FR Doc E7-16100

[Federal Register: August 16, 2007 (Volume 72, Number 158)]
[Proposed Rules]
[Page 45986-45991]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16au07-32]

[[Page 45986]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28973; Directorate Identifier 2007-NM-118-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-400, -400D, and -400F
Series Airplanes; Boeing Model 757 Airplanes; and 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 certain Boeing airplanes listed above. This proposed AD would
require an inspection of certain lighted pushbutton switches in the
flight compartment for configuration `D' master modules and part
numbers and corrective action if necessary. This proposed AD also
provides an option to inspect panel assemblies for part numbers. This
proposed AD results from a report indicating that the integrated drive
generator failed in flight due to a possible switch malfunction. We are
proposing this AD to ensure that certain lighted pushbutton switches in
the flight compartment do not malfunction and cause the flightcrew to
be unable to control critical airplane systems and continue safe
airplane operation.

DATES: We must receive comments on this proposed AD by October 1, 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: U.S. Department of Transportation, Docket
Operations, M-30, West Building, Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
By fax: (202) 493-2251.
Hand Delivery: Room W12-140 on the ground floor of the
West Building, 1200 New Jersey Avenue, SE., 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: Georgios Roussos, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6482; 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-2007-28973;
Directorate Identifier 2007-NM-118-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 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 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 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 Operations office between 9

a.m. and 5 p.m., Monday through Friday, except Federal holidays. The
Docket Operations office (telephone (800) 647-5527) is located on the
ground floor of the West Building at the 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 indicating that the integrated drive
generator (IDG) failed in flight on a Boeing Model 757 airplane. The
failure caused considerable oil staining of the fan case, and fire
damage to the inner skin of the fan cowl and to the engine wiring in
the immediate area. The flightcrew had used a lighted pushbutton switch
to disconnect the IDG before flight, but investigators concluded that
the switch failed and did not disconnect the IDG. The IDG disconnect
switch had a master module that was a configuration prior to
configuration `D.' Switches with master modules prior to configuration
`D' can malfunction due to ``cap pop-up'' (the switch releases from ON
to OFF without detection or warning) or ``jamming'' (the switch gets
stuck in one position and cannot be activated or deactivated).
These switches are used to control critical systems in the flight
compartment. These critical systems include:
Fuel management;
Engine ignition and start control;
Auxiliary power unit and cargo fire control;
Ice and rain protection;
Emergency lights/passenger oxygen;
Electrical system;
Battery/standby power;
Air conditioning-temperature control;
Autoflight-yaw damper;
Engine electronic control;
Pneumatic-bleed air control; and
Landing gear actuator control.
Cap pop-up or jamming, if not corrected, could cause the flightcrew
to be unable to control critical airplane systems and continue safe
airplane operation.
The lighted pushbutton switches used to control critical systems in
the flight compartment on Boeing Model 757 airplanes are identical to
those installed on Boeing Model 747-400, -400D, and -400F series
airplanes, and Model 767 airplanes. Therefore, all of these models
might be subject to the identified unsafe condition.

Relevant Service Information

We have reviewed the Boeing service bulletins in the following
table.

[[Page 45987]]

Boeing Alert Service Bulletins
----------------------------------------------------------------------------------------------------------------
Boeing alert service bulletin Revision Date Model
----------------------------------------------------------------------------------------------------------------
747-33A2280........................ 1................. September 25, 2003............. 747-400, -400D, and -
400F series
airplanes.
757-33A0044........................ 1................. September 25, 2003............. 757-200, -200CB, and -
200PF series
airplanes.
757-33A0045........................ 1................. September 25, 2003............. 757-300 series
airplanes.
767-33A0087........................ 1................. September 25, 2003............. 767-200, -300, and -
300F series
airplanes.
767-33A0088, including Appendix A.. Original.......... December 19, 2001.............. 767-400ER series
airplanes.
----------------------------------------------------------------------------------------------------------------

These service bulletins describe procedures for examining certain
lighted pushbutton switches in the flight compartment for configuration
`D' master modules and performing corrective action if a switch does
not have a configuration `D' master module. The corrective action if a
switch does not have a configuration `D' master module includes doing
one of the replacements specified below and other actions:
Replacing the switch without a configuration `D' master
module with a switch having a configuration `D' master module.
Replacing the switch master module with a new
configuration `D' master module.
Replacing the panel assembly with a new panel assembly.
Changing the part number of the panel assembly.
Doing operational tests of the critical systems if
components are replaced.

If a switch does have a configuration `D' master module but does not
have a correct part number of the panel assembly, the service bulletin
specifies a corrective action of changing the part number of the panel
assembly.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
The Boeing service bulletins refer to Korry Service Bulletin 433-
33-05, dated July 23, 2001, as an additional source of service
information for finding configuration `D' switches, for replacing the
switch master module with a configuration `D' master module, and for
doing various operational tests after the replacement.
Korry Service Bulletin 433-33-06, dated November 7, 2001, is an
appropriate source of service information for finding the one-to-one
switch correlation between the existing switches and the new part
number switches.
The Boeing service bulletins refer to the Boeing component service
bulletins that are described below. The component service bulletins
specify procedures for replacing the switch or switch master module at
applicable critical locations in the flight compartment and for doing
one-time operational tests after the replacement.

Boeing Component Service Bulletins
----------------------------------------------------------------------------------------------------------------
Component service bulletin-- Date-- Model-- Critical location--
----------------------------------------------------------------------------------------------------------------
233N3203-21-01, Revision 1........ September 25, 2003............ 757 airplanes........ Equipment Cooling
Panel.
233N3204-30-02, Revision 1........ September 25, 2003............ 757 airplanes........ Anti-ice Panel.
233N3206-28-02, Revision 1........ September 25, 2003............ 757-200, -200CB, and - Fuel Control Panel.
200PF series
airplanes.
233N3209-24-03, Revision 1........ September 25, 2003............ 757 airplanes, and Electrical Systems
767-200, -300, and - Panel.
300F series
airplanes.
233N3211-24-02, Revision 1........ September 25, 2003............ 757 airplanes and 767 Battery/Standby Power
airplanes. Panel.
233N3215-36-01, Revision 1........ September 25, 2003............ 757 airplanes........ Bleed Air Panel
Assembly.
233N3216-22-01, Revision 1........ September 25, 2003............ 757 airplanes and 767 Yaw Damper Panel
airplanes. Assembly.
233N3219-33-01, including Appendix December 19, 2001............. 757-200, -200CB, and - Emergency Lights/
A. 200PF series Passenger Oxygen
airplanes. Panel.
233N3223-31-03, Revision 1........ September 25, 2003............ 757 airplanes........ Engine Start/Ram Air
Turbine Panel
Assembly.
233N3224-73-01, Revision 1........ September 25, 2003............ 757-200, -200CB, and - Electronic Engine
200PF series Control Power Panel
airplanes. Assembly.
233N6203-26-10, Revision 1........ September 25, 2003............ 757 airplanes, and Auxiliary Power Unit/
767-200, -300, and - Cargo Fire Control
300F series Panel Assembly.
airplanes.
233T3210-33-01, Revision 1........ September 25, 2003............ 757 airplanes and 767 Emergency Lights
airplanes. Panel.
233T3215-24-01, including Appendix December 19, 2001............. 767-400ER series Electrical Control
A. airplanes. Module Assembly.
233T3235-28-05, Revision 1........ September 25, 2003............ 767-200, -300, and - Fuel Management Panel
300F series Assembly.
airplanes.
233T3236-21-05, Revision 1........ September 25, 2003............ 767 airplanes........ Temperature Control
Panel.
233T3237-36-04, Revision 1........ September 25, 2003............ 767 airplanes........ Bleed Air Control
Panel.
233T3241-30-03, Revision 1........ September 25, 2003............ 757-200, -200CB, and - Wing and Engine Anti-
200PF series ice Control Panel.
airplanes, and 767-
200, -300, and -300F
series airplanes.
233T3242-73-02, Revision 1........ September 25, 2003............ 757 airplanes, and Electronic Engine
767-200, -300, and - Control Panel.
300F series
airplanes.
233T3244-74-03, Revision 1........ September 25, 2003............ 767 airplanes........ Engine Ignition and
Start Control Panel.
233T6211-26-01, including Appendix December 19, 2001............. 767-400ER series Auxiliary Power Unit
A. airplanes. and Cargo Fire
Control Module
Assembly.
233U3201-30-04, Revision 1........ September 25, 2003............ 747-400, -400D, and - Rain Removal/Anti-ice
400F series Module.
airplanes.

[[Page 45988]]

233U3202-24-02, Revision 1........ September 25, 2003............ 747-400, -400D, and - Electrical and
400F series Standby Power/
airplanes. Auxiliary Power Unit
Start Module.
233U3203-36-01, Revision 1........ September 25, 2003............ 747-400, -400D, and - Bleed Air Control
400F series Module.
airplanes.
233U3206-28-01, Revision 1........ September 25, 2003............ 747-400, -400D, and - Engine Ignition
400F series Control/Fuel
airplanes. Jettison Module.
233U3208-22-02, Revision 1........ September 25, 2003............ 747-400, -400D, and - Passenger Oxygen and
400F series Yaw Damper Module.
airplanes.
233U3214-26-06, Revision 1........ September 25, 2003............ 747-400, -400D, and - Fire Control Module.
400F series
airplanes.
257U0002-32-04, including Appendix December 19, 2001............. 747-400, -400D, and - Landing Gear Actuator
A. 400F series Control Lever Module
airplanes. Assembly.
----------------------------------------------------------------------------------------------------------------

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 accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the Proposed AD and the Service Bulletins.''

Differences Between the Proposed AD and the Service Bulletins

Although the Boeing service bulletins recommend a compliance time
for accomplishing the inspection at the earliest opportunity when labor
and facilities are available, subsequent to issuing the service
bulletins, Boeing has recommended the actions be done within 60 months.
The FAA concurs. In developing an appropriate compliance time for this
proposed AD, we considered the degree of urgency associated with the
subject unsafe condition, the average utilization of the affected
fleet, and the time necessary to perform the inspection (8 work hours).
In light of all of these factors, we find that a 60-month compliance
time represents an appropriate interval of time for affected airplanes
to continue to operate without compromising safety.
Where the Boeing service bulletins specify to ``examine'' certain
parts, this proposed AD refers to a ``general visual inspection.'' We
have included the definition for a general visual inspection in a note
in the proposed AD.
The Boeing service bulletins specify inspecting the switch master
module to determine if the master module is configuration `D' and
replacing the switch with a switch having a configuration `D' master
module if necessary. However, for the operators' convenience and to
reduce workload, this proposed AD would include inspections for certain
part numbers (an inspection of panel assemblies for part numbers and an
inspection of the switches to determine if the switches have a new part
number) that would result in no further action or fewer actions being
required.
In contrast to the service bulletins, this proposed AD would allow
an inspection of panel assemblies for part numbers. If the panel
assemblies have certain part numbers, no further action would be
required. If the panel assemblies have certain other part numbers, then
this proposed AD would require inspecting to determine whether a
configuration `D' master module is installed or whether the switch has
a new part number. If a configuration `D' master module is installed or
the switch has a new part number, then this proposed AD would require
changing the part number of the panel assembly. If no new switch part
number is found and the master module is not configuration `D,' the
corrective action includes replacing the switch with a new part number
switch, replacing the switch with a switch having a configuration `D'
master module, or replacing the switch master module with a new
configuration `D' master module. The new switch must have one of the
following part numbers (P/Ns): Boeing P/N S231T290-4201 through -4325
inclusive or Korry P/N 4336731004-4201 through -4325 inclusive. One-to-
one correlation between the existing part number switches and the new
part number switches is detailed in Korry Service Bulletin 433-33-06,
dated November 7, 2001. We have coordinated this inspection and
replacement with Boeing.
The Boeing service bulletins also specify doing a replacement of
certain panel assemblies with new panel assemblies that have switches
with configuration `D' master modules. However, this proposed AD would
require only doing a general visual inspection of the applicable
switches of the panel assemblies to identify configuration `D' master
modules and the P/N of the switch; the inspection is specified as an
option in the Boeing service bulletins. We have determined that since
only a few switches on a given panel might need to be replaced, doing
the inspection of the applicable switches or panel assemblies is
sufficient and cost-effective.
The Boeing service bulletins do not refer to any service
information for the removal and/or installation of certain panels. This
proposed AD would require operators to remove or install those parts
according to a method approved by the FAA, or in accordance with the
actions specified in paragraph (l) of this proposed AD. We have
coordinated this difference with Boeing.
Boeing issued Information Notice 747-33A2280 IN 01, dated July 1,
2004, to clarify instructions specified in paragraph 3.B.14.b.(3) of
the Accomplishment Instructions of Boeing Alert Service Bulletin 747-
33A2280, Revision 1, dated September 25, 2003. We have included this
information in paragraph (n) of this proposed AD.

Costs of Compliance

There are about 2,511 airplanes of the affected designs in the
worldwide fleet. This proposed AD would affect about 934 airplanes of
U.S. registry.
The proposed inspection of switches would take about 8 work hours
per airplane, at an average labor rate of $80 per work hour. Based on
these figures, the estimated cost of the proposed inspection for U.S.
operators is $597,760, or $640 per airplane.

Authority for This Rulemaking

The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. Subtitle I, Section 106
describes the authority of the FAA Administrator. Subtitle VII,
Aviation Programs,

[[Page 45989]]

describes in more detail the scope of the agency's authority.
This rulemaking is promulgated 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-2007-28973; Directorate Identifier 2007-NM-
118-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by October 1, 2007.

Affected ADs

(b) None.

Applicability

Table 1.--Applicability
------------------------------------------------------------------------
As identified in Boeing alert
Model-- service bulletin--
------------------------------------------------------------------------
747-400, -400D, and -400F series 747-33A2280, Revision 1, dated
airplanes. September 25, 2003.
757-200, -200CB, and -200PF series 757-33A0044, Revision 1, dated
airplanes. September 25, 2003.
757-300 series airplanes............... 757-33A0045, Revision 1, dated
September 25, 2003.
767-200, -300, and -300F series 767-33A0087, Revision 1, dated
airplanes. September 25, 2003.
767-400ER series airplanes............. 767-33A0088, including Appendix
A, dated December 19, 2001.
------------------------------------------------------------------------

Unsafe Condition

(d) This AD results from a report indicating that the integrated
drive generator (IDG) failed in flight due to possible switch
malfunction. We are issuing this AD to ensure that certain lighted
pushbutton switches in the flight compartment do not malfunction and
cause the flightcrew to be unable to control critical airplane
systems and continue safe airplane operation.

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 ``the service bulletin,'' as used in this AD, means
the Accomplishment Instructions of the service bulletins listed in
Table 1 of this AD, as applicable.

Note 1: The Boeing alert service bulletins refer to Korry
Service Bulletin 433-33-05, dated July 23, 2001, as an additional
source of service information for finding configuration `D'
switches, for replacing the switch master module with a
configuration `D' master module, and for doing various operational
tests after the replacement.

Component Service Bulletin References

(g) The Boeing service bulletins listed in Table 1 of this AD
refer to the Boeing component service bulletins specified in Table 2
of this AD as additional sources of service information for
replacing the switch or switch master module at critical locations,
for doing operational tests after the replacement, and for
identifying new panel part numbers.

Table 2.--Boeing Component Service Bulletins: Secondary Sources of Service Information
----------------------------------------------------------------------------------------------------------------
Boeing component service bulletin--
Date-- Model-- Critical location--
----------------------------------------------------------------------------------------------------------------
233N3203-21-01, Revision 1........ September 25, 2003............ 757 airplanes........ Equipment Cooling
Panel.
233N3204-30-02, Revision 1........ September 25, 2003............ 757 airplanes........ Anti-ice Panel.
233N3206-28-02, Revision 1........ September 25, 2003............ 757-200, -200CB, and - Fuel Control Panel.
200PF series
airplanes.
233N3209-24-03, Revision 1........ September 25, 2003............ 757 airplanes, and Electrical Systems
767-200, -300, and - Panel.
300F series
airplanes.
233N3211-24-02, Revision 1........ September 25, 2003............ 757 airplanes and 767 Battery/Standby Power
airplanes. Panel.
233N3215-36-01, Revision 1........ September 25, 2003............ 757 airplanes........ Bleed Air Panel
Assembly.
233N3216-22-01, Revision 1........ September 25, 2003............ 757 airplanes and 767 Yaw Damper Panel
airplanes. Assembly.
233N3219-33-01, including Appendix December 19, 2001............. 757-200, -200CB, and - Emergency Lights/
A. 200PF series Passenger Oxygen
airplanes. Panel.
233N3223-31-03, Revision 1........ September 25, 2003............ 757 airplanes........ Engine Start/Ram Air
Turbine Panel
Assembly.

[[Page 45990]]

233N3224-73-01, Revision 1........ September 25, 2003............ 757-200, -200CB, and - Electronic Engine
200PF series Control Power Panel
airplanes. Assembly.
233N6203-26-10, Revision 1........ September 25, 2003............ 757 airplanes, and Auxiliary Power Unit/
767-200, -300, and - Cargo Fire Control
300F series Panel Assembly.
airplanes.
233T3210-33-01, Revision 1........ September 25, 2003............ 757 airplanes and 767 Emergency Lights
airplanes. Panel.
233T3215-24-01, including Appendix December 19, 2001............. 767-400ER series Electrical Control
A. airplanes. Module Assembly.
233T3235-28-05, Revision 1........ September 25, 2003............ 767-200, -300, and - Fuel Management Panel
300F series Assembly.
airplanes.
233T3236-21-05, Revision 1........ September 25, 2003............ 767 airplanes........ Temperature Control
Panel.
233T3237-36-04, Revision 1........ September 25, 2003............ 767 airplanes........ Bleed Air Control
Panel.
233T3241-30-03, Revision 1........ September 25, 2003............ 757-200, -200CB, and - Wing and Engine Anti-
200PF series ice Control Panel.
airplanes, and 767-
200, -300, and -300F
series airplanes.
233T3242-73-02, Revision 1........ September 25, 2003............ 757 airplanes, and Electronic Engine
767-200, -300, and - Control Panel.
300F series
airplanes.
233T3244-74-03, Revision 1........ September 25, 2003............ 767 airplanes........ Engine Ignition and
Start Control Panel.
233T6211-26-01, including Appendix December 19, 2001............. 767-400ER series Auxiliary Power Unit
A. airplanes. and Cargo Fire
Control Module
Assembly.
233U3201-30-04, Revision 1........ September 25, 2003............ 747-400, -400D, and - Rain Removal/ Anti-
400F series ice Module.
airplanes.
233U3202-24-02, Revision 1........ September 25, 2003............ 747-400, -400D, and - Electrical and
400F series Standby Power/
airplanes. Auxiliary Power Unit
Start Module.
233U3203-36-01, Revision 1........ September 25, 2003............ 747-400, -400D, and - Bleed Air Control
400F series Module.
airplanes.
233U3206-28-01, Revision 1........ September 25, 2003............ 747-400, -400D, and - Engine Ignition
400F series Control/Fuel
airplanes. Jettison Module.
233U3208-22-02, Revision 1........ September 25, 2003............ 747-400, -400D, and - Passenger Oxygen and
400F series Yaw Damper Module.
airplanes.
233U3214-26-06, Revision 1........ September 25, 2003............ 747-400, -400D, and - Fire Control Module.
400F series
airplanes.
257U0002-32-04, including Appendix December 19, 2001............. 747-400, -400D, and - Landing Gear Actuator
A. 400F series Control Lever Module
airplanes. Assembly.
----------------------------------------------------------------------------------------------------------------

Inspection

(h) Within 60 months after the effective date of this AD: Do a
general visual inspection of the switches specified in paragraphs
(h)(1), (h)(2), (h)(3), (h)(4), and (h)(5) of this AD, as
applicable, to identify configuration `D' master modules and the
part number (P/N) of the switch, in accordance with the applicable
service bulletin, except as provided by paragraph (i) of this AD.

Note 2: For the purposes of this AD, a general visual inspection
is ``A visual examination of a interior or exterior area,
installation or assembly to detect obvious damage, failure or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normal available lighting
conditions such as daylight, hangar lighting, flashlight or drop-
light and may require removal or opening of access panels or doors.
Stands, ladders or platforms may be required to gain proximity to
the area being checked.''

(1) For Model 757-200, -200CB, and -200PF series airplanes:
Switches identified in step 1 and step 3 of Figure 1 of Boeing Alert
Service Bulletin 757-33A0044, Revision 1, dated September 25, 2003.
(2) For Model 757-300 series airplanes: Switches identified in
step 1 of Figure 1 of Boeing Alert Service Bulletin 757-33A0045,
Revision 1, dated September 25, 2003.
(3) For Model 767-200, -300, and -300F series airplanes:
Switches identified in step 1 of Figure 1 of Boeing Alert Service
Bulletin 767-33A0087, Revision 1, dated September 25, 2003.
(4) For Model 767-400ER series airplanes: Switches identified in
step 1 of Figure 1 of Boeing Alert Service Bulletin 767-33A0088,
dated December 19, 2001.
(5) For all airplanes: Switches identified for the panel
assemblies specified in the applicable service bulletin.

Optional Inspection

(i) Instead of doing the inspection required by paragraph (h) of
this AD, operators may inspect the part number of the panel
assemblies specified in paragraphs (i)(1) and (i)(2) of this AD, as
applicable, at the time specified in paragraph (h) of this AD. If
the part number is identified as a new part number in paragraph 2.E.
Existing Parts Accountability or Appendix B of the applicable
service bulletin, no further action is required. If the part number
is not identified as a new part number, the inspection required by
paragraph (h) of this AD must be done at the specified time.
(1) For switches identified in paragraphs (h)(1), (h)(2),
(h)(3), and (h)(4) of this AD: P3-1 and P10 panel assemblies, as
applicable.
(2) For switches identified in paragraphs (h)(5) of this AD: The
panel assemblies identified in the applicable service bulletin.

Corrective Action

(j) If during any inspection required by paragraph (h) of this
AD, any switch is found that does not have a configuration `D'
switch master module and no switch part number specified in
paragraph (j)(1)(i) or (j)(1)(ii) of this AD is found: Before
further flight, do the actions specified in either paragraph (j)(1)
or (j)(2) of this AD and do the part number revision, as applicable,
specified in paragraph (j)(3) of this AD.
(1) Replace the switch with a switch specified in paragraph
(j)(1)(i), (j)(1)(ii), or (j)(1)(iii) of this AD, in accordance with
the applicable service bulletin, except as provided by paragraph (k)
of this AD.
(i) Switches having Boeing P/N S231T290-4201 through -4325
inclusive.
(ii) Switches having Korry P/N 4336731004-4201 through -4325
inclusive.

Note 3: One-to-one switch correlation between the existing
switches and the new part number switches can be found in Korry
Service Bulletin 433-33-06, dated November 7, 2001.

(iii) Switches that have a configuration `D' master module.
(2) Replace the switch master module with a new configuration
`D' master module in accordance with the applicable service
bulletin.

[[Page 45991]]

(3) If all switches on a panel assembly have a configuration `D'
master module or have a switch part number specified in paragraph
(j)(1)(i) or (j)(1)(ii) of this AD: Revise the part number of the
panel assembly; in accordance with the applicable service bulletin.
(k) If during any inspection required by paragraph (h) of this
AD, a configuration 'D' switch master module is found or the switch
part number is specified in paragraph (j)(1)(i) or (j)(1)(ii) of
this AD on all switches for a panel assembly: Before further flight,
revise the part number of the panel assembly, in accordance with the
applicable service bulletin.

Contact the FAA/Removal and Installation Procedures

(l) If the applicable service bulletin specifies removal or
installation of certain parts and does not specify removal or
installation instructions: Before further flight, remove or install
those parts according to a method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA, or by doing the actions
specified in paragraph (l)(1) of this AD for removal or paragraph
(l)(2) of this AD for installation, as applicable.
(1) Remove the module/panel assembly by doing the actions
specified in paragraphs (l)(1)(i), (l)(1)(ii), and (l)(1)(iii) of
this AD.
(i) Hold the module/panel assembly in position and loosen the
quick-release screws.
(ii) Carefully lower the module/panel assembly from the overhead
panel.
(iii) Remove the electrical connectors attached to the rear of
the module/panel assembly.
(2) Install the module/panel assembly by doing the actions
specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD.
(i) Make sure that the module/panel assembly is correctly
aligned, and connect the electrical connectors to the rear of the
unit.
(ii) Carefully lift the module/panel assembly into position and
install it with the quick-release screws.

Operational Tests

(m) If any panel assemblies, switches, or master modules are
replaced during any action required by this AD: Before further
flight, do all applicable operational tests in accordance with the
applicable service bulletin, except as provided by paragraph (n) of
this AD.
(n) Where paragraph 3.B.14.b.(3) of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-33A2280, Revision
1, dated September 25, 2003, specifies procedures to do a test of
the engine ignition control/fuel jettison module assembly, this AD
requires that operators dry-motor the engine to remove the fuel from
the tail pipe before doing the procedures in paragraph 3.B.14.b.(3).
All fuel must be removed from the engine tail pipe before performing
the test, because during the test the engine igniter will be
energized.

Actions Accomplished According to Previous Issue of Service Bulletins

(o) Actions accomplished before the effective date of this AD in
accordance with Boeing Alert Service Bulletins 747-33A2280, 757-
33A0044, 757-33A0045, or 767-33A0087, all dated December 19, 2001,
are considered acceptable for compliance with the corresponding
action specified in this AD, provided that the actions specified in
this AD are done on the switches for the additional panel assemblies
specified in Revision 1 of the service bulletins.

Alternative Methods of Compliance (AMOCs)

(p)(1) The Manager, Seattle ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.

Issued in Renton, Washington, on August 2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-16100 Filed 8-15-07; 8:45 am]

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