (torsion bar). This proposed 

AD is prompted by several cases of 

corrosion in the metal strands of the 

torsion bar. The proposed actions are 

intended to detect corrosion and 

prevent failure of the torsion bar, loss of 

a main rotor blade, and subsequent loss 

of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by January 19, 2016. 

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 by searching for 

and locating Docket No. FAA–2015– 

5914; 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, 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. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 10101 

Hillwood Pkwy, Fort Worth, Texas 

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 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, issued EASA AD No. 2014–0216, 

dated September 24, 2014, to correct an 

unsafe condition for Airbus Helicopters 

Model SA341G and SA342J helicopters. 

EASA advises that several cases of 

cracks were found on the polyurethane 

(PU) coating of part-numbered 

704A33633274 torsion bars installed on 

military Model SA341 helicopters. 

EASA states that these parts can also be 


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installed on civilian Model SA341 and 

SA342 helicopters. According to EASA, 

analysis of the cracked torsion bars 

showed small areas of superficial 

corrosion on the strands inside the bars 

can also develop during the 

manufacturing process. EASA states that 

cracking of the PU coating near these 

areas and the associated penetration of 

water can lead to further and deeper 

development of the corrosion. EASA 

advises that this condition, if not 

detected and corrected, allows water to 

penetrate into the torsion bar causing 

corrosion and failure of the metal 

strands inside the bar. Failure of the 

metal strands could lead to torsion bar 

failure, resulting in an in-flight loss of 

a main rotor blade and consequent loss 

of control of the helicopter. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Helicopters 

Gazelle work card 65.12.607, dated 

August 2008. This service information 

describes inspecting the torsion bars for 

a crack in the PU coating and for 

corrosion and thickness of the bushings. 

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. 

Other Related Service Information 

Airbus Helicopters has issued Alert 

Service Bulletin No. SA341/SA342– 

05.40, Revision 0, dated April 28, 2014 

(ASB), for Model SA341G and SA342J 

helicopters certificated by the FAA, and 

military Model SA341B, C, D, E, F, and 

H and SA342K, L, L1, M, M1, and Ma 

helicopters. The ASB specifies 

repetitively inspecting the torsion bars 

in accordance with certain work cards, 

including work card 65.12.07. These 

inspections are part of Airbus 

Helicopters’ current maintenance 

program, and the ASB revises the 

compliance time interval for the 

inspections. 

Proposed AD Requirements 

This proposed AD would require 

removing and performing repetitive 

inspections of each torsion bar for a 

crack in the PU coating, the dimension 

of the angle between the bushings, 

corrosion on the inside diameter of each 

bushing, the thickness of each bushing, 

the size of the inside diameter of each 

bushing, and missing varnish on the two 

faces of each bushing. This proposed 

AD would require replacing the torsion 

bar before further flight if there is a 

crack in the PU coating of a torsion bar 

that matches or exceeds the damage 

criteria, if the angle of the torsion bar is 

7 degrees or more, if any corrosion on 

a bushing cannot be removed by rubbing 

it with an abrasive pad, if the thickness 

of a bushing is less than 37.520 mm 

(1.477 in), or if the diameter of a 

bushing is larger than 21,040 mm (.828 

in). If varnish is missing from more than 

15 percent of the surface area from a 

face of a bushing, this proposed AD 

would require removing all varnish, 

finishing with an abrasive pad, and 

applying a coat of paint to the face of 

the bushing. 

Differences Between This Proposed AD 

and the EASA AD 

This proposed AD would require you 

to replace a torsion bar instead of 

returning it to the manufacturer for 

examination. 

Interim Action 

We consider this proposed AD to be 

an interim action. If final action is later 

identified, we might consider further 

rulemaking. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 33 helicopters of U.S. 

Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. We estimate $85 per work 

hour for labor. We estimate 8 work 

hours to inspect each helicopter at an 

estimated cost of $680 per helicopter 

and $22,440 for the fleet per inspection 

cycle. Replacing a torsion bar would 

cost $7,020 for required parts; no 

additional labor would be necessary. 

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, 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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): 

Airbus Helicopters (formerly Eurocopter 

France): Docket No. FAA–2015–5914; 

Directorate Identifier 2014–SW–056–AD. 


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72392 Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 

(a) Applicability 

This AD applies to Model SA341G and 

SA342J helicopters with a main rotor head 

torsion bar (torsion bar) part number 

704A33633274 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the coating of the torsion bar 

resulting in corrosion. This condition could 

result in failure of a torsion bar, loss of a 

main rotor blade, and subsequent loss of 

control of the helicopter. 

(c) Comments Due Date 

We must receive comments by January 19, 

2016. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) For each torsion bar with less than 5 

years since the first date of installation on 

any helicopter, within the compliance time 

shown in Table 1 to paragraph (e)(1) of this 

AD: 

(i) Remove the torsion bar and, using a 

magnifying glass with a maximum 

magnification level of 10X, visually inspect 

for a crack in the polyurethane (PU) coating 

of the torsion bar as depicted in Figure 1 of 

Airbus Helicopters Gazelle work card 

65.12.607, dated August 2008 (work card). 

Consider two cracks that are less than 5 mm 

(.196 in) apart as a single crack. If there is a 

crack in the PU coating that is more than 5 

mm (.196 in), replace the torsion bar before 

further flight. Do not rework the PU coating 

of the torsion bar in any way. 

(ii) Inspect the angle, dimension alpha, as 

depicted in View on Arrow F of Figure 1 of 

the work card. If the angle is 7 or more 

degrees, replace the torsion bar before further 

flight. 

(iii) Inspect each bushing for corrosion on 

the inside diameter. If any corrosion cannot 

be removed by rubbing it with an abrasive 

pad, replace the torsion bar before further 

flight. 

(iv) Using an outside micrometer, measure 

the thickness, dimension a, of each bushing 

as depicted in Detail AA of Figure 1 of the 

work card. If the thickness is less than 37.520 

mm (1.477 in), replace the torsion bar before 

further flight. 

(v) Using an inside micrometer, measure 

the inside diameter, dimension b, of each 

bushing as depicted in Detail AA of Figure 

1 of the work card. If the diameter is larger 

than 21.040 mm (.828 in), replace the torsion 

bar before further flight. 

(vi) Inspect the two faces of each bushing 

for missing varnish. If varnish is missing 

from more than 15% of the surface area on 

a face of a bushing, before further flight, 

remove all varnish using 400-grit abrasive 

paper. Finish with an abrasive pad and apply 

a coat of P05 paint to the face of the bushing. 

TABLE 1 TO PARAGRAPH (e)(1) 

Time accumulated on torsion bar Compliance time 

(i) Less than 320 hours time-in-service (TIS) since new and has never 

been inspected in accordance with Airbus Helicopters 341G–342J 

Airworthiness Limitations, Revision 18, dated June 2014 (limitations 

inspection).

Before accumulating 420 hours TIS since new or within 24 months 

since the date of first installation on any helicopter, whichever occurs 

first. 

(ii) 320 or more hours TIS since new and has never had a limitations 

inspection.

Within 100 hours TIS, or before accumulating 600 hours TIS since 

new, or within 24 months since the date of first installation on any 

helicopter, whichever occurs first. 

(iii) Less than 320 hours TIS since the last limitations inspection ........... Before accumulating 420 hours TIS since the last limitations inspection 

or within 24 months since the last limitations inspection, whichever 

occurs first. 

(iv) 320 or more hours TIS since the last limitations inspection .............. Within 100 hours TIS, or before accumulating 600 hours TIS since the 

last limitations inspection, or within 24 months since the last limitations inspection, whichever occurs first. 

(2) For each torsion bar with 5 or more 

years since the first date of installation on 

any helicopter, within the compliance time 

shown in Table 2 to paragraph (e)(2) of this 

AD, do the inspections required by 

paragraphs (e)(1)(i) through (vi) of this AD. 

TABLE 2 TO PARAGRAPH (e)(2) 

Time accumulated on torsion bar Compliance time 

(i) Less than 320 hours TIS since new, and less than 6 months since 

the date of first installation on any helicopter, and has never had a 

limitations inspection.

Before accumulating 420 hours TIS since new or within 12 months 

since the date of first installation on any helicopter, whichever occurs 

first. 

(ii) 320 or more hours TIS since new or more than 6 months since the 

date of first installation on any helicopter, and has never had a limitations inspection.

Within 100 hours TIS, or within 6 months, or before accumulating 600 

hours TIS since new, or within 24 months since the date of first installation on any helicopter, whichever occurs first. 

(iii) Less than 320 hours TIS since last limitations inspection and less 

than 6 months since the last limitations inspection.

Before accumulating 420 hours TIS since last limitations inspection or 

12 months since last limitations inspection, whichever occurs first. 

(iv) 320 or more hours TIS since last limitations inspection or 6 or more 

months since the last limitations inspection.

Within 100 hours TIS, or within 6 months, or before accumulating 600 

hours TIS since the last limitations inspection, or within 24 months 

since the last limitations inspection, whichever occurs first. 

(3) Repeat the inspections required by 

paragraphs (e)(1)(i) through (vi) of this AD as 

follows: 

(i) For torsion bars with less than 6 years 

since the date of installation on any 

helicopter, at intervals not to exceed 420 

hours TIS or 24 months, whichever occurs 

first. 

(ii) For torsion bars with 6 or more years 

since the date of installation on any 

helicopter, at intervals not to exceed 420 

hours TIS or 12 months, whichever comes 

first. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 10101 Hillwood Pkwy, Fort 

Worth, TX 76177; telephone (817) 222–5110; 

email 9-ASW-FTW-AMOC-Requests@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 


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Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 72393 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

(1) Airbus Helicopters Alert Service 

Bulletin ASB No. SA341/SA342–05.40, 

Revision 0, dated April 28, 2014, which is 

not incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Airbus Helicopters, 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. 2014–0216, dated September 24, 2014. 

You may view the EASA AD on the Internet 

at http://www.regulations.gov in the AD 

Docket. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700 Main Rotor. 

Issued in Fort Worth, Texas, on November 

9, 2015. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–29402 Filed 11–18–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5808; Directorate 

Identifier 2015–NM–111–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 of water leakage 

from the potable water system due to 

improperly installed waterline 

couplings, and water leaking into the 

electronics equipment (EE) bays from 

above the floor in the main cabin, 

resulting in water on the equipment in 

the EE bays. This proposed AD would 

require replacing the potable waterline 

couplings above the forward and aft EE 

bays with new, improved couplings. 

This proposed AD would also require 

sealing the main cabin floor areas above 

the aft EE bay, installing drip shields 

and foam blocks, and rerouting the wire 

bundles near the drip shields above the 

equipment in the aft EE bay. We are 

proposing this AD to prevent a water 

leak from an improperly installed 

potable water system coupling, or main 

cabin water source, which could cause 

the equipment in the EE bays to become 

wet, resulting in an electrical short and 

potential loss of system functions 

essential for safe flight. 

DATES: We must receive comments on 

this proposed AD by January 4, 2016. 

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– 

5808. 

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– 

5808; 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: 

Susan L. Monroe, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6457; 

fax: 425–917–6590; email: 

susan.l.monroe@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– 

2015–5808; Directorate Identifier 2015– 

NM–111–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 received reports of water leakage 

from the potable water system due to 

improperly installed waterline 

couplings, and water leaking into the EE 

bays from above the floor in the main 

cabin, resulting in water on the 

equipment in the EE bays. Such leakage 

could result in an electrical short and 

potential loss of system functions 

essential for safe flight. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information: 

• Boeing Alert Service Bulletin B787– 

81205–SB380009–00, Issue 001, dated 

March 26, 2015. 

• Boeing Alert Service Bulletin B787– 

81205–SB530029–00, Issue 001, dated 

March 26, 2015. 

• Boeing Alert Service Bulletin B787– 

81205–SB530031–00, Issue 001, dated 

March 26, 2015. 

This service information describes 

procedures for replacing the potable 

waterline couplings above the forward 

and aft EE bays with new, improved 

couplings; sealing the floors, seat tracks, 

and lavatories above the aft EE bay; 

installing drip shields and foam blocks; 

and rerouting the wire bundles adjacent 

to the drip shields above the aft EE bay. 


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