[Federal Register Volume 72, Number 101 (Friday, May 25, 2007)]
[Proposed Rules]
[Pages 29282-29284]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-10105]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28281; Directorate Identifier 2006-NM-238-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Boeing Model 767 airplanes. This proposed AD would require 
repetitive replacement of the internal electrical feed-through 
connectors of the main fuel tank boost pumps. This proposed AD results 
from a report of cracking in the epoxy potting compound on the internal 
feed-through connector of the fuel boost pump in the area of the 
soldered wire connector lugs. We are proposing this AD to prevent a 
hazardous electrical path from the dry side to the wet side of the fuel 
boost pump through a cracked feed-through connector, which could create 
an ignition source on the wet side of the fuel boost pump and lead to 
subsequent explosion of the fuel tank.

DATES: We must receive comments on this proposed AD by July 9, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
      DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Judy Coyle, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6497; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2007-
28281; Directorate Identifier 2006-NM-238-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT

[[Page 29283]]

street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    We have received a report that, after close examination of the 
internal electrical circuit of the fuel boost pump, supplier tests 
revealed cracking in the epoxy potting compound on the feed-through 
connector in the area of the soldered wire connector lugs of several 
pumps. This condition, if not corrected, could allow a hazardous 
electrical path from the dry side to the wet side of the fuel boost 
pump through a cracked feed-through connector, which could create an 
ignition source on the wet side of the fuel boost pump and lead to 
subsequent explosion of the fuel tank.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletins 767-28A0095 (for 
Model 767-200, -300, and -300F airplanes) and 767-28A0096 (for Model 
767-400ER airplanes), both dated September 15, 2005, which describe 
procedures for repetitively replacing the internal electrical feed-
through connectors of the main fuel tank boost pumps with new feed-
through connectors. This may be accomplished by replacing the fuel 
boost pump with a new fuel boost pump or with a modified and re-
identified fuel boost pump having a new feed-through connector 
installed.
    The alert service bulletins refer to Hamilton Sundstrand Alert 
Service Bulletin 5006003-28-A4, dated May 9, 2005, as an additional 
source of service information for replacing the feed-through connector 
of the fuel boost pump.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the Boeing 
service information described previously.

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 may consider additional rulemaking.

Costs of Compliance

    There are about 941 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 414 airplanes of 
U.S. registry, at an average labor rate of $80 per work hour.
    The proposed fuel boost pump replacement would take about 3 work 
hours per boost pump (4 boost pumps per airplane) or up to 12 work 
hours per airplane, per replacement cycle. The parts cost for 
replacement fuel boost pumps would be offset by returning the existing 
fuel boost pumps to the manufacturer for rework. Based on these 
figures, the estimated cost of the proposed AD for U.S. operators to 
replace the fuel boost pumps is up to $397,440, or up to $960 per 
airplane, per replacement cycle.
    If done, the proposed feed-through connector replacement would take 
about 3 work hours per connector (4 connectors per airplane) or up to 
12 work hours per airplane, per replacement cycle. Required parts would 
cost $691 per connector (up to $2,764 per airplane). Based on these 
figures, the estimated cost of the proposed AD for U.S. operators to 
replace the feed-through connectors is up to $1,541,736, or up to 
$3,724 per airplane, per replacement cycle.

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 have 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 that the 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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: FAA-2007-28281; Directorate Identifier 2006-NM-238-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 9, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 767-200, -300, -300F, 
and -400ER series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from a report of cracking in the epoxy 
potting compound on the internal feed-through connector of the fuel 
boost pump in the area of the soldered wire connector lugs. We are 
issuing this AD to prevent a hazardous electrical path from the dry 
side to the wet side of the fuel boost pump through a cracked feed-
through connector, which could create an ignition source on the wet 
side of the fuel boost pump and lead to subsequent explosion of the 
fuel tank.

[[Page 29284]]

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Compliance Times

    (f) At the later of the times specified in paragraphs (f)(1) and 
(f)(2) of this AD, do the actions specified in paragraph (g) of this 
AD, in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 767-28A0095 or 767-28A0096; both dated 
September 15, 2005; as applicable.
    (1) Within 96 months since the date of issuance of the original 
standard airworthiness certificate or the date of issuance of the 
original export certificate of airworthiness, or before the 
accumulation of 40,000 total flight hours, whichever comes first.
    (2) Within 24 months after the effective date of this AD.

Replacement of Fuel Boost Pump Feed-Through Connector

    (g) At the compliance time specified in paragraph (f) of this 
AD: Replace the feed-through connector of each fuel boost pump as 
described in paragraph (g)(1) or (g)(2) of this AD. Repeat this 
replacement thereafter at intervals not to exceed 40,000 flight 
hours or 96 months, whichever comes first.
    (1) Replace the fuel boost pump with a new fuel boost pump.
    (2) Replace the fuel boost pump with a modified and re-
identified fuel boost pump having a new feed-through connector 
installed.

    Note 1: Boeing Alert Service Bulletins 767-28A0095 and 767-
28A0096 refer to Hamilton Sundstrand Alert Service Bulletin 5006003-
28-A4, dated May 9, 2005, as a source of service information for 
replacing the feed-through connector and re-identifying the fuel 
boost pump.

Parts Installation

    (h) As of the effective date of this AD, no person may install a 
fuel boost pump on any airplane, unless that pump meets the 
requirements of paragraph (g) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

    Issued in Renton, Washington, on May 17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-10105 Filed 5-24-07; 8:45 am]
BILLING CODE 4910-13-P