[Federal Register Volume 79, Number 41 (Monday, March 3, 2014)]
[Proposed Rules]
[Pages 11725-11728]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-04568]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0128; Directorate Identifier 2013-NM-133-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 The 
Boeing Company Model airplanes equipped with Rolls-Royce Trent 800 
series engines. This proposed AD was prompted by reports of in-flight 
separation of the aft plug from the forward plug, which are the two 
parts of the turbine exhaust plug assembly. This proposed AD would 
require installation of a serviceable turbine exhaust plug assembly 
(for certain airplanes), and a general visual inspection (for certain 
airplanes) to determine the diameter of the bolt used at the forward 
and aft plug interface, and applicable corrective actions. We are 
proposing this AD to prevent separation of the forward plug from the 
aft plug of the turbine exhaust plug assembly, which could result in 
parts departing the airplane and hitting the empennage or hitting a 
person on the ground, and destabilizing the airplane during a critical 
flight phase; parts remaining on a runway could cause damage to another 
airplane.

DATES: We must receive comments on this proposed AD by April 17, 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

[[Page 11726]]

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; 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, Seattle Aircraft Certification Office 
(ACO) FAA, 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-2014-0128; 
Directorate Identifier 2013-NM-133-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 in-flight separation of the aft plug from 
the forward plug, which are the two parts of the turbine exhaust plug 
assembly. A subsequent investigation showed that some of the interface 
bolts were found loose or missing. The turbine exhaust plug assembly 
was sent for analysis and it was found that the remaining bolts had 
less than the necessary minimum run-on torque value. It was also found 
that the operator of the analyzed turbine exhaust plug assembly had 
disassembled it a minimum of three times during maintenance actions. 
Repeated assembly and disassembly causes the locking property of the 
nut on the nutplate to wear out and subsequently let the bolts become 
loose or removed in service. This condition, if not corrected, could 
result in parts departing the airplane and hitting the empennage or 
hitting a person on the ground, and destabilizing the airplane during a 
critical flight phase; parts remaining on a runway could cause damage 
to another airplane.

Relevant Service Information

    We reviewed Boeing Special Attention Service Bulletin 777-78-0051, 
Revision 3, dated August 23, 2012. For information on the procedures 
and compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA 2014-0128.

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 these same type 
designs.

Proposed AD Requirements

    This proposed AD would require installation of a serviceable 
turbine exhaust plug assembly (for certain airplanes), and a general 
visual inspection (for certain airplanes) to determine the diameter of 
the bolt used at the forward and aft plug interface, and applicable 
corrective actions.
    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.

Differences Between the Proposed AD and the Service Information

    The applicability of the proposed AD and the effectivity of Boeing 
Special Attention Service Bulletin 777-78-0051, Revision 3, dated 
August 23, 2012, both include Model 777 airplanes equipped with Rolls-
Royce Trent 800 series engines. Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, however, is 
further limited to airplanes with line numbers before line position 
470. Because we have determined that these engines are interchangeable 
among the Model 777 airplane fleet, this proposed AD would apply to all 
line positions of Model 777 airplanes equipped with Rolls-Royce Trent 
800 engines, and would prohibit installation of non-serviceable turbine 
exhaust plug assemblies on any affected airplane.
    Boeing Special Attention Service Bulletin 777-78-0051, Revision 3, 
dated August 23, 2012, does not specify a compliance time for 
accomplishing one of the corrective actions. In Table 2 of paragraph 
1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 777-
78-0051, Revision 3, dated August 23, 2012, the condition ``Only \1/4\ 
inch diameter bolts are found installed at all 33 locations forward and 
aft plug interface'' has a corrective action to ``reidentify the 
forward and aft plug'' with a compliance time of ``none.'' However, in 
paragraph (g)(2) of this proposed AD, the compliance time is ``before 
further flight'' for doing all applicable corrective actions, which 
includes reidentifying the forward and aft plug.
    Boeing Special Attention Service Bulletin 777-78-0051, Revision 3, 
dated August 23, 2012, specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 35 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 11727]]



                                                 Estimated Costs
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                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
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Installation.......................  5 work-hours x $85 per hour              $0            $425         $14,875
                                      = $425.
General visual inspection..........  2 work-hours x $85 per hour               0             170           5,950
                                      = $170.
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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 
this replacement:

                                               On-Condition Costs
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                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement (replacing the \3/16\ inch bolts    5 work-hours x $85 per hour =                 $0            $425
 with \1/4\ inch bolts).                         $425.
----------------------------------------------------------------------------------------------------------------

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-2014-0128; Directorate Identifier 
2013-NM-133-AD.

(a) Comments Due Date

    We must receive comments by April 17, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes; certificated in any 
category; equipped with Rolls-Royce Trent 800 series engines.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Engine 
Exhaust.

(e) Unsafe Condition

    This AD was prompted by reports of in-flight separation of the 
aft plug from the forward plug, which are the two parts of the 
turbine exhaust plug assembly. We are issuing this AD to prevent 
separation of the forward plug from the aft plug of the turbine 
exhaust plug assembly, which could result in parts departing the 
airplane and hitting the empennage or hitting a person on the 
ground, and destabilizing the airplane during a critical flight 
phase; parts remaining on a runway could cause damage to another 
airplane.

(f) Compliance

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

(g) Installation and General Visual Inspection

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 777-78-
0051, Revision 3, dated August 23, 2012, except as provided by 
paragraph (i) of this AD, do the applicable actions specified in 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in accordance with 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 3, dated August 23, 2012.
    (1) For airplanes identified as Group 1, Configuration 1, in 
Boeing Special Attention Service Bulletin 777-78-0051, Revision 3, 
dated August 23, 2012: Install a serviceable turbine exhaust plug 
assembly.
    (2) For airplanes identified as Group 1, Configurations 2 and 3, 
in Boeing Special Attention Service Bulletin 777-78-0051, Revision 
3, dated August 23, 2012: Do a general visual inspection to 
determine the diameter of the bolt used at the forward and aft plug 
interface, and before further flight, do all applicable corrective 
actions.
    (3) For airplanes listed in paragraph (c) of this AD that are 
not listed in the ``Effectivity'' section of Boeing Special 
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23, 
2012: Do a general visual inspection to determine if a serviceable 
turbine exhaust plug assembly is installed. If a serviceable turbine 
exhaust plug assembly is not installed, before further flight, 
install a serviceable turbine exhaust plug assembly.

[[Page 11728]]

(h) Definition of Serviceable Assembly

    For purposes of this AD, an acceptable serviceable turbine 
exhaust plug assembly must meet the conditions specified in 
paragraph (h)(1) or (h)(2) of this AD.
    (1) A new assembly with part number 314W5520-22.
    (2) A serviceable assembly as defined in the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 777-78-
0051, Revision 3, dated August 23, 2012; except, for any assembly on 
which the actions specified in Part 2 or Part 3 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 777-78-0051, Revision 3, dated August 23, 2012, are done, 
and Boeing Special Attention Service Bulletin 777-78-0051, Revision 
3, dated August 23, 2012, specifies to contact Boeing for repair 
instructions, this AD requires repair before further flight using a 
method approved in accordance with the procedures specified in 
paragraph (k) of this AD.

(i) Exception to Service Information Specifications

    Where paragraph 1.E., ``Compliance,'' of Boeing Special 
Attention Service Bulletin 777-78-0051, Revision 3, dated August 23, 
2012, specifies a compliance time ``after the Revision 3 date of 
this service bulletin,'' this AD requires compliance within the 
applicable time after the effective date of this AD.

(j) Parts Installation Limitation

    As of the effective date of this AD, only a serviceable turbine 
exhaust plug assembly may be installed on any airplane.

(k) 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 (m) 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 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.

(l) Related Information

    (1) For more information about this AD, contact Kevin Nguyen, 
Aerospace Engineer, Propulsion Branch, ANM-140S, Seattle Aircraft 
Certification Office (ACO) FAA, 1601 Lind Avenue SW., Renton, 
Washington 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 February 24, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04568 Filed 2-28-14; 8:45 am]
BILLING CODE 4910-13-P