
[Federal Register Volume 79, Number 216 (Friday, November 7, 2014)]
[Proposed Rules]
[Pages 66343-66345]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-26534]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0755; Directorate Identifier 2014-NM-080-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 all 
The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER 
series airplanes, Model 757 airplanes, Model 767 airplanes, and Model 
777 airplanes. This proposed AD results from fuel system reviews 
conducted by the manufacturer. This proposed AD would require an 
inspection to determine if certain spar-mounted motor-operated valve 
actuators for the spar-mounted fuel valves are installed, and 
replacement of any affected actuators. We are proposing this AD to 
prevent electrical energy from lightning, hot shorts, or fault current 
from entering the fuel tank through the actuator shaft, which could 
result in fuel tank explosions and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by December 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.

Examining the AD Docket

    You may examine the AD docket on the Internet http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0755; 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: Rebel Nichols, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6509; fax: 425-917-6590; email: rebel.nichols@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-2014-0755; 
Directorate Identifier 2014-NM-080-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

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this

[[Page 66344]]

rule included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 (66 FR 23086, May 7, 2001) requires 
certain type design (i.e., type certificate (TC) and supplemental type 
certificate (STC)) holders to substantiate that their fuel tank systems 
can prevent ignition sources in the fuel tanks. This requirement 
applies to type design holders for large turbine-powered transport 
airplanes and for subsequent modifications to those airplanes. It 
requires them to perform design reviews and to develop design changes 
and maintenance procedures if their designs do not meet the new fuel 
tank safety standards. As explained in the preamble to the rule, we 
intended to adopt airworthiness directives to mandate any changes found 
necessary to address unsafe conditions identified as a result of these 
reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this AD are 
necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.
    We are proposing this AD to prevent electrical energy from 
lightning, hot shorts, or fault current from entering the fuel tank 
through the actuator shaft, which could result in fuel tank explosions 
and consequent loss of the airplane.

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 an inspection to determine whether 
any spar-mounted motor-operated valve (MOV) actuators for the spar-
mounted fuel valves having part number (P/N) MA20A1001-1 (S343T003-39) 
are installed, and replacement of any affected actuator with a 
serviceable, FAA-approved MOV actuator other than one having P/N 
MA20A1001-1 (S343T003-39).

Costs of Compliance

    We estimate that this proposed AD affects 2,140 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                    Cost per       Cost on U.S.
              Action                        Labor cost            Parts cost        product         operators
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Inspection to determine part        1 work-hour x $85 per                  $0              $85         $181,900
 number.                             hour = $85.
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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
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             Action                      Labor cost              Parts cost              Cost per product
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Replace actuator................  1 work-hour x $85 per     $5,000 per actuator  $5,085 per actuator.
                                   hour = $85 per actuator.
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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:

[[Page 66345]]

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-2014-0755; Directorate Identifier 
2014-NM-080-AD.

(a) Comments Due Date

    We must receive comments by December 22, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company airplanes identified 
in paragraphs (c)(1) through (c)(4) of this AD, certificated in any 
category.
    (1) Model 737-600, -700, -700C, -800, -900, and -900ER series 
airplanes.
    (2) Model 757-200, -200PF, -200CB, and -300 series airplanes.
    (3) Model 767-200, -300, -300F, and -400ER series airplanes.
    (4) Model 777-200, -200LR, -300, -300ER, and -777F series 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel 
Selector/Shut-off Valve.

(e) Unsafe Condition

    This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent electrical energy 
from lightning, hot shorts, or fault current from entering the fuel 
tank through the actuator shaft, which could result in fuel tank 
explosions and consequent loss of the airplane.

(f) Compliance

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

(g) Inspection To Determine Part Number

    Within 60 months after the effective date of this AD: Do an 
inspection to determine whether any motor-operated shutoff valve 
(MOV) actuators having part number (P/N) MA20A1001-1 (S343T003-39) 
for the fuel tanks or fuel feed system are installed on the 
airplane. A review of airplane maintenance records is acceptable in 
lieu of this inspection if the part number of the actuator can be 
conclusively determined from that review.

(h) Replacement

    If, during the inspection required by paragraph (g) of this AD, 
any MOV actuator having (P/N) MA20A1001-1 (S343T003-39) for the fuel 
tanks is installed: Within 60 months after the effective date of 
this AD, replace the affected MOV actuator with a serviceable, FAA-
approved MOV actuator other than one having P/N MA20A1001-1 
(S343T003-39).

(i) Parts Installation Prohibition

    As of the effective date of this AD, no person may install an 
MOV actuator having part number MA20A1001-1 (S343T003-39) on any 
airplane.

(j) 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 (k) 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.

(k) Related Information

    For more information about this AD, contact Rebel Nichols, 
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle 
Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6509; fax: 425-917-6590; email: 
rebel.nichols@faa.gov.

     Issued in Renton, Washington, on October 30, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-26534 Filed 11-6-14; 8:45 am]
BILLING CODE 4910-13-P


