FR Doc 04-20122

[Federal Register: September 3, 2004 (Volume 69, Number 171)]
[Proposed Rules]
[Page 53848-53853]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03se04-23]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18998; Directorate Identifier 2003-NM-253-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 737-200, 737-300, 737-400,
737-500, 737-600, 737-700, 737-800, 737-900, 757-200, and 757-300
Series Airplanes; and McDonnell Douglas Model DC-10-10, DC-10-10F, DC-
10-30, DC-10-30F, DC-10-40, MD-10-10F, MD-10-30F, MD-11, and MD-11F
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain transport category airplanes.
That AD currently requires modification of the reinforced flight deck
door. This proposed AD would expand the applicability of the existing
AD and require other actions related to the reinforced flight deck
door. These other actions include modifying the door, inspecting and
modifying wiring in the area, and revising the maintenance program to
require more frequent testing of the decompression panels of the flight
deck door. This proposed AD is prompted by reports of discrepancies
with the reinforced flight deck door. We are proposing this AD to
prevent inadvertent release of the decompression latch and consequent
opening of the decompression panel in the flight deck door, or
penetration of the flight deck door by smoke or shrapnel, any of which
could result in injury to the airplane flightcrew. This proposed AD
would also find and fix wire chafing, which could result in arcing,
fire, and/or reduced controllability of the airplane.

DATES: We must receive comments on this proposed AD by October 18,
2004.

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.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207; or C & D Aerospace, 5701 Bolsa Avenue, Huntington Beach,
California 92647-2063.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or at the Docket Management Facility, U.S.

Department of Transportation, 400 Seventh Street SW., room PL-401, on
the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ron Atmur, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood,

[[Page 53849]]

California 90712-4137; telephone (562) 627-5224; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-18998;
Directorate Identifier 2003-NM-253-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 our
docket 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 the 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.

We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.Examining
the Docket

You can 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 DMS receives them.

Discussion

On July 2, 2003, we issued AD 2003-14-04, amendment 39-13223 (68 FR
41063, July 10, 2003), for certain Boeing Model 737-200, 737-300, 737-
400, 737-500, 737-600, 737-700, 737-800, 737-900, 757-200, and 757-300
series airplanes; and McDonnell Douglas Model DC-10-10F, DC-10-30, DC-
10-30F, DC-10-40, MD-10-30F, MD-11, and MD-11F airplanes. That AD
requires modification of the reinforced flight deck door installed on
the airplane. That AD was prompted by several reports of incidents
involving the reinforced flight deck door on certain Boeing Model 737-
300, 737-500, 737-800, and 757-200 series airplanes. We issued that AD
to prevent inadvertent release of the decompression latch and
consequent opening of the decompression panel in the flight deck door.
If an airplane crewmember is in close proximity to the flight deck door
when the decompression panel opens, the decompression panel could hit
and injure the crewmember.

Actions Since Existing AD Was Issued

Since we issued AD 2003-14-04, we have made these determinations:
Some subject airplanes may have been excluded from AD
2003-14-04's applicability. The requirements of that AD should apply to
any airplane that has an affected reinforced flight deck door installed
under certain supplemental type certificates (STC), not just those
airplanes listed in the service bulletins that AD 2003-14-04
references.
For Model DC-10, MD-11, and MD-11F series airplanes, the
currently required modifications may not prevent inadvertent release of
the decompression latch and consequent opening of the decompression
panel in the flight deck door. Installing new, improved latch straps on
the upper and lower decompression panels on the flight deck door will
better ensure that a decompression panel does not open inadvertently.
Based on post-certification testing, other modifications
are necessary to the reinforced flight deck door. These modifications
are included in the service information we reference in AD 2003-14-04,
but we did not previously require them (as explained in the
``Differences Between This AD and the Service Bulletins'' section of AD
2003-14-04). Installing an armor plate over the deadbolt area of the
flight deck door will better protect the door edge and door lip
extrusion against penetration by bullets. Although the door as
certified meets the ballistics and intrusion resistance security
requirements of Section 25.795 (``Security Considerations'') of the
Federal Aviation Regulations (14 CFR 25.795) (when the door is properly
closed, latched, and locked), fragments caused by a bullet striking the
door latch area could enter the flight deck and cause injury to a
member of the flightcrew. Also, strengthening the smoke screens will
allow the smoke screens to close properly and prevent smoke from
entering the flight deck in the event of a fire in the airplane. Smoke
in the flight deck could hinder the flightcrew's ability to continue to
fly the airplane safely.
For certain Model 737 and 757 series airplanes, the
interval for the repetitive functional test of the decompression panels
of the reinforced flight deck doors, as established in the original
issue of the Certification Maintenance Requirements (CMR) document, is
not conservative enough. More frequent inspections are needed to ensure
that any failure is found in a timely manner.
Certain wiring in the area of the flight deck door on
Model 737-200 series airplanes could be damaged due to, for example,
chafing against a connector bracket for the flight deck door wiring and
the flight deck door post. This damage could result in arcing, fire,
and/or reduced controllability of the airplane.
These determinations have prompted us to propose the new AD.

Relevant Service Information

We have reviewed these service bulletins:
C & D Aerospace Report B22-69, Revision E, dated November
8, 2002, which applies to certain McDonnell Douglas Model 737 and 757
series airplanes. That report summarizes the CMRs for the reinforced
flight deck doors installed on those airplanes. Revision E of that
report reduces the repetitive interval for functional tests of the
decompression panels of the flight deck door.

[[Page 53850]]

C & D Aerospace Service Bulletin B211200-52-02, Revision
2, dated September 29, 2003, which applies to certain flight deck door
assemblies installed on certain McDonnell Douglas Model DC-10, MD-10,
and MD-11 airplanes. (AD 2003-14-04 refers to Revision 1 of that
service bulletin, dated June 3, 2003, as the appropriate source of
service information for installing spacers in the upper and lower
pressure relief latch assemblies.) In addition to the procedures for
installing spacers in the upper and lower pressure relief latch
assemblies, that service bulletin describes procedures for installing
an armor plate in the area of the deadbolt for ballistics
reinforcement, and installing stiffeners to strengthen the smoke screen
on the decompression panels.
C & D Aerospace Service Bulletin B211200-52-01, Revision
3, dated September 18, 2003, which applies to certain flight deck door
assemblies installed on certain McDonnell Douglas Models DC-10, MD-11,
and MD-11F airplanes. That service bulletin describes procedures for
modifying the upper and lower pressure relief latch assemblies by
installing new latch straps.
C & D Aerospace Alert Service Bulletin B221001-52A02,
dated November 5, 2002, which applies to certain flight deck door
assemblies installed on certain Boeing Model 737-200 series airplanes.
That service bulletin describes procedures for inspecting for chafing
of wire bundles in the area of the flight deck door, and corrective
actions if necessary. The corrective actions involve rerouting certain
wiring or reorienting certain brackets, as applicable.
C & D Aerospace Alert Service Bulletin B221001-52A05,
Revision 2, dated June 19, 2003, which applies to certain flight deck
door assemblies installed on certain Boeing Model 737-200 series
airplanes. That service bulletin describes procedures for reworking
certain wiring for the flight deck door to relocate a power wire for
the flight deck door.
C & D Aerospace Service Bulletin B221200-52-01, Revision
1, dated June 27, 2003, which applies to certain flight deck door
assemblies installed on certain Boeing Model 737 and 757 series
airplanes. That service bulletin describes procedures for installing an
armor plate in the area of the flight deck door deadbolt for ballistics
reinforcement.
C & D Aerospace Alert Service Bulletin B251200-52-01,
dated April 30, 2003, which applies to certain flight deck door
assemblies installed on certain Model MD-11 airplanes. That service
bulletin describes procedures for modifying the flight deck door by
installing stiffeners to strengthen the smoke screen on the flight deck
door's decompression panels.
Doing the actions specified in the applicable service information
is intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. Therefore, we are proposing this AD, which
would supersede AD 2003-14-04. This proposed AD would continue to
require modification of the reinforced flight deck door. This proposed
AD would expand the applicability of the existing AD to include all
airplanes modified under certain STCs. This proposed AD would require
you to do the actions in the applicable service information described
previously, using that same service information, except as discussed
under ``Differences Between the Proposed AD and Service Information.''
This proposed AD would also require you to revise the airplane's
maintenance program to require repetitive functional testing of the
decompression panels of the flight deck door at the intervals specified
in C & D Aerospace Report B22-69, Revision E.

Differences Between the Proposed AD and Service Information

Although the service bulletins recommend accomplishing the
modification ``as soon as manpower, facilities, and retrofit kits
become available,'' or ``as soon as possible,'' we have determined that
a more specific compliance time is necessary to ensure an adequate
level of safety for the affected fleet. In developing an appropriate
compliance time for this AD, we considered the flight deck door
manufacturer's recommendation, the degree of urgency associated with
the subject unsafe conditions, the number of affected airplanes in the
fleet, and the time necessary to perform the modifications. In light of
all of these factors, we find that 6 months to 18 months, depending on
the action, represents an appropriate interval of time for affected
airplanes to continue to operate without compromising safety.
C & D Aerospace Alert Service Bulletin B221001-52A02 specifies
inspecting for chafing of wire bundles in the area of the flight deck
door, but does not specify the type of inspection. Paragraph (l)(2) of
this proposed AD identifies this inspection as a general visual
inspection, and Note 2 of this proposed AD defines this inspection.
Table 3 of this proposed AD specifies that the actions in C & D
Aerospace Service Bulletin B211200-52-01 must be done on McDonnell
Douglas Model DC-10-10, DC-10-10F, DC-10-30, DC-10-30F, DC-10-40, MD-
10-10F, MD-10-30F, MD-11, and MD-11F airplanes that are equipped with a
flight deck door assembly having part number B211200. Though the
effectivity listing of C & D Aerospace Service Bulletin B211200-52-01
does not identify all of these models, we find that the subject flight
deck door assembly is type certificated for all of these models. Thus,
listing all affected models will ensure that the applicable actions are
done on all affected airplanes.

Changes to Existing AD

This proposed AD would retain all requirements of AD 2003-14-04.
Since AD 2003-14-04 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 2003-14-04 this proposed AD
------------------------------------------------------------------------
Paragraph (a)......................... Paragraph (f).
Paragraph (b)......................... Paragraph (g).
Paragraph (c)......................... Paragraph (h).
------------------------------------------------------------------------

Also, we have revised paragraph (f)(3) of this proposed AD (which
was paragraph (a)(3) of the existing AD) to remove the last sentence of
the paragraph. We have determined that this sentence does not apply to
the airplanes listed in paragraph (f)(3).

Costs of Compliance

This proposed AD would affect about 3,423 airplanes worldwide.
The following table provides the estimated costs for U.S. operators
to comply with the currently required actions that this proposed AD
would continue to require, at an average labor rate of $65 per work
hour.

[[Page 53851]]

Estimated Costs: Existing Requirements of AD 2003-14-04
----------------------------------------------------------------------------------------------------------------
As Listed in C & Number of
D Aerospace Cost per U.S.-
Airplane models Service Work hours Parts airplane registered Fleet cost
Bulletin-- airplanes
----------------------------------------------------------------------------------------------------------------
737.......................... B221001-52-03, 1 $0 $65 1,040 $67,600
Revision 3.
757.......................... B231001-52-02, 2 0 130 519 67,470
Revision 4.
DC-10, MD-10, MD-11.......... B211200-52-02, 2 0 130 21 2,730
Revision 1.
----------------------------------------------------------------------------------------------------------------

The following table provides the estimated costs for U.S. operators
to comply with the new actions that would be required by this proposed
AD, at an average labor rate of $65 per work hour.

Estimated Costs: New Proposed Requirements
--------------------------------------------------------------------------------------------------------------------------------------------------------
Cost per Number of U.S.-registered
Airplane models Action Work hours Parts airplane airplanes Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
737...................................... Modification in C & D 1 $0 $65 Unknown: airplanes not N/A
Aerospace Service Bulletin modified under AD 2003-14-
B221001-52-03, Revision 3. 04.
737, 757................................. Revision of maintenance 1 None 65 651........................ $42,315
program.
737, 757................................. Modification in C & D 1 0 65 1,673...................... 108,745
Aerospace Service Bulletin
B221200-52-01, Revision 1.
737-200.................................. Modification in C & D 1 None 65 134........................ 8,710
Aerospace Alert Service
Bulletin B221001-52A05,
Revision 2.
737-200.................................. Inspection in C & D 2 None 130 134........................ 17,420
Aerospace Alert Service
Bulletin B221001-52A02.
757...................................... Modification in C & D 2 0 130 Unknown: airplanes not N/A
Aerospace Service Bulletin modified under AD 2003-14-
B231001-52-02, Revision 4. 04.
DC-10, MD-11, MD-11F..................... Modification in C & D 1 0 65 155........................ 10,075
Aerospace Service Bulletin
B211200-52-01, Revision 3.
DC-10, MD-10, MD-11...................... Modification in C & D 2 0 130 Unknown: airplanes not N/A
Aerospace Service Bulletin modified under AD 2003-14-
B211200-52-02. 04.
MD-11.................................... Modification in C & D 1 0 65 6.......................... 390
Aerospace Alert Service
Bulletin B251200-52-01.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 removing amendment 39-13223 (68 FR
41063, July 10, 2003) and adding the following new airworthiness
directive (AD):

[[Page 53852]]

Transport Category Airplanes: Docket No. FAA-2004-18998; Directorate
Identifier 2003-NM-253-AD.

Comments Due Date

(a) The Federal Aviation Administration must receive comments on
this airworthiness directive (AD) action by October 18, 2004.

Affected ADs

(b) This AD supersedes AD 2003-14-04, amendment 39-13223.

Applicability

Table 1.--Affected Airplane Models
------------------------------------------------------------------------
Modified by
Supplemental
Airplane manufacturer Airplane model Type Certificate
(STC)
------------------------------------------------------------------------
Boeing........................ 737-200, -300, -400, - ST01335LA
500, -600, -700, -
800, and -900 series.
Boeing........................ 757-200 and -300 ST9514LA-T
series.
McDonnell Douglas............. DC-10-10, DC-10-10F, ST01391LA
DC-10-30, DC-10-30F,
DC-10-40, MD-10-10F,
MD-10-30F, MD-11, and
MD-11F.
------------------------------------------------------------------------

Unsafe Condition

(d) This AD was prompted by reports of discrepancies with the
reinforced flight deck door. We are issuing this AD to prevent
inadvertent release of the decompression latch and consequent
opening of the decompression panel in the flight deck door, or
penetration of the flight deck door by smoke or shrapnel, any of
which could result in injury to the airplane flightcrew. We are also
issuing this AD to find and fix wire chafing, which could result in
arcing, fire, and/or reduced controllability 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.

Requirements of AD 2003-14-04

Note 1: Where there are differences between this AD and the
referenced service bulletins, this AD prevails.

Modification

(f) For airplanes listed in Table 2 of this AD: Within 90 days
after July 25, 2003 (the effective date of AD 2003-14-04, amendment
39-13223), modify the reinforced flight deck door according to
paragraph (f)(1), (f)(2), or (f)(3) of this AD, as applicable.

Table 2.--Airplane Models Subject to Requirements of AD 2003-14-04
------------------------------------------------------------------------
As listed in C&D
Airplane manufacturer Airplane model Aerospace Service
Bulletin--
------------------------------------------------------------------------
Boeing...................... 737-200, -300, -400, B221001-52-03,
-500, -600, -700, - Revision 3, dated
800, and -900 March 25, 2003.
series.
Boeing...................... 757-200 and -300 B231001-52-02,
series. Revision 4, dated
March 19, 2003.
McDonnell Douglas........... DC-10-10F, DC-10-30, B211200-52-02,
DC-10-30F, DC-10- Revision 1, dated
40, MD-10-30F, MD- June 3, 2003.
11, and MD-11F.
------------------------------------------------------------------------

(1) For Boeing Model 737-200, -300, -400, -500, -600, -700, -
800, and -900 series airplanes: Modify the upper and lower pressure
relief latch assemblies on the flight deck door by doing all actions
specified in and according to paragraphs 3.A., 3.B., and 3.C. of the
Accomplishment Instructions of C & D Aerospace Service Bulletin
B221001-52-03, Revision 3, dated March 25, 2003. One latch strap
should be installed at the bottom of the upper pressure relief
assembly, and a second latch strap should be installed at the top of
the lower pressure relief assembly. When properly installed, the
strap should cover a portion of the latch hook.
(2) For Boeing Model 757-200 and -300 series airplanes: Modify
the upper and lower pressure relief latch assemblies on the flight
deck door by doing all actions specified in and according to
paragraphs 3.A., 3.B., and 3.C. of the Accomplishment Instructions
of C & D Aerospace Service Bulletin B231001-52-02, Revision 4, dated
March 19, 2003. One latch strap should be installed at the bottom of
the upper pressure relief assembly, and a second latch strap should
be installed at the top of the lower pressure relief assembly. When
properly installed, the strap should cover a portion of the latch
hook.
(3) For McDonnell Douglas DC-10-10F, DC-10-30, DC-10-30F, DC-10-
40, MD-10-30F, MD-11, and MD-11F airplanes: Install spacers in the
upper and lower pressure relief latch assemblies of the flight deck
door, by doing all actions specified in and according to paragraphs
3.A., 3.C., and 3.D. of C & D Aerospace Service Bulletin B211200-52-
02, Revision 1, dated June 3, 2003; or Revision 2, dated September
29, 2003.

Modifications Accomplished Per Previous Issues of Service Bulletin

(g) For airplanes listed in Table 2 of this AD: Modifications
accomplished before July 25, 2003, per a service bulletin listed in
paragraph (g)(1), (g)(2), or (g)(3) of this AD; as applicable; are
considered acceptable for compliance with the corresponding action
specified in paragraph (f) of this AD.
(1) For Boeing Model 737-200, -300, -400, -500, -600, -700, -
800, and -900 series airplanes: C & D Aerospace Service Bulletin
B221001-52-03, dated December 6, 2002; Revision 1, dated January 2,
2003; or Revision 2, dated February 20, 2003.
(2) For Boeing Model 757-200 and -300 series airplanes: C & D
Aerospace Service Bulletin B231001-52-02, dated December 6, 2002;
Revision 1, dated January 2, 2003; Revision 2, dated February 20,
2003; or Revision 3, dated March 7, 2003.
(3) For McDonnell Douglas DC-10-10F, DC-10-30, DC-10-30F, DC-10-
40, MD-10-30F, MD-11, and MD-11F airplanes: C & D Aerospace Service
Bulletin B211200-52-02, dated April 30, 2003.

Parts Installation

(h) As of July 25, 2003, no person may install, on any airplane,
a reinforced flight deck door having any part number listed in the
paragraph 1.A. of C & D Aerospace Service Bulletin B221001-52-03,
Revision 3, dated March 25, 2003; B231001-52-02, Revision 4, dated
March 19, 2003; or B211200-52-02, Revision 1, dated June 3, 2003; as
applicable; unless the door has been modified as required by
paragraph (f) of this AD.

New Requirements of This AD

Model 737 and 757 Series Airplanes: Revise Maintenance Program

(i) For Model 737-200, -300, -400, -500, -600, -700, -800, and -
900 series airplanes; and Model 757-200 and -300 series airplanes:
Within 6 months after the effective date of this AD, revise the FAA-
approved maintenance inspection program to include the information
specified in C & D Report

[[Page 53853]]

CDR B22-69, Revision E, dated November 8, 2002.

Modifications to Flight Deck Door

(j) Modify the reinforced flight deck door by doing all
applicable actions specified in the applicable service bulletin
listed in Table 3 of this AD at the applicable compliance time
specified in that table.

Table 3.--New Modifications to the Flight Deck Door
----------------------------------------------------------------------------------------------------------------
Equipped with a flight Within this compliance Do all actions in
For these models-- deck door assembly having time after the effective the accomplishment
this P/N-- date of this AD-- instructions of--
----------------------------------------------------------------------------------------------------------------
McDonnell Douglas DC-10-10, DC-10- B211200 6 months.................. C & D Aerospace
10F, DC-10-30, DC-10-30F, DC-10- Service Bulletin
40, MD-10-10F, MD-10-30F, MD-11, B211200-52-01,
and MD-11F airplanes. Revision 3, dated
September 18, 2003.
McDonnell Douglas Model MD-11 and B251200 6 months.................. C & D Aerospace
MD-11F airplanes. Alert Service
Bulletin B251200-52-
01, dated April 30,
2003.
Boeing Model 737-200, -300, -400, - B221200 18 months................. C & D Aerospace
500, -600, -700, -800, and -900 Service Bulletin
series airplanes; and Model 757- B221200-52-01,
200 and -300. Revision 1, dated
June 27, 2003.
Boeing Model 737-200, -300, -400, - B221001 18 months................. C & D Aerospace
500, -600, -700, -800, and -900 Service Bulletin
series airplanes. B221001-52-03,
Revision 3, dated
March 25, 2003;
except as provided
by paragraph (k) of
this AD.
Boeing Model 757-200 and -300 B231001 18 months................. C & D Aerospace
series airplanes. Service Bulletin
B231001-52-02,
Revision 4, dated
March 19, 2003;
except as provided
by paragraph (k) of
this AD.
McDonnell Douglas DC-10-10, DC-10- B211200 18 months................. C & D Aerospace
10F, DC-10-30, DC-10-30F, DC-10- Service Bulletin
40, MD-10-10F, MD-10-30F, MD-11, B211200-52-02,
and MD-11F airplanes. Revision 1, dated
June 3, 2003; or
Revision 2, dated
September 29, 2003,
except as provided
by paragraph (k) of
this AD.
----------------------------------------------------------------------------------------------------------------

(k) For airplanes subject to paragraph (f) of this AD: Actions
required by paragraph (f) of this AD that were done within the
compliance time specified in paragraph (f) of this AD do not need to
be repeated in accordance with paragraph (j) of this AD.

Model 737-200 Series Airplanes: Wiring Modification/Inspection

(l) For Model 737-200 series airplanes equipped with flight deck
door assembly P/N B221001: Within 18 months after the effective date
of this AD, do paragraphs (l)(1) and (l)(2) of this AD.
(1) Rework the wiring for the flight deck door to relocate a
power wire for the flight deck door, in accordance with the
Accomplishment Instructions of C & D Aerospace Alert Service
Bulletin B221001-52A05, Revision 2, dated June 19, 2003.
(2) Perform a general visual inspection for chafing of wire
bundles in the area of the flight deck door and applicable
corrective actions by doing all of the actions in the Accomplishment
Instructions of C & D Aerospace Alert Service Bulletin B221001-
52A02, dated November 5, 2002. Any applicable corrective actions
must be done before further flight.
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.''

Parts Installation

(m) As of the effective date of this AD, no person may install a
reinforced flight deck door under any STC listed in Table 1 of this
AD, on any airplane, unless all applicable requirements of this AD
have been done on the door.

Alternative Methods of Compliance (AMOCs)

(n)(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested in accordance with the procedures found in 14 CFR 39.19.
(2) Alternative methods of compliance, approved previously per
AD 2003-14-04, amendment 39-13223, are approved as alternative
methods of compliance with this AD.

Issued in Renton, Washington, on August 25, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-20122 Filed 9-2-04; 8:45 am]

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