[Federal Register Volume 68, Number 132 (Thursday, July 10, 2003)]
[Rules and Regulations]
[Pages 41063-41065]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-17311]
[[Page 41063]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-152-AD; Amendment 39-13223; AD 2003-14-04]
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-10-10F, DC-10-30, DC-
10-30F, DC-10-40, MD-10-30F, MD-11, and MD-11F Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain transport category airplanes as listed above.
This action requires modification of the reinforced flight deck door
installed on the airplane. This action is necessary 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. This action is intended to address the identified
unsafe condition.
DATES: Effective July 25, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 25, 2003.
Comments for inclusion in the Rules Docket must be received on or
before September 8, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-152-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:
[email protected]. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-152-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 this AD may be obtained from
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington
98124-2207; or C & D Aerospace, 5701 Bolsa Avenue, Huntington Beach,
California 92647-2063. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; at the FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, California; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Ron Atmur, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5224; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: The FAA has received 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. In these
incidents, slamming the flight deck door caused the decompression latch
to release and the decompression panel in the door to open. This
condition, if not corrected, could result in the decompression panel
hitting and injuring an airplane crewmember, if the crewmember is in
close proximity to the flight deck door when the decompression panel
opens.
The decompression latches for the reinforced flight deck doors on
certain Boeing Model 737-200, 737-400, 737-600, 737-700, 737-900, and
757-300 series airplanes; and certain McDonnell Douglas Model DC-10-
10F, DC-10-30, DC-10-30F, DC-10-40, MD-10-30F, MD-11, and MD-11F
airplanes; are identical to those on the affected Model 737-300, 737-
500, 737-800, and 757-200 series airplanes. Therefore, all of these
models may be subject to the same unsafe condition.
The subject reinforced flight deck doors meet 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. The
possibility that the decompression panel may open if the door is
slammed shut is unrelated to the flight deck door's ballistics and
intrusion resistance characteristics.
Explanation of Relevant Service Information
The FAA has reviewed and approved C & D Aerospace Service Bulletin
B221001-52-03, Revision 3, dated March 25, 2003, which applies to
certain Boeing Model 737-200, -300, -400, -500, -600, -700, -800, and -
900 series airplanes; and C & D Aerospace Service Bulletin B231001-52-
02, Revision 4, dated March 19, 2003, which applies to certain Boeing
Model 757-200 and -300 series airplanes. Those service bulletins
describe procedures for modifying the reinforced flight deck door by,
among other things, modifying the upper and lower pressure relief latch
assemblies. The procedures for modifying the upper pressure relief
latch assembly include removing the upper pressure relief latch
assembly and spacer, installing a new decompression latch strap,
reinstalling the existing upper pressure relief latch assembly and
spacer, and installing a new pressure relief latch spacer. The
procedures for modifying the lower pressure relief latch assembly
involve removing the lower pressure relief latch cover, latch assembly,
and spacer; installing a new decompression latch strap; reinstalling
the existing lower pressure relief latch assembly, spacer, and cover;
and installing a new pressure relief latch spacer.
The FAA has also reviewed and approved C & D Aerospace Service
Bulletin B211200-52-02, Revision 1, dated June 3, 2003, which applies
to certain 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 service bulletin
describes procedures for modifying the reinforced flight deck door by,
among other things, installing spacers in the upper and lower pressure
relief latch assemblies. The procedures for installing the spacers
include removing the upper pressure relief latch strap and the upper
and lower pressure relief latch assemblies and spacers, installing new
spacers, and reinstalling the existing upper pressure relief latch
strap, and the upper and lower pressure relief latch assemblies and
spacers.
Accomplishment of the actions specified in the applicable service
bulletin is intended to adequately address the identified unsafe
condition.
Explanation of the Requirements of the Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, this AD requires accomplishment
[[Page 41064]]
of the actions specified in the applicable service bulletin described
previously, except as discussed below under the heading ``Differences
Between This AD and the Service Bulletins.'' The actions are required
to be accomplished according to the applicable service bulletin
described previously.
Operators should note that the illustrations in the service
bulletins may be confusing in a way that would lead to the incorrect
installation of a strap at the top of the upper pressure relief
assembly or on the bottom of the lower pressure relief assembly. 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.
Explanation of Applicability
This AD identifies McDonnell Douglas model designations as
published in the most recent type certificate data sheet for the
affected models.
Differences Between This AD and the Service Bulletins
Although the service bulletins recommend accomplishing the
modification ``as soon as manpower, facilities, and retrofit kits
become available,'' 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 condition, the
number of affected airplanes in the fleet, and the time necessary to
perform the modification (1 to 2 work hours). In light of all of these
factors, we find that a 90-day compliance time represents an
appropriate interval of time for affected airplanes to continue to
operate without compromising safety.
Also, the service bulletins include instructions for other
modifications to the reinforced flight deck door besides those
described previously. However, this AD requires only the modification
of the upper and lower pressure relief latch assemblies for the Boeing
airplane models identified previously, and the installation of spacers
in the upper and lower pressure relief latch assemblies for the
McDonnell Douglas airplane models identified previously.
Changes to 14 CFR Part 39/Effect on the 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.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Submit comments using the following format:
[sbull] 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.
[sbull] For each issue, state what specific change to the AD is
being requested.
[sbull] 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 rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2003-NM-152-AD.'' The postcard will be date stamped
and returned to the commenter.
Regulatory Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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. Section 39.13 is amended by adding the following new airworthiness
directive:
[[Page 41065]]
2003-14-04 Transport Category Airplanes: Amendment 39-13223. Docket
2003-NM-152-AD.
Applicability: The airplanes listed in Table 1 of this AD,
certificated in any category. Table 1 of this AD follows:
Table 1.--Affected Airplane Models
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As listed in C & D Aerospace
Airplane manufacturer Airplane model Service Bulletin
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Boeing..................................... 737-200, -300, -400, -500, -600, - B221001-52-03, Revision 3, dated
700, -800, and -900 series. March 25, 2003.
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Boeing..................................... 757-200 and -300 series.......... B231001-52-02, Revision 4, dated
March 19, 2003.
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McDonnell Douglas.......................... DC-10-10F, DC-10-30, DC-10-30F, B211200-52-02, Revision 1, dated
DC-10-40, MD-10-30F, MD-11, and June 3, 2003.
MD-11F.
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Compliance: Required as indicated, unless accomplished
previously.
To prevent inadvertent release of the decompression latch and
consequent opening of the decompression panel in the reinforced
flight deck door, which could result in the decompression panel
hitting and injuring an airplane crewmember, if the crewmember is in
close proximity to the flight deck door when the decompression panel
opens, accomplish the following:
Note 1: Where there are differences between this AD and the
referenced service bulletins, this AD prevails.
Modification
(a) Within 90 days after the effective date of this AD, modify
the reinforced flight deck door according to paragraph (a)(1),
(a)(2), or (a)(3) of this AD, as applicable.
(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 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. 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.
Modifications Accomplished Per Previous Issues of Service Bulletin
(b) Modifications accomplished before the effective date of this
AD per a service bulletin listed in paragraph (b)(1), (b)(2), or
(b)(3) of this AD; as applicable; are considered acceptable for
compliance with the corresponding action specified in paragraph (a)
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
(c) As of the effective date of this AD, 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 (a) of this AD.
Alternative Methods of Compliance
(d) In accordance with 14 CFR 39.19, the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance for this AD.
Incorporation by Reference
(e) Unless otherwise specified in this AD, the actions shall be
done in accordance with C & D Aerospace Service Bulletin B211200-52-
02, Revision 1, dated June 3, 2003; C & D Aerospace Service Bulletin
B221001-52-03, Revision 3, dated March 25, 2003; or C & D Aerospace
Service Bulletin B231001-52-02, Revision 4, dated March 19, 2003; as
applicable. This incorporation by reference was approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Copies may be obtained from Boeing Commercial
Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207; or C
& D Aerospace, 5701 Bolsa Avenue, Huntington Beach, California
92647-2063. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; at the FAA,
Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
Effective Date
(f) This amendment becomes effective on July 25, 2003.
Issued in Renton, Washington, on July 2, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-17311 Filed 7-9-03; 8:45 am]
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