Airworthiness Directives; Boeing Model 767 Series Airplanes, 7678-7681 [05-2839]
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<![CDATA[
7678
Federal Register / Vol. 70, No. 30 / Tuesday, February 15, 2005 / Proposed Rules
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD. 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2005–20352;
Directorate Identifier 2004–NM–214–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this AD
action by April 1, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757–
200 and –300 series airplanes and Model
767–200, –300, –300F, and –400ER series
airplanes; certificated in any category;
equipped with a Pegasus flight management
computer (FMC) system.
Unsafe Condition
(d) This AD was prompted by reports of
‘‘old’’ or expired air traffic control (ATC)
clearance messages being displayed on the
control display unit (CDU) of the FMC
system during subsequent flights. We are
issuing this AD to prevent the airplane
entering unauthorized airspace or following
a flight path that does not provide minimum
separation requirements between aircraft,
and a consequent near miss or mid-air
collision.
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.
Replacing the Operational Program Software
(OPS) and Flight Information and Data
Output (FIDO) Software
(f) Within 18 months after the effective
date of this AD, replace the OPS and FIDO
software of the existing FMC with Pegasus
2003 OPS and FIDO software, in accordance
with the applicable service bulletin specified
in Table 1 of this AD.
TABLE 1.—APPLICABLE SERVICE BULLETIN
Boeing airplane model
Boeing alert service bulletin
757–200 series airplanes ..........................................................
757–300 series airplanes ..........................................................
767–200, –300, and –300F series airplanes .............................
767–400ER series airplanes .....................................................
757–34A0258 ...........................................................................
757–34A0259 ...........................................................................
767–34A0389, Revision 2 ........................................................
767–34A0390 ...........................................................................
Acceptable for Compliance
DEPARTMENT OF TRANSPORTATION
(g) Accomplishment of Boeing Alert
Service Bulletin 767–34A0389, dated
February 19, 2004; or Revision 1, dated
September 16, 2004, before the effective date
of this AD, is an acceptable method of
compliance with the requirements of this AD.
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20351; Directorate
Identifier 2003–NM–269–AD]
Alternative Methods of Compliance
(AMOCs)
RIN 2120–AA64
(h) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
Airworthiness Directives; Boeing
Model 767 Series Airplanes
Issued in Renton, Washington, on February
6, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–2840 Filed 2–14–05; 8:45 am]
BILLING CODE 4910–13–P
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Jkt 205001
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Boeing Model 767 series airplanes. This
proposed AD would require an
inspection of each main tank fuel boost
pump for the presence of a pump shaft
flame arrestor, and if the flame arrestor
is missing, replacement of that pump
with a pump having a pump shaft flame
arrestor. This proposed AD would also
require repetitive measurements of the
flame arrestor’s position in the pump,
and corrective actions if necessary. This
proposed AD is prompted by reports
that certain fuel boost pumps may not
have flame arrestors installed in the
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Dated (2004)
February 12.
February 12.
December 16.
February 19.
pump shaft. We have also received
reports that the pin that holds the flame
arrestor in place can break due to metal
fatigue. We are proposing this AD to
prevent the possible migration of a
flame from a main tank fuel boost pump
inlet to the vapor space of that fuel tank,
and consequent ignition of fuel vapors,
which could result in a fire or explosion
should the pump inlets become
uncovered.
We must receive comments on
this proposed AD by April 1, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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.
• By 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.
DATES:
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Federal Register / Vol. 70, No. 30 / Tuesday, February 15, 2005 / Proposed Rules
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20351; the directorate identifier for this
docket is 2003–NM–269–AD.
FOR FURTHER INFORMATION CONTACT:
Bernie Gonzalez, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Transport Airplane Directorate, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6498;
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 under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20351; Directorate Identifier
2003–NM–269–AD’’ in the subject line
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
submitted 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 https://
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
website, 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 can
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
You can examine the AD docket on
the Internet at https://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
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14:39 Feb 14, 2005
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(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
Discussion
We have received reports that certain
fuel boost pumps for the main fuel tanks
do not have pump shaft flame arrestors
installed. While the affected fuel boost
pumps were installed on certain Boeing
Model 767 series airplanes, the pumps
may have been transferred to other
airplanes during operator maintenance.
Therefore, all Boeing Model 767
airplanes may be affected.
We have also received reports that the
roll pin that holds the flame arrestor in
the proper position in the fuel boost
pump shaft can break due to metal
fatigue. If the pin breaks, the pin and the
flame arrestor can drop down the pump
shaft into the reprime/vapor removal
portion of the pump. The ingestion of
the metal pieces created by the broken
pin may produce a sparking condition
and consequent ignition of vapor if
present. The pump shaft flame arrestor
is part of the explosion-proof enclosure
of the fuel pump. This flame arrestor’s
function is to contain an internal pump
explosion and prevent any flame from
reaching the fuel tank via the pump
inlet. If the flame arrestor is missing or
loose, the pump is no longer explosion
proof. In this condition, if the pump
inlet is uncovered such that the pump
runs dry, the fuel tank has no protection
from flame egress due to an ignition
within the pump. Such conditions may
exist during ground defueling of the
airplane fuel tanks and during abnormal
operating conditions involving a low
quantity of fuel in the tank. During low
fuel operation one or more fuel pumps
may experience intermittent dry
operation for sufficient periods of time
to permit vapor ignition within the
pump. This condition, if not corrected,
could result in the migration of a flame
from a main tank fuel boost pump inlet
to the vapor space of that fuel tank, and
consequent ignition of fuel vapors,
which could result in a fire or
explosion.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletins 767–28A0077 (for
Model 767–200, –300, and –300F series
airplanes) and 767–28A0081 (for Model
767–400ER series airplanes), both
Revision 1, both dated July 8, 2004,
which describe procedures for
inspecting each main tank fuel boost
pump to determine if the pin and flame
arrestor are installed, repetitively
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7679
measuring the position of the flame
arrestor in the pump, and corrective
actions. The corrective actions include
installing serviceable boost pumps. The
Boeing alert service bulletins reference
Hamilton Sundstrand Service Bulletin
5006003–28–2, dated October 25, 2002,
as an additional source of service
information for doing the inspections
and corrective actions. The procedures
in the Hamilton Sundstrand service
bulletin include:
• Removing the pumping unit
assemblies from the main fuel tank
boost pumps.
• Measuring the distance from the
impeller end of the shaft to the flame
arrestor (finned plug) in the pumping
unit assemblies.
• Testing certain pumping unit
assemblies.
• Marking the identification plates of
each pumping unit assembly with the
symbol ‘‘28–2.’’
• Reinstalling the pumping unit
assemblies into the fuel boost pumps.
If the measurement is greater than the
limit specified in the Hamilton Standard
service bulletin, that service bulletin
specifies to return the affected pumping
unit assembly to a repair shop for
replacement of the pin and flame
arrestor.
Accomplishing the actions specified
in the service information is intended to
adequately address the unsafe
condition.
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. Therefore, we are
proposing this AD, which would require
a detailed inspection of each main tank
fuel boost pump to determine if a flame
arrestor is installed, repetitive
measurements of the position of the
flame arrestor in the pump, and
corrective actions if necessary. The
proposed AD would require you to use
the service information described
previously, except as discussed under
‘‘Difference Between the Proposed AD
and Service Information.’’
Difference Between the Proposed AD
and Service Information
Operators should note that, although
the Hamilton Sundstrand service
bulletin specifies to return main tank
fuel boost pumps with damaged,
broken, or out-of-position flame
arrestors to a repair shop, that action is
not required by this proposed AD.
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Federal Register / Vol. 70, No. 30 / Tuesday, February 15, 2005 / Proposed Rules
Clarification of Inspection Terminology
Boeing Alert Service Bulletins 767–
28A0077 and 767–28A0081, both
Revision 1, specify to do an inspection
of each main tank fuel boost pump for
the presence or integrity of the flame
arrestor as specified in Hamilton
Sundstrand Service Bulletin 5006003–
28–2, dated October 25, 2002. This
proposed AD requires a detailed
inspection of each main tank fuel boost
pump for the presence of the flame
arrestor. Note 2 has been included in
this proposed AD to define this type of
inspection.
The inspection of the integrity of the
flame arrestor is referred to as a ‘‘check’’
in the Hamilton Sundstrand service
bulletin. Instead of referring to this
action as a check, this proposed AD uses
the term ‘‘measurement.’’
Interim Action
We consider this proposed AD
interim action. If final action is later
identified, we may consider further
rulemaking then.
Costs of Compliance
This proposed AD would affect about
915 airplanes worldwide, and 400
airplanes of U.S. registry. The following
table provides the estimated costs for
U.S. operators to comply with this
proposed AD.
ESTIMATED COSTS
Action
Work hours
Average
labor rate
per
hour
Inspection of flame arrestor presence/position, per inspection cycle.
5
$65
Cost per
airplane
Number of
U.S.-registered airplanes
Fleet cost
$325, per inspection cycle ......
400
$130,000
Parts
None
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.
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. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
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,
Authority: 49 U.S.C. 106(g), 40113, 44701.
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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:
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2005–20351;
Directorate Identifier 2003–NM–269–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this AD
action by April 1, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model
767 series airplanes, certificated in any
category.
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Fmt 4702
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Unsafe Condition
(d) This proposed AD is prompted by
reports that certain fuel boost pumps may not
have flame arrestors installed in the pump
shaft. We have also received reports that the
pin that holds the flame arrestor in place can
break due to metal fatigue. We are issuing
this AD to prevent the possible migration of
a flame from a main tank fuel boost pump
inlet to the vapor space of that fuel tank, and
consequent ignition of fuel vapors, which
could result in a fire or explosion should the
pump inlets become uncovered.
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.
Service Bulletin References
(f) The term ‘‘alert service bulletin,’’ as
used in this AD, means the Accomplishment
Instructions of Boeing Alert Service Bulletins
767–28A0077 (for Model 767–200, –300, and
–300F series airplanes) and 767–28A0081
(for Model 767–400ER series airplanes), both
Revision 1, both dated July 8, 2004; as
applicable.
Note 1: The Boeing alert service bulletins
reference Hamilton Sundstrand Service
Bulletin 5006003–28–2, dated October 25,
2002, as an additional source of service
information for accomplishment of the
inspection and corrective actions. Although
the Hamilton Sundstrand service bulletin
specifies to return main tank fuel boost
pumps with damaged, broken, or out-ofposition flame arrestors to a repair shop, that
action is not required by this AD.
Inspection for Presence/Position of Flame
Arrestor in Main Tank Fuel Boost Pumps
(g) Prior to the accumulation of 15,000 total
flight hours, or within 365 days after the
effective date of this AD, whichever is later:
Do a detailed inspection of each main tank
fuel boost pump to determine if the pump
shaft flame arrestor is installed, a
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Federal Register / Vol. 70, No. 30 / Tuesday, February 15, 2005 / Proposed Rules
measurement of the flame arrestor’s position
in the pump, and any applicable corrective
actions, by accomplishing all of the actions
in the applicable alert service bulletin.
Repeat the measurement of the flame
arrestor’s position in the pump thereafter at
intervals not to exceed 6,000 flight hours or
24 months, whichever is first. Any applicable
corrective actions must be done before
further flight.
Note 2: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Note 3: There is no terminating action
available at this time for the repetitive
inspections required by paragraph (g) of this
AD.
Parts Installation
(h) As of the effective date of this AD, no
main tank fuel boost pump may be installed
on any airplane unless it has been inspected,
and any applicable corrective action
performed, in accordance with the
requirements of this AD.
Alternative Methods of Compliance
(AMOCs)
(i) 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.
Issued in Renton, Washington, on February
6, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–2839 Filed 2–14–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20350; Directorate
Identifier 2004–NM–202–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 777–200 and –300 Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 777–200 and –300
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14:39 Feb 14, 2005
Jkt 205001
series airplanes. This proposed AD
would require inspecting the valve
control and indication wire bundles of
the fuel system of the wing rear spar for
discrepancies, and corrective action if
necessary. This proposed AD is
prompted by reports of six incidents of
the wire bundles chafing against the rear
spar stiffeners outside the fuel tank. We
are proposing this AD to prevent this
chafing, which could result in wire
damage leading to a short circuit,
subsequent ignition of flammable
vapors, and possible uncontrollable fire
during fueling or flight.
DATES: We must receive comments on
this proposed AD by April 1, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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.
• By 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.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20350; the directorate identifier for this
docket is 2004–NM–202–AD.
FOR FURTHER INFORMATION CONTACT:
Georgios Roussos, Systems and
Equipment Branch, ANM–130S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6482; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new
procedures for maintaining AD dockets
electronically. As of May 17, 2004, new
AD actions are posted on DMS and
assigned a docket number. We track
each action and assign a corresponding
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7681
directorate identifier. The DMS AD
docket number is in the form ‘‘Docket
No. FAA–2004–99999.’’ The Transport
Airplane Directorate identifier is in the
form ‘‘Directorate Identifier 2004–NM–
999–AD.’’ Each DMS AD docket also
lists the directorate identifier (‘‘Old
Docket Number’’) as a cross-reference
for searching purposes.
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 under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–20350; Directorate Identifier
2004–NM–202–AD’’ in the subject line
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
submitted 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 https://
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
website, 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 can
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
We are reviewing the writing style we
currently use in regulatory documents.
We are interested in your comments on
whether the style of this document is
clear, and your suggestions to improve
the clarity of our communications that
affect you. You can get more
information about plain language at
https://www.faa.gov/language and https://
www.plainlanguage.gov.
Examining the Docket
You can examine the AD docket on
the Internet at https://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
street address stated in the ADDRESSES
section. Comments will be available in
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]]>Agencies
[Federal Register Volume 70, Number 30 (Tuesday, February 15, 2005)]
[Proposed Rules]
[Pages 7678-7681]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2839]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20351; Directorate Identifier 2003-NM-269-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Boeing Model 767 series airplanes. This proposed AD would
require an inspection of each main tank fuel boost pump for the
presence of a pump shaft flame arrestor, and if the flame arrestor is
missing, replacement of that pump with a pump having a pump shaft flame
arrestor. This proposed AD would also require repetitive measurements
of the flame arrestor's position in the pump, and corrective actions if
necessary. This proposed AD is prompted by reports that certain fuel
boost pumps may not have flame arrestors installed in the pump shaft.
We have also received reports that the pin that holds the flame
arrestor in place can break due to metal fatigue. We are proposing this
AD to prevent the possible migration of a flame from a main tank fuel
boost pump inlet to the vapor space of that fuel tank, and consequent
ignition of fuel vapors, which could result in a fire or explosion
should the pump inlets become uncovered.
DATES: We must receive comments on this proposed AD by April 1, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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.
By 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.
[[Page 7679]]
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-20351; the directorate identifier for this docket is
2003-NM-269-AD.
FOR FURTHER INFORMATION CONTACT: Bernie Gonzalez, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Transport Airplane Directorate,
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 917-6498; 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 under ADDRESSES. Include ``Docket No. FAA-2005-20351;
Directorate Identifier 2003-NM-269-AD'' in the subject line 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 submitted 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 https://
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 website, 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 can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at https://
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
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
We have received reports that certain fuel boost pumps for the main
fuel tanks do not have pump shaft flame arrestors installed. While the
affected fuel boost pumps were installed on certain Boeing Model 767
series airplanes, the pumps may have been transferred to other
airplanes during operator maintenance. Therefore, all Boeing Model 767
airplanes may be affected.
We have also received reports that the roll pin that holds the
flame arrestor in the proper position in the fuel boost pump shaft can
break due to metal fatigue. If the pin breaks, the pin and the flame
arrestor can drop down the pump shaft into the reprime/vapor removal
portion of the pump. The ingestion of the metal pieces created by the
broken pin may produce a sparking condition and consequent ignition of
vapor if present. The pump shaft flame arrestor is part of the
explosion-proof enclosure of the fuel pump. This flame arrestor's
function is to contain an internal pump explosion and prevent any flame
from reaching the fuel tank via the pump inlet. If the flame arrestor
is missing or loose, the pump is no longer explosion proof. In this
condition, if the pump inlet is uncovered such that the pump runs dry,
the fuel tank has no protection from flame egress due to an ignition
within the pump. Such conditions may exist during ground defueling of
the airplane fuel tanks and during abnormal operating conditions
involving a low quantity of fuel in the tank. During low fuel operation
one or more fuel pumps may experience intermittent dry operation for
sufficient periods of time to permit vapor ignition within the pump.
This condition, if not corrected, could result in the migration of a
flame from a main tank fuel boost pump inlet to the vapor space of that
fuel tank, and consequent ignition of fuel vapors, which could result
in a fire or explosion.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletins 767-28A0077 (for
Model 767-200, -300, and -300F series airplanes) and 767-28A0081 (for
Model 767-400ER series airplanes), both Revision 1, both dated July 8,
2004, which describe procedures for inspecting each main tank fuel
boost pump to determine if the pin and flame arrestor are installed,
repetitively measuring the position of the flame arrestor in the pump,
and corrective actions. The corrective actions include installing
serviceable boost pumps. The Boeing alert service bulletins reference
Hamilton Sundstrand Service Bulletin 5006003-28-2, dated October 25,
2002, as an additional source of service information for doing the
inspections and corrective actions. The procedures in the Hamilton
Sundstrand service bulletin include:
Removing the pumping unit assemblies from the main fuel
tank boost pumps.
Measuring the distance from the impeller end of the shaft
to the flame arrestor (finned plug) in the pumping unit assemblies.
Testing certain pumping unit assemblies.
Marking the identification plates of each pumping unit
assembly with the symbol ``28-2.''
Reinstalling the pumping unit assemblies into the fuel
boost pumps.
If the measurement is greater than the limit specified in the
Hamilton Standard service bulletin, that service bulletin specifies to
return the affected pumping unit assembly to a repair shop for
replacement of the pin and flame arrestor.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
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. Therefore, we are proposing this AD, which
would require a detailed inspection of each main tank fuel boost pump
to determine if a flame arrestor is installed, repetitive measurements
of the position of the flame arrestor in the pump, and corrective
actions if necessary. The proposed AD would require you to use the
service information described previously, except as discussed under
``Difference Between the Proposed AD and Service Information.''
Difference Between the Proposed AD and Service Information
Operators should note that, although the Hamilton Sundstrand
service bulletin specifies to return main tank fuel boost pumps with
damaged, broken, or out-of-position flame arrestors to a repair shop,
that action is not required by this proposed AD.
[[Page 7680]]
Clarification of Inspection Terminology
Boeing Alert Service Bulletins 767-28A0077 and 767-28A0081, both
Revision 1, specify to do an inspection of each main tank fuel boost
pump for the presence or integrity of the flame arrestor as specified
in Hamilton Sundstrand Service Bulletin 5006003-28-2, dated October 25,
2002. This proposed AD requires a detailed inspection of each main tank
fuel boost pump for the presence of the flame arrestor. Note 2 has been
included in this proposed AD to define this type of inspection.
The inspection of the integrity of the flame arrestor is referred
to as a ``check'' in the Hamilton Sundstrand service bulletin. Instead
of referring to this action as a check, this proposed AD uses the term
``measurement.''
Interim Action
We consider this proposed AD interim action. If final action is
later identified, we may consider further rulemaking then.
Costs of Compliance
This proposed AD would affect about 915 airplanes worldwide, and
400 airplanes of U.S. registry. The following table provides the
estimated costs for U.S. operators to comply with this proposed AD.
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of
Average U.S.-
Action Work hours labor rate Parts Cost per airplane registered Fleet cost
per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection of flame arrestor 5 $65 None $325, per inspection cycle.............. 400 $130,000
presence/position, per
inspection 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. 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 FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA-2005-20351; Directorate Identifier 2003-NM-
269-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by April 1, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model 767 series airplanes,
certificated in any category.
Unsafe Condition
(d) This proposed AD is prompted by reports that certain fuel
boost pumps may not have flame arrestors installed in the pump
shaft. We have also received reports that the pin that holds the
flame arrestor in place can break due to metal fatigue. We are
issuing this AD to prevent the possible migration of a flame from a
main tank fuel boost pump inlet to the vapor space of that fuel
tank, and consequent ignition of fuel vapors, which could result in
a fire or explosion should the pump inlets become uncovered.
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.
Service Bulletin References
(f) The term ``alert service bulletin,'' as used in this AD,
means the Accomplishment Instructions of Boeing Alert Service
Bulletins 767-28A0077 (for Model 767-200, -300, and -300F series
airplanes) and 767-28A0081 (for Model 767-400ER series airplanes),
both Revision 1, both dated July 8, 2004; as applicable.
Note 1: The Boeing alert service bulletins reference Hamilton
Sundstrand Service Bulletin 5006003-28-2, dated October 25, 2002, as
an additional source of service information for accomplishment of
the inspection and corrective actions. Although the Hamilton
Sundstrand service bulletin specifies to return main tank fuel boost
pumps with damaged, broken, or out-of-position flame arrestors to a
repair shop, that action is not required by this AD.
Inspection for Presence/Position of Flame Arrestor in Main Tank Fuel
Boost Pumps
(g) Prior to the accumulation of 15,000 total flight hours, or
within 365 days after the effective date of this AD, whichever is
later: Do a detailed inspection of each main tank fuel boost pump to
determine if the pump shaft flame arrestor is installed, a
[[Page 7681]]
measurement of the flame arrestor's position in the pump, and any
applicable corrective actions, by accomplishing all of the actions
in the applicable alert service bulletin. Repeat the measurement of
the flame arrestor's position in the pump thereafter at intervals
not to exceed 6,000 flight hours or 24 months, whichever is first.
Any applicable corrective actions must be done before further
flight.
Note 2: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Note 3: There is no terminating action available at this time
for the repetitive inspections required by paragraph (g) of this AD.
Parts Installation
(h) As of the effective date of this AD, no main tank fuel boost
pump may be installed on any airplane unless it has been inspected,
and any applicable corrective action performed, in accordance with
the requirements of this AD.
Alternative Methods of Compliance (AMOCs)
(i) 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.
Issued in Renton, Washington, on February 6, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-2839 Filed 2-14-05; 8:45 am]
BILLING CODE 4910-13-P
