This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

14402 

Vol. 81, No. 52 

Thursday, March 17, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4225; Directorate 

Identifier 2015–NM–139–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 The 

Boeing Company Model 777–200 and 

–300 series airplanes equipped with 

Rolls-Royce Model Trent 800 engines. 

This proposed AD was prompted by 

reports of damage to the upper 

bifurcation forward fire seal and seal 

deflector, and localized damage to the 

insulation blanket installed just aft of 

the fire seal. This proposed AD would 

require installing serviceable thrust 

reverser (T/R) halves on the left and 

right engines. We are proposing this AD 

to prevent a breach in the engine 

firewall due to a failed upper 

bifurcation forward fire seal. A breach 

could delay or prevent the fire detection 

and suppression system from 

functioning properly, and could result 

in an increased risk of a fire, prolonged 

burning, and breach of the fire zone; and 

could allow fire to reach unprotected 

areas of the engine, the strut, and wing 

after engine shutdown. Also, fan air 

bypassing the fire seal could cause 

localized damage to the T/R insulation 

blanket installed just aft of the fire seal, 

which could allow limited thermal 

degradation of the thrust reverser inner 

wall. This could aggravate existing 

damage and cause the thrust reverser’s 

inner wall to fail. 

DATES: We must receive comments on 

this proposed AD by May 2, 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 NPRM, 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–2016– 

4225. 

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–2016– 

4225; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6501; 

fax: 425–917–6590; email: 

kevin.nguyen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2016–4225; Directorate Identifier 2015– 

NM–139–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 damage to the 

upper bifurcation forward fire seal and 

seal deflector. The damage included 

cracking, wear, and missing material on 

the fire seal; and cracking and wear on 

the seal deflector. There was also a 

report of localized damage to the 

insulation blanket installed just aft of 

the damaged fire seal. Boeing has 

determined that a design deficiency is 

the most probable root cause for the 

damage to the upper bifurcation forward 

fire seal and seal deflector. A 

combination of factors including 

operational pressure differential and 

seal deflections that the system is 

subjected to during high thrust 

operation were not accounted for in the 

design. This design deficiency allows 

the upper bifurcation forward fire seal 

to allow air to bypass the sealing 

interface at the unsupported section, 

which, over time, damages the upper 

bifurcation forward fire seal and seal 

deflector. 

The T/R firewall seal is an integral 

part of the fire suppression system for 

the engine core compartment. A 

damaged upper bifurcation forward fire 

seal and seal deflector can result in a 

breach of the engine firewall and allow 

airflow into the engine fire zone, which 

can decrease the effectiveness of the 

engine fire detection and suppression 

systems due to excess fan air entering 

the core compartment fire zone. A 

breach in the engine firewall could 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules 14403 

delay or prevent the fire detection and 

suppression system from functioning 

properly, and could result in an 

increased risk of a fire, prolonged 

burning, and potential breach of the fire 

zone. A breach of the fire wall could 

allow fire to reach unprotected areas of 

the engine, strut, and wing after engine 

shutdown. Also, engine fan air 

bypassing the seal could cause localized 

damage to the T/R insulation blanket 

installed just aft of the fire seal, which 

could allow limited thermal degradation 

of the thrust reverser inner wall. This 

could aggravate existing damage and 

cause the thrust reverser’s inner wall to 

fail. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Special 

Attention Service Bulletin 777–78– 

0101, Revision 1, dated October 30, 

2015. The service information describes 

procedures for installing serviceable left 

and right T/R halves on the left and 

right engines. 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. 

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. 

Differences Between This Proposed AD 

and the Service Information 

The service information specifies the 

compliance time as 1,875 days. For this 

proposed AD, we specified a 

compliance time of 60 months. 

Other Relevant Rulemaking 

We have issued additional proposed 

rulemaking related to the T/Rs for 

Model 777–200 and –300 series 

airplanes equipped with Rolls-Royce 

Model RB211–Trent 800 engines. We 

issued a supplemental NPRM (SNPRM), 

Docket No. FAA–2011–0027, Directorate 

Identifier 2010–NM–127–AD, that 

published in the Federal Register on 

September 25, 2015 (80 FR 57744). The 

SNPRM proposes to require repetitive 

inspections requirements for T/R halves 

having a thermal protective system 

installed. The SNPRM also proposes to 

require installation of serviceable T/R 

halves. The SNPRM also proposes to 

revise the maintenance or inspection 

program by incorporating new 

airworthiness limitations. 

Costs of Compliance 

We estimate that this proposed AD 

affects 55 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 

Install serviceable T/R halves ...... Up to 91 work-hours × $85 per 

hour = $7,735.

Up to $7,338 .... Up to $15,073 per airplane .......... Up to $829,015. 

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. 

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– 

2016–4225; Directorate Identifier 2015– 

NM–139–AD. 

(a) Comments Due Date 

We must receive comments by May 2, 

2016. 

(b) Affected ADs 

None. 


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14404 Federal Register / Vol. 81, No. 52 / Thursday, March 17, 2016 / Proposed Rules 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 and -300 series airplanes 

equipped with Rolls-Royce Model Trent 800 

engines. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine Exhaust. 

(e) Unsafe Condition 

This AD was prompted by reports of 

damage to the upper bifurcation forward fire 

seal and seal deflector, and localized damage 

to the insulation blanket installed just aft of 

the fire seal. We are issuing this AD to 

prevent a breach in the engine firewall due 

to a failed upper bifurcation forward fire seal. 

A breach could delay or prevent the fire 

detection and suppression system from 

functioning properly, and could result in an 

increased risk of a fire, prolonged burning, 

and breach of the fire zone; and could allow 

fire to reach unprotected areas of the engine, 

the strut, and wing after engine shutdown. 

Also, fan air bypassing the seal could cause 

localized damage to the thrust reverser (T/R) 

insulation blanket installed just aft of the fire 

seal, which could allow limited thermal 

degradation of the thrust reverser inner wall. 

This could aggravate existing damage and 

cause the thrust reverser’s inner wall to fail. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation of Serviceable T/R Halves on 

Each Engine 

Within 60 months after the effective date 

of this AD: Install serviceable left and right 

T/R halves on the left and right engines, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–78–0101, Revision 1, 

dated October 30, 2015. A serviceable T/R 

half is defined in the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–78–0101, Revision 1, 

dated October 30, 2015. 

(h) 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 (i) 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, 

modification, or alteration 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. To be 

approved, the repair method, modification 

deviation, or alteration deviation 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 (h)(4)(i) and (h)(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. 

(i) Related Information 

(1) For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6501; fax: 425–917–6590; 

email: kevin.nguyen@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

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

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

may 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 March 9, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–05831 Filed 3–16–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4226; Directorate 

Identifier 2015–NM–095–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2003–25– 

07 for certain Airbus Model A319 and 

A320 series airplanes; and AD 2005–13– 

39 for certain Airbus Model A321 series 

airplanes. AD 2003–25–07 currently 

requires a revision to the airplane flight 

manual (AFM) and replacement of both 

elevator aileron computers (ELACs) 

having L80 standards with new ELACs 

having L81 standards. AD 2005–13–39 

currently requires a revision to the 

AFM, replacement of existing ELACs 

with ELACs having either L83 or L91 

standards, as applicable; and a 

concurrent action. Since we issued AD 

2003–25–07 and AD 2005–13–39, we 

have determined that new ELAC 

standards must be incorporated. The 

ELAC standards have been upgraded to 

version L97+, which implements 

enhanced angle-of-attack (AOA) 

monitoring to better detect AOA 

blockage, including multiple AOA 

blockages. This proposed AD would 

require replacing existing ELACs with 

new ELACs having L97+ standards or 

revising the software in an existing 

ELAC to the L97+ standards, as 

applicable, which would terminate the 

requirements of AD 2003–25–07 and AD 

2005–13–39. This proposed AD would 

also add Airbus Model A318 series 

airplanes to the applicability. We are 

proposing this AD to prevent 

inadvertent activation of the AOA 

protections. Inadvertent activation of 

the AOA protections could result in a 

continuous nose down pitch rate that 

could result in reduced controllability 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 2, 2016. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 


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