[Federal Register Volume 81, Number 52 (Thursday, March 17, 2016)]
[Proposed Rules]
[Pages 14402-14404]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-05831]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 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.
 
 ========================================================================
 

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

[[Page 14402]]



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: [email protected].

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

[[Page 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
----------------------------------------------------------------------------------------------------------------
                                                                                               Cost on  U.S.
            Action                 Labor cost           Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Install serviceable T/R halves  Up to 91 work-    Up to $7,338.........  Up to $15,073     Up to $829,015.
                                 hours x $85 per                          per airplane.
                                 hour = $7,735.
----------------------------------------------------------------------------------------------------------------

    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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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.

[[Page 14404]]

(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: [email protected].
    (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: 
[email protected].
    (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