
[Federal Register Volume 79, Number 152 (Thursday, August 7, 2014)]
[Proposed Rules]
[Pages 46201-46203]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-18664]


 ========================================================================
 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.
 
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 

  Federal Register / Vol. 79, No. 152 / Thursday, August 7, 2014 / 
Proposed Rules  

[[Page 46201]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0523; Directorate Identifier 2014-NM-050-AD]
RIN 2120-AA64


Airworthiness Directives; the Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 777-200 and -300 series airplanes 
equipped with Pratt and Whitney engines. This proposed AD was prompted 
by reports of blocked drain lines at the engine forward strut that 
caused flammable fluid to accumulate in a flammable leakage zone. This 
AD would require repetitive functional checks for blockage of the 
forward strut drain line, and doing corrective actions (including 
cleaning or replacing any blocked drain lines) if necessary; and a one-
time cleaning of certain forward strut drain lines. We are proposing 
this AD to detect and correct blockage of forward strut drain lines, 
which could cause flammable fluids to collect in the forward strut area 
and potentially cause an uncontrolled fire or cause failure of engine 
attachment structure and consequent airplane loss.

DATES: We must receive comments on this proposed AD by September 22, 
2014.

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.

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-2014-
0523; 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, 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-2014-0523; 
Directorate Identifier 2014-NM-050-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 more than five reports of the forward drain lines of 
the engine struts being blocked with coked particles. Coked particles 
form when hydraulic fluid is exposed to, and degraded by, the high 
temperatures of the hot core zone of the engine and the hot pneumatic 
bleed ducts. In two events, fluids backed up into the electrical (left) 
side of the disconnect box assembly of the strut system, causing an 
electrical fault that resulted in a false overheat detection engine 
indicating and crew-alerting system (EICAS) message. Flammable fluids 
collecting in the electrical side of the disconnect box assembly of the 
strut system can cause an electrical fault for electrical components, 
and create a potential ignition source for trapped flammable fluids 
that can lead to fuel explosion.
    In the other three events, flammable fluids backed up and pooled in 
the fluid (right) side of the disconnect box assembly of the strut 
system. Flammable fluids collecting in the disconnect box assembly of 
the strut system are a fire hazard because that area has no fire 
detection, containment, or extinguishing capability and with an 
ignition source can result in an uncontrolled fire in the strut. Also, 
flammable fluids pooling in the disconnect box assembly of the strut 
system can spill over onto the engine and initiate an engine fire in 
the engine core cavity compartment.
    Hydraulic fluid collecting in the disconnect box assembly of the 
strut system can cause contamination and hydrogen embrittlement of the 
titanium structure resulting in cracks that can compromise the engine 
firewall by allowing a fire in the engine area to enter the strut; or 
by allowing flammable fluids to leak down and initiate an engine fire 
in the engine core cavity compartment, and also compromise the engine 
fire extinguishing system. Hydraulic fluid contamination, including 
contamination

[[Page 46202]]

caused by hydraulic fluid in its liquid, vapor, and/or solid (i.e., 
coked) form, in the strut forward dry bay can lead to hydrogen 
embrittlement of the titanium fittings of the forward engine mount 
bulkhead and also the consequent inability of the fittings to carry 
engine loads, resulting in the loss or separation of an engine. 
Hydraulic embrittlement could also cause a through-crack formation 
across the fittings through which an engine fire could breach into the 
strut, resulting in an uncontained strut fire. We are proposing this AD 
to detect and correct blockage of forward strut drain lines, which 
could cause flammable fluids to collect in the forward strut area and 
potentially cause an uncontrolled fire or cause failure of engine 
attachment structure and consequent airplane loss.

Related Rulemaking

    On May 24, 2013, we issued AD 2013-11-14, Amendment 39-17474 (78 FR 
35749, June 14, 2013), for certain The Boeing Company Model 777-200 and 
-300 series airplanes. AD 2013-11-14 currently requires repetitive 
general visual inspections of the strut forward dry bay for hydraulic 
fluid contamination, and related investigative and corrective actions 
if necessary. AD 2013-11-14 was prompted by reports of hydraulic fluid 
contamination found in the strut forward dry bay. The actions required 
by AD 2013-11-14 are intended to detect and correct hydraulic fluid 
contamination of the strut forward dry bay that could result in 
hydrogen embrittlement of the titanium forward engine mount bulkhead 
fittings, and the consequent inability of the fittings to carry engine 
loads, resulting in engine separation.
    On April 12, 2011, we issued AD 2011-09-11, Amendment 39-16673 (76 
FR 24354, May 2, 2011), for certain The Boeing Company Model 777-200 
and -300 series airplanes. AD 2011-09-11 requires repetitive 
inspections for hydraulic fluid contamination of the interior of the 
strut disconnect assembly; repetitive inspections for discrepancies of 
the interior of the strut disconnect assembly, if necessary; repetitive 
inspections of the exterior of the strut disconnect assembly for 
cracks, if necessary; corrective action if necessary; and an optional 
terminating action for the inspections. AD 2011-09-11 resulted from 
reports of system disconnect boxes that have been contaminated with 
hydraulic fluid and, in one incident, led to subsequent cracking of 
titanium parts in the system disconnect assembly. We issued AD 2011-09-
11 to detect and correct hydraulic fluid contamination, which can cause 
cracking of titanium parts in the system disconnect assembly, resulting 
in compromise of the engine firewall.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 777-54-0027, 
Revision 1, dated September 12, 2013. For information on the procedures 
and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0523.

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 this same type design.

Proposed AD Requirements

    This AD would require repetitive functional checks for blockage of 
the forward strut drain line, doing corrective actions (including 
cleaning or replacing any blocked drain lines) if necessary; and a one-
time cleaning of certain forward strut drain lines. This proposed AD 
would require accomplishing the actions specified in the service 
information described previously.
    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.

Interim Action

    We consider this proposed AD interim action. The manufacturer is 
currently developing a modification that will address the unsafe 
condition identified in this AD. Once this modification is developed, 
approved, and available, we might consider additional rulemaking.

Costs of Compliance

    We estimate that this proposed AD affects 54 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
----------------------------------------------------------------------------------------------------------------
Repetitive functional checks of 2  9 work-hours x $85               $0  $765 per inspection  $41,310 per
 struts per inspection cycle.       per hour = $765                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
One-time cleaning................  13 work-hours x $85               0  $1,105.............  $59,670.
                                    per hour = $1,105.
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    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
----------------------------------------------------------------------------------------------------------------
Clean and repair drain tube        Up to 5 work-hours x $85   $0......................  Up to $425.
 assemblies in up to 2 struts.      per hour = $425.
Replace drain tube assemblies in   Up to 5 work-hours x $85   Up to $4,484............  Up to $4,909.
 up to 2 struts.                    per hour = $425.
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    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.

[[Page 46203]]

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 proposed 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-2014-0523; Directorate Identifier 
2014-NM-050-AD.

(a) Comments Due Date

    We must receive comments by September 22, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -300 
series airplanes, certificated in any category, equipped with Pratt 
& Whitney engines, as identified in Boeing Special Attention Service 
Bulletin 777-54-0027, Revision 1, dated September 12, 2013.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Unsafe Condition

    This AD was prompted by reports of blocked drain lines at the 
engine forward strut that caused flammable fluid to accumulate in a 
flammable leakage zone. We are proposing this AD to detect and 
correct blockage of forward strut drain lines, which could cause 
flammable fluids to collect in the forward strut area and 
potentially cause an uncontrolled fire or cause failure of engine 
attachment structure and consequent airplane loss.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Functional Check, Cleaning, and Corrective Actions

    At the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 777-54-
0027, Revision 1, dated September 12, 2013, except as provided by 
paragraph (h) of this AD, do the actions specified in paragraphs 
(g)(1) and (g)(2) of this AD, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-54-
0027, Revision 1, dated September 12, 2013. Repeat the functional 
check required by paragraph (g)(1) of this AD, thereafter at the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Boeing Special Attention Service Bulletin 777-54-0027, Revision 1, 
dated September 12, 2013.
    (1) Do a functional check for blockage of the forward strut 
drain line of the left and right strut, clean the forward strut 
drain line, and do all applicable corrective actions (including 
cleaning or replacing blocked drain tubes, repairing water leaks, 
and cleaning the inlet drain screen on the right system disconnect 
assembly inlet). Do all applicable corrective actions before further 
flight.
    (2) Do a one-time cleaning of the smaller forward strut drain 
lines connected to the left systems disconnect, the strut forward 
lower spar, and the forward fire seal pan inlets.

(h) Exception to the Service Information

    Where Boeing Special Attention Service Bulletin 777-54-0027, 
Revision 1, dated September 12, 2013, refers to a compliance time 
``after the Revision 1 date of this Service Bulletin,'' this AD 
requires compliance within the specified compliance time after the 
effective date of 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-AMOC-Requests@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.

(j) Related Information

    (1) For more information about this AD, contact Kevin Nguyen, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office, 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 July 30, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-18664 Filed 8-6-14; 8:45 am]
BILLING CODE 4910-13-P


