FR Doc E8-969

[Federal Register: January 24, 2008 (Volume 73, Number 16)]
[Rules and Regulations]
[Page 4066-4069]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24ja08-9]

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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;
Amendment 39-15344; AD 2008-02-14]
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: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing airplanes listed above. This AD requires 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 AD also provides an option to inspect panel
assemblies for part numbers. This AD results from a report indicating
that the integrated drive generator failed in flight due to a 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.

DATES: This AD becomes effective February 28, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of February 28,
2008.

ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Management Facility

between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.

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:

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Boeing Model
747-400, -400D, and -400F series airplanes; Boeing Model 757 airplanes;
and Boeing Model 767 airplanes. That NPRM was published in the Federal
Register on August 16, 2007 (72 FR 45986). That NPRM proposed to
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. That NPRM also provided an
option to inspect panel assemblies for part numbers.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.

Support for the NPRM

Boeing, the airplane manufacturer, concurs with the content of the
NPRM.

Request To Remove Reference to Revision 1 of the Service Bulletins

Japan Airlines requests that we remove the reference in the NPRM to
Boeing Alert Service Bulletins 747-33A2280 and 767-33A0087, both
Revision 1, both dated September 25, 2003 (we referred to those service
bulletins as appropriate sources of service information for doing the
actions specified in the NPRM). The commenter notes that it has
incorporated Boeing Alert Service Bulletins 747-33A2280 and 767-
33A0087, both dated December 19, 2001, for its Model 747-400 and Model
767-200/-300 fleets. The commenter notes that it strictly controls the
configuration `D' master module. However, the commenter states it did
not carry out some top assembly module part number changes according to
the instructions of Revision 1 of the service bulletins because in some
cases the original top assembly module part number was not indicated
anywhere, or was indicated unclearly.
The commenter believes that it is impossible to follow the part
number change indicated in Revision 1 of the service bulletins and
notes that because it tracks the base module, it can ignore the top
assembly module part number.
The commenter also states that Boeing agrees that Japan Airlines
does not need to perform Revision 1 of the service bulletins because
the changes to the bulletin caused by Revision 1 do not affect Japan
Airlines' fleet/units.
We disagree with removing the reference to Boeing Alert Service
Bulletins 747-33A2280 and 767-33A0087, both Revision 1. We acknowledge
that each operator may wish to use different parts and have its own
tracking methods. However, we cannot accommodate every operator's
differences in each AD. We have determined that the best way to handle
such circumstances is for operators to request an alternative method of
compliance (AMOC) in accordance with paragraph (p) of this AD, rather
than increasing the complexity of the AD by addressing each operator's
unique situation. We have not revised this AD in this regard.

Conclusion

We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD as proposed.

Costs of Compliance

There are about 2,511 airplanes of the affected designs in the
worldwide fleet. This AD affects about 934 airplanes of U.S. registry.
The inspection of switches takes 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 inspection for U.S. operators is $597,760, or
$640 per airplane.

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

[[Page 4067]]

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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 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, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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]

0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):

2008-02-14 Boeing: Amendment 39-15344. Docket No. FAA-2007-28973;
Directorate Identifier 2007-NM-118-AD.

Effective Date

(a) This AD becomes effective February 28, 2008.

Affected ADs

(b) None.

Applicability

Table 1.--Applicability
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As identified in Boeing Alert
Model-- Service Bulletin--
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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.
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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 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
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Boeing Component Service Bulletin-- Date-- Model-- Critical location--
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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 767- Electrical Systems
200, -300, and -300F Panel.
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.

[[Page 4068]]

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 767- Auxiliary Power Unit/
200, -300, and -300F Cargo Fire Control
series airplanes. Panel Assembly.
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 airplanes. Assembly.
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 767- Electronic Engine
200, -300, and -300F Control Panel.
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 airplanes. Module.
233U3202-24-02, Revision 1......... September 25, 2003......... 747-400, -400D, and - Electrical and Standby
400F series airplanes. Power/Auxiliary Power
Unit Start Module.
233U3203-36-01, Revision 1......... September 25, 2003......... 747-400, -400D, and - Bleed Air Control
400F series airplanes. Module.
233U3206-28-01, Revision 1......... September 25, 2003......... 747-400, -400D, and - Engine Ignition
400F series airplanes. Control/Fuel Jettison
Module.
233U3208-22-02, Revision 1......... September 25, 2003......... 747-400, -400D, and - Passenger Oxygen and
400F series airplanes. Yaw Damper Module.
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 airplanes. Control Lever Module
Assembly.
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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 paragraph (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.

[[Page 4069]]

(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.
(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 tailpipe before doing the procedures in paragraph 3.B.14.b.(3).
All fuel must be removed from the engine tailpipe 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 Bulletin 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 bulletin.

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.

Material Incorporated by Reference

(q) You must use the service bulletins listed in Table 3 of this
AD to perform the actions that are required by this AD, unless the
AD specifies otherwise. The Director of the Federal Register
approved the incorporation by reference of these documents in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207,
for a copy of this service information. You may review copies at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html
.

Table 3.--Material Incorporated by Reference
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Boeing Alert Service Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
747-33A2280.............................. 1........................... September 25, 2003.
757-33A0044.............................. 1........................... September 25, 2003.
757-33A0045.............................. 1........................... September 25, 2003.
767-33A0087.............................. 1........................... September 25, 2003.
767-33A0088, including Appendix A........ Original.................... December 19, 2001.
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Issued in Renton, Washington, on January 14, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-969 Filed 1-23-08; 8:45 am]

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