FR Doc E6-1682

[Federal Register: February 8, 2006 (Volume 71, Number 26)]
[Proposed Rules]
[Page 6404-6408]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08fe06-25]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23803; Directorate Identifier 2005-NM-238-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-400, 747-400D, and
747-400F Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking.

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all Boeing Model 747-400, -400D, and -
400F series airplanes. The existing AD currently requires revising the
airplane flight manual (AFM) to require the flightcrew to maintain
certain minimum fuel levels in the center fuel tanks, and to prohibit
the use of the horizontal stabilizer fuel tank. This proposed AD would
require installing new integrated display software in the integrated
display units and electronic flight instrument system/engine indication
and crew alerting system interface units (EIUs) of the flight deck.
This proposed AD also would require revising the AFM to include
procedures to prevent dry operation of the center wing and horizontal
stabilizer fuel tanks; for maintaining minimum fuel levels; and for de-
fueling fuel tanks. For certain airplanes, the proposed AD also
requires removing G13 pin ground wires of a certain wire integration
unit of the EIUs at certain connector locations. This proposed AD
results from fuel system reviews conducted by the manufacturer. We are
proposing this AD to reduce the potential for ignition sources inside
fuel tanks, which, in combination with flammable fuel vapors, could
result in fuel tank explosions and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by March 27, 2006.

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 service information identified in this
proposed AD.

FOR FURTHER INFORMATION CONTACT: Sulmo Mariano, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6501; 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 ``Docket No.
FAA-2006-23803; Directorate Identifier 2005-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 the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or 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
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.

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''
(67 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this 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 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent

[[Page 6405]]

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 another 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.

Relevant Rulemaking

On December 23, 2002, we issued AD 2002-24-52, amendment 39-12993
(68 FR 14, January 2, 2003), for all Boeing Model 747-400, -400D, and -
400F series airplanes. That AD requires revising the airplane flight
manual (AFM) to require the flightcrew to maintain certain minimum fuel
levels in the center fuel tanks, and to prohibit the use of the
horizontal stabilizer fuel tank. That AD resulted from reports
indicating that two fuel pumps showed evidence of extreme localized
overheating of parts in the priming and vapor pump section of the fuel
pump. We issued that AD to require the flightcrew to maintain certain
minimum fuel levels in the center fuel tanks, and to prohibit the use
of the horizontal stabilizer fuel tank.

Other Relevant Rulemaking

We also issued the following ADs:

Other Relevant Rulemaking
----------------------------------------------------------------------------------------------------------------
AD-- Requires-- And-- And--
----------------------------------------------------------------------------------------------------------------
2001-12-21, amendment 39-12277 (66 FR Revising the AFM to For certain airplanes, For certain airplanes,
33170, June 21, 2001). include procedures to prohibits operation of requires installing
prevent dry operation the horizontal improved fuel pumps,
of the center wing stabilizer tank which terminates the
fuel tank override/ transfer pumps in AFM revision.
jettison pumps. flight.
2001-21-07, amendment 39-12478 (66 FR For certain airplanes, For all airplanes, Reworking of certain
54652, October 30, 2001). revising the AFM. performing repetitive components, which ends
inspections for wear the repetitive
or damage of the inlet inspection
check valves and inlet requirements.
adapters of the
override/jettison
pumps, and doing
corrective actions if
necessary.
2002-19-52, amendment 39-12900 (67 FR Removing currently Prohibits installation Permits the AFM
61253, September 30, 2002). required AFM of any uninspected revision and placard
revisions, inserting pumps. to be removed under
new AFM revisions, and certain conditions.
installing placards to
alert the flightcrew
to the operating
restrictions.
----------------------------------------------------------------------------------------------------------------

Actions Since Existing ADs Were Issued

The preambles to ADs 2002-24-52 and 2002-19-52 explain that we
consider the requirements ``interim action'' and were considering
further rulemaking. We now have determined that further rulemaking is
indeed necessary, and this proposed AD follows from that determination.
We have reviewed the following service bulletins:

Service Bulletins
------------------------------------------------------------------------
Boeing Alert Service Bulletin-- For Model--
------------------------------------------------------------------------
747-31A2350, Revision 1, dated March 747-400 and 747-400F series
17, 2005. airplanes.
747-31A2351, Revision 1, dated March 747-400, 747-400D, and 747-400F
17, 2005. series airplanes.
747-31A2352, Revision 1, dated March 747-400 and 747-400F series
17, 2005. airplanes.
------------------------------------------------------------------------

The service bulletins describe procedures for installing new
integrated display software in the integrated display units (IDUs) and
electronic flight instrument system (EFIS)/engine indication and crew
alerting system (EICAS) interface units (EIU) of the flight deck. The
new software provides new IDS EICAS fuel system messages. These
messages alert the flightcrew when to shut the fuel pumps off.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
Each service bulletin described previously refers to Rockwell
Collins Service Bulletins IDS-7000-31-49, IDS-7000-31-50, or IDS-7000-
31-51; all dated June 28, 2004; as applicable; as an additional source
of service information for installing the new software.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2002-24-52 to continue to require revising the AFM
to require the flightcrew to maintain certain minimum fuel levels in

[[Page 6406]]

the center fuel tanks, and to prohibit the use of the horizontal
stabilizer fuel tank. The proposed AD also would require:
Accomplishing the actions specified in the Boeing service
information described previously;
Revising the Limitations section of the AFM to include
procedures to prevent dry operation of the center wing and horizontal
stabilizer fuel tanks; for maintaining minimum fuel levels; and for de-
fueling fuel tanks; and
For certain airplanes: Removing G13 pin ground wires of
the wire integration unit on the E2-6 electronic shelf of the left,
center, and right electronics interface units at certain connector
locations.
After installing the new software and incorporating the new AFM
revisions, the AFM revision required by AD 2002-24-52 and certain AFM
revisions required by ADs 2001-12-21, 2001-21-07, and 2002-19-52 may be
removed.

Change to Existing AD

This proposed AD would retain all the requirements of AD 2002-24-
52. Since AD 2002-24-52 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:

Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2002-24-52 this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (g).
paragraph (b)............................. paragraph (h).
------------------------------------------------------------------------

Costs of Compliance

There are about 520 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.

Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per airplane registered Fleet cost
rate per hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM revision (required by AD 2002- 1 $65 None............... $65 101 $6,565.
24-52).
Installation of new IDS software 3 65 $100............... 295 101 $29,795.
(new proposed action).
Removal of G-13 pin ground wires 1 65 None............... 65 0 $65 if an affected
(new proposed action). airplane is
imported and placed
on the U.S.
Register in the
future.
AFM revision (new proposed 1 65 None............... 65 101 $6,565.
action).
--------------------------------------------------------------------------------------------------------------------------------------------------------

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
removing amendment 39-12993 (68 FR 14, January 2, 2003) and adding the
following new airworthiness directive (AD):

Boeing: Docket No. FAA-2006-23803; Directorate Identifier 2005-NM-
238-AD.

Comments Due Date

(a) The FAA must receive comments on this AD action by March 27,
2006.

Affected ADs

(b) This AD supersedes AD 2002-24-52. In addition, after
accomplishing the requirements of paragraphs (h) and (k) of this AD,
the airplane flight manual (AFM)

[[Page 6407]]

requirements specified in table 1 of this AD may be removed.

Table 1.--Affected ADs
------------------------------------------------------------------------
AFM requirements of-- Of--
------------------------------------------------------------------------
(1) Paragraph (a)...................... AD 2001-12-21, amendment 39-
12277.
(2) Paragraph (a)...................... AD 2001-21-07, amendment 39-
12478.
(3) Paragraph (c)...................... AD 2002-19-52, amendment 39-
12900.
(4) Paragraphs (f) and (g)............. This AD.
------------------------------------------------------------------------

Applicability

Table 2.--Applicability
------------------------------------------------------------------------
As identified in Boeing Service
Boeing model-- Bulletin--
------------------------------------------------------------------------
(1) 747-400, 747-400D, and 747-400F 747-31A2351, Revision 1, dated
series airplanes. March 17, 2005.
(2) 747-400 and 747-400F series 747-31A2350, Revision 1, dated
airplanes. March 17, 2005.
(3) 747-400 and 747-400F series 747-31A2352, Revision 1, dated
airplanes. March 17, 2005.
------------------------------------------------------------------------

Unsafe Condition

(d) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to reduce the potential for
ignition sources inside fuel tanks, which, in combination with
flammable fuel vapors, could result in fuel tank explosions and
consequent loss of the airplane.

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.

Restatement of Requirements of AD 2002-24-52

Airplane Flight Manual (AFM) Revision

(f) Within 4 days after receipt of emergency AD 2002-24-51,
instead of complying with the requirements of paragraph (d) of AD
2002-24-51, revise the Limitations section of the AFM to include the
following (this may be accomplished by inserting a copy of this AD
into the AFM):

CERTIFICATE LIMITATIONS

Fueling and use of the horizontal stabilizer tank (if installed)
is prohibited.
The center wing tank (CWT) must contain a minimum of 17,000
pounds (7,700 kilograms) prior to engine start, if the CWT override/
jettison pumps are to be selected ON during flight.
The CWT fuel quantity indication system must be operative to
dispatch with CWT mission fuel.
Both CWT override/jettison pump switches must be selected OFF at
or before CWT fuel quantity reaches 7,000 pounds (3,200 kilograms),
if CWT fuel quantity is less than 50,000 pounds (22,700 kilograms)
prior to engine start. The CWT override pumps may be selected ON
during stabilized cruise conditions. Both CWT override/jettison pump
switches must be selected OFF at or before the CWT fuel quantity
reaches 3,000 pounds (1,400 kilograms).

Note: With CWT override/jettison pumps selected OFF and CWT fuel
quantity greater than 6,000 pounds (2,800 kilograms), the FUEL OVRD
CTR L & R EICAS messages will be displayed. Do not accomplish the
associated non-normal procedure.

Both CWT override/jettison pump switches must be selected OFF at
or before CWT fuel quantity reaches 3,000 pounds (1,400 kilograms),
if CWT fuel quantity is greater than or equal to 50,000 pounds
(22,700 kilograms) prior to engine start.
Both CWT override/jettison pumps must be selected OFF when
either CWT override/jettison fuel pump low pressure light
illuminates.
Warning: Do not reset a tripped fuel pump circuit breaker.
Warning: Do not cycle CWT override/jettison pump switches from
ON to OFF to ON with any continuous low pressure indication present.

Note: The center wing tank may be emptied normally during an
emergency fuel jettison.

Note: In a low fuel situation, both CWT override/jettison pumps
may be selected ON and all CWT fuel may be used.

If a center wing tank pump fails with fuel in the center tank,
accomplish the FUEL OVRD CTR L, R non-normal procedure.
If the main tanks are not full, the zero fuel gross weight of
the airplane plus the weight of CWT tank fuel may exceed the maximum
zero fuel gross weight by up to 7,000 pounds (3,200 kilograms) for
takeoff, climb, cruise, descent, and landing, provided that the
effects of balance (CG) have been considered.
When defueling any fuel tanks, the Fuel Pump Low Pressure
indication lights must be monitored and the fuel pumps positioned to
OFF at the first indication of fuel pump low pressure. Defueling
with passengers on board is prohibited.
The limitations contained in this AD supersede any conflicting
basic airplane flight manual limitations.''
(g) If an operator has already complied with AD 2002-24-51, it
can comply with paragraph (f) of this AD by deleting the phrase ``if
a placard prohibiting its use is installed'' from the first
paragraph of the AFM revision required by paragraph (d) of AD 2002-
24-51.

New Actions Required by This AD

Installation of New Integrated Display System (IDS) Software

(h) Within 6 months after the effective date of this AD, install
new IDS software in the integrated display units and electronic
flight instrument system/engine indication and crew alerting system
interface units of the flight deck, in accordance with the
Accomplishment Instructions of the applicable service bulletin in
table 3 of this AD.

Table 3.--Revision 1 of Service Bulletins
------------------------------------------------------------------------
For model-- Boeing service bulletin--
------------------------------------------------------------------------
(1) 747-400, 747-400D, and 747-400F 747-31A2351, Revision 1, dated
series airplanes. March 17, 2005.
(2) 747-400 and 747-400F series 747-31A2350, Revision 1, dated
airplanes. March 17, 2005.

[[Page 6408]]

(3) 747-400 and 747-400F series 747-31A2352, Revision 1, dated
airplanes. March 17, 2005.
------------------------------------------------------------------------

Note 1: Each service bulletin identified in table 3 of this AD
refers to Rockwell Collins Service Bulletins IDS-7000-31-49, IDS-
7000-31-50, or IDS-7000-31-51; all dated June 28, 2004; as
applicable; as an additional source of service information for
installing the new IDS software.

(i) Installing new IDS software before the effective date of
this AD in accordance with the applicable service bulletin in table
4 of this AD, is acceptable for compliance with the requirements of
paragraph (h) of this AD.

Table 4.--Original Service Bulletins
------------------------------------------------------------------------
For model-- Boeing service bulletin--
------------------------------------------------------------------------
(1) 747-400, 747-400D, and 747-400F 747-31A2351, dated September 3,
series airplanes. 2004.
(2) 747-400 and 747-400F series 747-31A2350, dated September 3,
airplanes. 2004.
(3) 747-400 and 747-400F series 747-31A2352, dated September 3,
airplanes. 2004.
------------------------------------------------------------------------

Removal of Pin Ground Wires

(j) For airplanes on which FR-HiTEMP fuel pumps have been
incorporated in accordance with Boeing Service Bulletin 747-28-2258,
dated December 19, 2003; or Revision 1, dated August 11, 2005:
Before further flight after installing the new IDS software required
by paragraph (h) of this AD, remove the G13 pin ground wires of the
wire integration unit on the E2-6 electronic shelf of the left,
center, and right electronics interface units, that correspond to
the connector locations in table 5 of this AD, in accordance with a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA. Chapter 20-41-03 of the Boeing 747-400 Aircraft
Maintenance Manual is one approved method.

Table 5.--Connector Location
------------------------------------------------------------------------
Connector Location
------------------------------------------------------------------------
DM7353CA.................................. Left EIU.
DM7352CA.................................. Center EIU.
DM7351CA.................................. Right EIU.
------------------------------------------------------------------------

AFM Revision

(k) Concurrently with the requirements of paragraph (h) of this
AD, revise the Limitations section of the AFM to include the
following (this may be done by inserting a copy of this AD into the
AFM):

Certification Limitations

Center Wing Tank (CWT): The CWT fuel quantity indication system
must be operative to dispatch with CWT mission fuel.
The CWT must contain a minimum of 17,000 pounds (7,700
kilograms) prior to engine start, if the CWT override/jettison pumps
are to be selected ON during takeoff.
If the FUEL LOW CTR L or R message is displayed both CWT
override/jettison pumps must be selected OFF.
If the FUEL PRESS CTR L or R message is displayed, the
corresponding CWT override/jettison pump must be selected OFF.
Horizontal Stabilizer Tank (HST): The following additional
limitations must be followed if the HST is fueled and used:
The HST fuel quantity indication system must be operative to
dispatch with HST mission fuel.
If the FUEL PMP STB L or R message is displayed while on the
ground both HST pumps must be selected OFF.
If the FUEL LOW STAB L or R message is displayed in flight the
corresponding HST pump must be selected OFF.
If the FUEL PRESS STAB L or R is displayed the corresponding HST
pump must be selected OFF.
The remaining fuel in the HST must be considered unusable, and
the effects of that unusable fuel on balance (CG) must be
considered.
Warning: Do not reset a tripped fuel pump circuit breaker.
Defueling: Prior to defueling any fuel tanks, perform a lamp
test of the respective Fuel Pump Low Pressure indication lights.
When defueling, the Fuel Pump Low Pressure indication lights must be
monitored and the fuel pumps positioned to OFF at the first
indication of fuel pump low pressure. When defueling with passengers
on board, fuel pump switches must be selected OFF at or above
approximately 7,000 pounds (3,200 kilograms) for the CWT, 3,000
pounds (1,400 kilograms) for main tanks, and 2,100 pounds (1,000
kilograms) for the HST.

Alternative Methods of Compliance (AMOCs)

(l)(1) The Manager, Seattle ACO, 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 January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-1682 Filed 2-7-06; 8:45 am]

BILLING CODE 4910-13-P