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[Federal Register: September 4, 2003 (Volume 68, Number 171)]
[Proposed Rules]
[Page 52539-52542]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr04se03-17]

=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-238-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-200 Series Airplanes
Modified by Supplemental Type Certificate ST00516AT

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Boeing Model 737-200 series
airplanes modified by Supplemental Type Certificate ST00516AT (STC).
This proposal would require removal of the in-flight entertainment
(IFE) system installed per that STC. This action is necessary to
eliminate the possibility that the airplane crew could be unable to
remove power from the IFE system during a non-normal or emergency
situation, which could result in the airplane crew's inability to
control smoke or fumes in the airplane flight deck or cabin. This
action is intended to address the identified unsafe condition.

DATES: Comments must be received by October 20, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-238-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-238-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Kosola and Associates, Inc., 5601 Newton Road, P.O. Box
3529, Albany, Georgia 31706. This information may be examined at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Atlanta Aircraft Certification Office, One
Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia.

FOR FURTHER INFORMATION CONTACT: Myles Jalalian, Aerospace Engineer,
Systems and Flight Test Branch, ACE-116A, FAA, Atlanta Aircraft
Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite
450, Atlanta, Georgia 30349; telephone (770) 703-6073; fax (770) 703-
6097.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
Submit comments using the following format:
◙ Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
◙ For each issue, state what specific change to the proposed
AD is being requested.
◙ Include justification (e.g., reasons or data) for each
request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following

[[Page 52540]]

statement is made: ``Comments to Docket Number 2002-NM-238-AD.'' The
postcard will be date stamped and returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2002-NM-238-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.

Discussion

The Federal Aviation Administration (FAA) recently completed a
review of in-flight entertainment (IFE) systems certified by
supplemental type certificate (STC) and installed on transport category
airplanes. The review focused on the interface between the IFE system
and airplane electrical system, with the objective of determining if
any unsafe conditions exist with regard to the interface. STCs issued
between 1992 and 2000 were considered for the review.
The type of IFE systems considered for review were those that
contain video monitors (cathode ray tubes or liquid crystal displays;
either hanging above the aisle or mounted on individual seat backs or
seat trays), or complex circuitry (i.e., power supplies, electronic
distribution boxes, extensive wire routing, relatively high power
consumption, multiple layers of circuit protection, etc.). In addition,
in-seat power supply systems that provide power to more than 20 percent
of the total passenger seats were also considered for the review. The
types of IFE systems not considered for review include systems that
provide only audio signals to each passenger seat, ordinary in-flight
telephone systems (e.g., one telephone handset per group of seats or
bulkhead-mounted telephones), systems that only have a video monitor on
the forward bulkhead(s) (or a projection system) to provide passengers
with basic airplane and flight information, and in-seat power supply
systems that provide power to less than 20 percent of the total
passenger seats.
Items considered during the review include the following:
◙ Can the electrical bus(es) supplying power to the IFE
system be de-energized when necessary without removing power from
systems that may be required for continued safe flight and landing?
◙ Can IFE system power be removed when required without
pulling IFE system circuit breakers (i.e., is there a switch (dedicated
to the IFE system or a combination of loads) located in the flight deck
or cabin that can be used to remove IFE power?)?
◙ If the IFE system requires changes to flightcrew
procedures, has the airplane flight manual (AFM) been properly amended?
◙ If the IFE system requires changes to cabin crew
procedures, have they been properly amended?
◙ Does the IFE system require periodic or special
maintenance?
In all, we reviewed approximately 180 IFE systems approved by STC.
The review results indicate that potential unsafe conditions exist on
some IFE systems installed on various transport category airplanes.
These conditions can be summarized as:
◙ Electrical bus(es) supplying power to the IFE system cannot
be de-energized when necessary without removing power from systems that
may be required for continued safe flight and landing.
◙ Power cannot be removed from the IFE system when required
without pulling IFE system circuit breakers (i.e., there is no switch
dedicated to the IFE system or combination of systems for the purpose
of removing power).
◙ Installation of the IFE system has affected crew
(flightcrew and/or cabin crew) procedures, but the procedures have not
been properly revised.

FAA's Determination

As part of our review of IFE systems, we have determined that an
unsafe condition exists on all Boeing Model 737-200 series airplanes
modified by STC ST00516AT. The IFE system on these airplanes is
connected to an electrical bus that cannot be deactivated without also
removing power from airplane systems necessary for safe flight and
landing. There is no other means to remove power from the IFE system.
Additionally, the airplane manufacturer's published flightcrew and
cabin crew emergency procedures do not advise that power cannot be
removed from the IFE system. This condition, if not corrected, could
result in the airplane crew's inability to remove power from the IFE
system during a non-normal or emergency situation, and consequent
inability to control smoke or fumes in the airplane flight deck or
cabin.

Explanation of Relevant Service Information

The FAA has reviewed and approved Kosola and Associates Service
Bulletin 2002-1, dated July 16, 2003, which describes a procedure for
removing the IFE system installed by STC ST00516AT. The procedure
includes disconnecting the power line that leads from the IFE system
control unit to the P6 panel, capping and stowing all related wiring or
removing that wiring from the airplane, removing the IFE system circuit
breaker from the P6 panel, and removing all components of the IFE
system from the airplane. Accomplishment of the actions specified in
the service bulletin is intended to adequately address the identified
unsafe condition.

Explanation of Requirements of Proposed Rule

Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require accomplishment of the actions specified in
the service bulletin described previously.

Other Relevant Rulemaking

The FAA has previously issued several ADs that address unsafe
conditions and require corrective actions similar to those that would
be required by the proposed AD. These other ADs, and the airplane
models and STCs to which they apply, are as follows:

--------------------------------------------------------------------------------------------------------------------------------------------------------
Model/series STC No. AD reference
--------------------------------------------------------------------------------------------------------------------------------------------------------
Airbus A340-211.............................................. ST0902AC-D.................................. AD 2001-18-01, amendment 39-12427 (66 FR
46939, September 10, 2001).
Boeing 737-300............................................... ST00171SE................................... AD 2001-14-10, amendment 39-12321 (66 FR
36455, July 12, 2001).
Boeing 737-700............................................... ST09100AC-D, ST09104AC-D, ST09105AC-D, AD 2001-14-12, amendment 39-12323 (66 FR
ST09106AC-D. 36452, July 12, 2001).
Boeing 747-100 and -200...................................... SA8622SW.................................... AD 2001-14-11, amendment 39-12322 (66 FR
36453, July 12, 2001).
Boeing 747-100 and -200...................................... ST00196SE................................... AD 2001-16-19, amendment 39-12388 (66 FR
43068, August 17, 2001).

[[Page 52541]]

Boeing 747-400............................................... SA8843SW.................................... AD 2001-14-15, amendment 12326 (66 FR
36447, July 12, 2001).
Boeing 747SP................................................. ST09097AC-D................................. AD 2001-14-14, amendment 39-12325 (66 FR
36449, July 12, 2001).
Boeing 757-200............................................... SA1727GL.................................... AD 2001-14-01, amendment 39-12311 (66 FR
36149, July 11, 2001).
Boeing 767-200............................................... SA4998NM.................................... AD 2001-16-21, amendment 39-12390 (66 FR
43072, August 17, 2001).
Boeing 767-200............................................... SA5134NM.................................... AD 2001-16-20, amendment 39-12389 (66 FR
43066, August 17, 2001).
Boeing 767-200............................................... ST09022AC-D................................. AD 2001-14-13, amendment 39-12324 (66 FR
36450, July 12, 2001).
Boeing 767-300............................................... SA5765NM, SA5978NM.......................... AD 2001-16-17, amendment 39-12386 (66 FR
42937, August 16, 2001).
Boeing 767-300............................................... SA7019NM-D.................................. AD 2001-18-08, amendment 39-12434 (66 FR
46517, September 6, 2001).
Boeing 767-300............................................... ST00118SE................................... AD 2001-14-04, amendment 39-12314 (66 FR
36699, July 13, 2001).
Boeing 767-300............................................... ST00157SE................................... AD 2001-16-18, amendment 39-12387 (66 FR
43070, August 17, 2001).
McDonnell Douglas DC-9-51 and DC-9-83........................ SA8026NM.................................... AD 2001-14-02, amendment 39-12312 (66 FR
36456, July 12, 2001).
McDonnell Douglas DC-10-30................................... SA8452SW.................................... AD 2001-16-22, amendment 39-12391 (66 FR
43074, August 17, 2001).
McDonnell Douglas DC-10-30................................... ST00054SE................................... AD 2001-13-03, amendment 39-12313 (66 FR
36150, July 11, 2001).
Boeing 767-300............................................... ST01869AT-D................................. AD 2002-26-14, amendment 39-13002 (68 FR
1525, January 13, 2003).
Boeing 767-300............................................... STC01783AT-D................................ AD 2003-07-15, amendment 39-13111 (68 FR
18535, April 16, 2003).
--------------------------------------------------------------------------------------------------------------------------------------------------------

Changes to 14 CFR Part 39/Effect on the Proposed AD

On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance (AMOCs). Because we have now included this material in part
39, only the office authorized to approve AMOCs is identified in each
individual AD.

Explanation of Cost Impact

We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, has been
revised to reflect this increase in the specified hourly labor rate.

Cost Impact

There are approximately 4 Model 737-200 series airplanes of the
affected design in the worldwide fleet. The FAA estimates that 2
airplanes of U.S. registry would be affected by this proposed AD, that
it would take approximately 1 work hour per airplane to accomplish the
proposed actions, and that the average labor rate is $65 per work hour.
Based on these figures, the cost impact of the proposed AD on U.S.
operators is estimated to be $130, or $65 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this proposed AD were not adopted. The cost impact
figures discussed in AD rulemaking actions represent only the time
necessary to perform the specific actions actually required by the AD.
These figures typically do not include incidental costs, such as the
time required to gain access and close up, planning time, or time
necessitated by other administrative actions.

Regulatory Impact

The regulations proposed herein 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. Therefore, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this 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) if promulgated, 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. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new
airworthiness directive:

[[Page 52542]]

Boeing: Docket 2002-NM-238-AD.

Applicability: Model 737-200 series airplanes modified by
Supplemental Type Certificate (STC) ST00516AT, certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To eliminate the possibility that the airplane crew could be
unable to remove power from the IFE system during a non-normal or
emergency situation, which could result in the airplane crew's
inability to control smoke or fumes in the airplane flight deck or
cabin, accomplish the following:

Removal of IFE System

(a) Within 18 months after the effective date of this AD, remove
the IFE system installed by STC ST00516AT per the procedure in
Kosola and Associates Service Bulletin 2002-1, dated July 16, 2003.
The procedure includes disconnecting the power line that leads from
the IFE system control unit to the P6 panel, capping and stowing all
related wiring or removing related wiring from the airplane,
removing the IFE system circuit breaker from the P6 panel, and
removing all components of the IFE system from the airplane.

Inspections Accomplished Per Previous Issue of Service Bulletin

(b) Removal of the IFE system installed by STC ST00516AT before
the effective date of this AD per Kosola and Associates Service
Bulletin 2002-1, dated June 5, 2002, is considered acceptable for
compliance with paragraph (a) of this AD.

Parts Installation

(c) As of the effective date of this AD, no person may install
an IFE system approved by STC ST00516AT on any airplane.

Alternative Methods of Compliance

(d) In accordance with 14 CFR 39.19, the Manager, Atlanta
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance for this AD.

Issued in Renton, Washington, on August 27, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-22496 Filed 9-3-03; 8:45 am]


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