AD 2003-08-08

[Federal Register Volume 68, Number 76 (Monday, April 21, 2003)]
[Rules and Regulations]
[Pages 19330-19334]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-9429]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-62-AD; Amendment 39-13119; AD 2003-08-08]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain McDonnell Douglas Model MD-11 and -11F 
airplanes, that currently requires, among other actions, a one-time 
inspection to detect discrepancies at certain areas around the entry 
light connector of the sliding ceiling panel above the forward 
passenger doors; repair, if necessary; and installation or modification 
of a flapper door ramp deflector on the forward entry drop ceiling 
structure. That AD also currently requires an inspection of the wire 
assembly support installation above the entry door (L1) sliding panel 
for chafing, and repair, if necessary. This amendment requires the 
existing requirements and requires replacing the wire support bracket 
with new support clip assemblies. The actions specified by this AD are 
intended to prevent chafing of electrical wire assemblies above the 
forward passenger doors and above the entry door (L1) sliding panel of 
the forward drop ceiling on the passenger compartment, which could 
result in electrical arcing, and consequent electrical fire in the 
passenger compartment. This action is intended to address the 
identified unsafe condition.

DATES: Effective May 27, 2003.
    The incorporation by reference of Boeing Alert Service Bulletin 
MD11-24A068, Revision 02, dated May 16, 2001; and Boeing Alert Service 
Bulletin MD11-25A194, Revision 07, dated January 9, 2002; as listed in 
the regulations, is approved by the Director of the Federal Register as 
of May 27, 2003.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-25A194, Revision 05, dated June 21, 1999, as listed in 
the regulations, was previously approved by the Director of the Federal 
Register as of March 23, 2000 (65 FR 8034, February 17, 2000).
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-25A194, Revision 06, dated January 27, 2000, as listed in 
the regulations, was previously approved by the Director of the Federal 
Register as of January 8, 2001 (65 FR 75612, December 4, 2000).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data 
and Service Management, Dept. C1-L5A (D800-0024). This information may 
be examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; or 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: Brett Portwood, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5350; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-24-11, 
amendment 39-12018 (65 FR 75612, December 4, 2000), which is applicable 
to certain McDonnell Douglas Model MD-11 and -11F airplanes, was 
published in the Federal Register on August 29, 2002 (67 FR 55368). The 
action proposed to continue to require, among other actions, a one-time 
inspection to detect discrepancies at certain areas around the entry 
light connector of the sliding ceiling panel above the forward 
passenger doors; repair, if necessary; and installation or modification 
of a flapper door ramp deflector on the forward entry drop ceiling 
structure. The action also proposed to continue to require an 
inspection of the wire assembly support installation above the entry 
door (L1) sliding panel for chafing, and repair, if necessary. The 
action also proposed to require replacement of the wire support bracket 
with new support clip assemblies.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

[[Page 19331]]

Request To Revise the Applicability

    One commenter states that it is exempt from the requirements of 
Boeing Alert Service Bulletin MD11-24A068, Revision 02, dated May 16, 
2001 (which is referenced in the notice of proposed rulemaking (NPRM) 
as an appropriate source of service information for accomplishing 
certain proposed actions), because of the statement in the note in 
paragraph 1., ``Planning Information'' of the service bulletin. The 
note states, ``Airplanes that have been modified from passenger to 
freighter and have had the entry door (L1) sliding panel described in 
this service bulletin removed are not affected.'' The commenter further 
states that its fleet has had all sliding panels removed.
    From this comment, the FAA infers that the commenter is requesting 
that we revise the applicability of the NPRM to exclude those airplanes 
mentioned by the commenter. No change to the final rule is necessary 
because the third column of Table 1--Applicability of this AD already 
excludes affected airplanes ``modified from a passenger to a freighter 
configuration on which the entry door (L1) sliding panel described in 
Boeing Alert Service Bulletin MD11-24A068, Revision 02, dated May 16, 
2001, has been removed.''
    The same commenter notes that in Table 1--Applicability, the first 
service bulletin listed is McDonnell Douglas Alert Service Bulletin 
MD11-24A194, Revision 06, dated January 27, 2000. The commenter 
believes the service bulletin should be MD11-25A194. The commenter 
notes that Service Bulletin MD11-24A194, original issue, dated January 
29, 2002, describes procedures for an inspection of the overhead flight 
compartment, not the L1 entry door.
    From this comment, we infer that the commenter is requesting that 
the correct service bulletin be referenced in the applicability. We 
agree. It was our intent, as noted elsewhere in the NPRM, to specify 
McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, 
dated January 27, 2000, in Table 1--Applicability of this AD. 
Therefore, we have revised that table accordingly.

Request To Reference Latest Service Bulletin

    The same commenter notes that McDonnell Douglas Alert Service 
Bulletin MD11-25A194 is now up to Revision 07, dated January 9, 2002.
    From this comment, we infer that the commenter is requesting that 
the NPRM be revised to reference that revision as an additional source 
of service information for accomplishing the proposed installation and 
modification. We agree. We have reviewed and approved Revision 07 of 
Boeing Alert Service Bulletin MD11-25A194. Revision 07, among other 
editorial changes, deletes fuselage number 0450 from the service 
bulletin effectivity. Therefore, we have revised the final rule to 
reference that revision as an appropriate source of service information 
for determining the applicability of the AD and for accomplishing the 
required installation and modification. In addition, we have revised 
the Cost Impact figures accordingly.

Explanation of Change to Notes

    Since the language in Notes 3 and 5 of the NPRM are regulatory in 
nature, we have redesignated those notes as paragraphs in this final 
rule and have renumbered subsequent paragraphs and notes accordingly.

Explanation of Change to Inspection Definitions

    We have changed all references to a ``detailed visual inspection'' 
in the existing AD (requirements are restated in paragraphs (a) through 
(f) of this final rule) to ``detailed inspection'' in this final rule 
to correspond with the terminology in MSG-3. For clarification 
purposes, we also have revised the definition of a ``detailed 
inspection'' in Note 2 of this final rule and a ``general visual 
inspection'' in Note 3 of this final rule.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

1. Actions Currently Required by AD 2000-24-11 and Retained in This AD

    There are approximately 110 airplanes of the affected design in the 
worldwide fleet that are affected by the actions currently required by 
AD 2000-24-11 and retained in this AD. Of these 110 airplanes, the FAA 
estimates that 21 airplanes of U.S. registry will be affected by this 
AD.
    The inspection to detect discrepancies around the entry light 
connector of the slide ceiling panel above the forward passenger doors 
takes approximately 2 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact of this currently required inspection on U.S. operators is 
estimated to be $2,520, or $120 per airplane.
    For Group 1 airplanes as specified in Boeing Alert Service Bulletin 
MD11-25A194, Revision 07 (approximately 16 airplanes of U.S. registry), 
the installation of the flapper door ramp deflector takes approximately 
8 work hours per airplane to accomplish, at an average labor rate of 
$60 per work hour. Required parts cost approximately $455 per airplane. 
Based on these figures, the cost impact of this currently required 
installation on U.S. operators of Group 1 airplanes is estimated to be 
$14,960, or $935 per airplane.
    For Group 2 airplanes as specified in Boeing Alert Service Bulletin 
MD11-25A194, Revision 07 (approximately 8 airplanes of U.S. registry), 
the installation of the flapper door ramp deflector takes approximately 
8 work hours per airplane to accomplish, at an average labor rate of 
$60 per work hour. Required parts cost approximately $890 per airplane. 
Based on these figures, the cost impact of this currently required 
installation on U.S. operators of Group 2 airplanes is estimated to be 
$10,960, or $1,370 per airplane.
    For airplanes listed in McDonnell Douglas Alert Service Bulletin 
MD11-24A068, Revision 01, dated March 8, 1999 (approximately 21 
airplanes of U.S. registry), the inspection of the wire assembly 
support installation takes approximately 1 work hour per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of this currently required inspection on 
U.S. operators is estimated to be $1,260, or $60 per airplane.
    For airplanes in Groups 1 and 3 as specified in Boeing Alert 
Service Bulletin MD11-25A194, Revision 07 (approximately 18 airplanes 
of U.S. registry), the modification of the ramp deflector assembly 
support bracket takes approximately 2 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of this currently required modification 
on U.S. operators is estimated to be $2,160, or $120 per airplane.

2. New Actions Required by This AD

    There are approximately 194 Model MD-11 and -11F airplanes of the 
affected design in the worldwide fleet that are affected by the actions 
required by this AD. Of these 194 airplanes, the FAA estimates that 64 
airplanes of U.S. registry will be affected by this AD.

[[Page 19332]]

    The new actions required by paragraph (g) of this AD will take 
approximately 3 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$294 per airplane. Based on these figures, the cost impact of the new 
requirements of this AD on U.S. operators is estimated to be $30,336, 
or $474 per airplane.

3. Cost Estimate Calculation Information

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this 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 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.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 removing amendment 39-12018 (65 FR 
75612, December 4, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-13119, to read as follows:

2003-08-08 McDonnell Douglas: Amendment 39-13119. Docket 2001-NM-62-
AD. Supersedes AD 2000-24-11, Amendment 39-12018.

    Applicability: The following airplanes listed in Table 1 of this 
AD, certificated in any category:

                         Table 1.--Applicability
------------------------------------------------------------------------
                                                           Excluding
              Model                 As listed in--        airplanes--
------------------------------------------------------------------------
MD-11 and MD-11F airplanes......  Boeing Alert        None.
                                   Service Bulletin
                                   MD11-25A194,
                                   Revision 07,
                                   dated January 9,
                                   2002.
MD-11 and MD-11F airplanes......  Boeing Alert        Modified from a
                                   Service Bulletin    passenger to a
                                   MD11-24A068,        freighter
                                   Revision 02,        configuration on
                                   dated May 16,       which the entry
                                   2001.               door (L1) sliding
                                                       panel described
                                                       in Boeing Alert
                                                       Service Bulletin
                                                       MD11-24A068,
                                                       Revision 02,
                                                       dated May 16,
                                                       2001, has been
                                                       removed.
------------------------------------------------------------------------


    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (h) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent chafing of electrical wire assemblies above the 
forward passenger doors and above the entry door (L1) sliding panel 
of the forward drop ceiling on the passenger compartment, which 
could result in electrical arcing, and consequent electrical fire in 
the passenger compartment, accomplish the following:

Requirements of AD 2000-24-11

Detailed Inspection

    (a) For airplanes listed in McDonnell Douglas Alert Service 
Bulletins MD11-25A194, Revision 05, dated June 21, 1999; and MD11-
24A068, Revision 01, dated March 8, 1999: Within 10 days after 
December 28, 1998 (the effective date of AD 98-25-11 R1, amendment 
39-10988), perform a detailed inspection of the aircraft wiring to 
detect discrepancies that include but are not limited to frayed, 
chafed, or nicked wires and wire insulation in the areas specified 
in paragraphs (a)(1) and (a)(2) of this AD.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

    (1) At the area of the forward drop ceiling just outboard of mod 
block S3-735, and forward and inboard of the light ballast for the 
entry light on the sliding ceiling panel above the forward left 
passenger door (1L) at station location x = 24.75, y = 435, and z = 
64.5.
    (2) At the area above the forward right passenger door (1R) at 
station location x = -30, y = 430, and z = 70 in the ramp deflector 
assembly part number 4223570-501.

Corrective Action

    (b) If any discrepancy is detected during the detailed 
inspection required by paragraph (a) of this AD, prior to further 
flight, repair in accordance with Chapter 20, Standard Wiring 
Practices of the MD-11 Wiring

[[Page 19333]]

Diagram Manual, dated January 1, 1998, or April 1, 1998.

Inspection, Installation, and Modification

    (c) For airplanes listed in McDonnell Douglas Alert Service 
Bulletin MD11-25A194, Revision 05, dated June 21, 1999; or MD11-
24A068, Revision 01, dated March 8, 1999: Within 6 months after 
March 23, 2000 (the effective date of AD 2000-03-10, amendment 39-
11569), accomplish the actions specified in paragraphs (c)(1), 
(c)(2), (c)(4), and (c)(5) of this AD, as applicable.
    (1) For Group 1 airplanes listed in McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999: 
Install a ramp deflector assembly on the right side forward entry 
drop ceiling structure in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999; 
McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, 
dated January 27, 2000; or Boeing Alert Service Bulletin MD11-
25A194, Revision 07, dated January 9, 2002. After the effective date 
of this AD, only Revision 07 of the alert service bulletin shall be 
used.
    (2) For Group 2 airplanes listed in McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999: 
Install a ramp deflector assembly on the right side forward entry 
drop ceiling structure in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999; 
McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, 
dated January 27, 2000; or Boeing Alert Service Bulletin MD11-
25A194, Revision 07, dated January 9, 2002. After the effective date 
of this AD, only Revision 07 of the alert service bulletin shall be 
used.
    (3) Installation of a ramp deflector assembly in accordance with 
McDonnell Douglas Service Bulletin MD11-25-194, dated March 15, 
1996; Revision 01, dated May 1, 1996; Revision 02, dated July 12, 
1996; Revision 03, dated December 12, 1996; or Revision 04, dated 
March 8, 1999; is acceptable for compliance with the requirements of 
paragraph (c)(2) of this AD.
    (4) For Group 3 airplanes listed in McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999: 
Modify the previously installed ramp deflector assembly bracket in 
accordance with McDonnell Douglas Alert Service Bulletin MD11-
25A194, Revision 05, dated June 21, 1999; McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000; 
or Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated 
January 9, 2002. After the effective date of this AD, only Revision 
07 of the alert service bulletin shall be used.
    (5) For airplanes listed in McDonnell Douglas Alert Service 
Bulletin MD11-24A068, Revision 01, dated March 8, 1999: Perform a 
general visual inspection of the wire assembly support installation 
for evidence of chafing, in accordance with the service bulletin. If 
any chafing is detected, prior to further flight, repair or replace 
any discrepant part with a new part in accordance with the service 
bulletin.

    Note 3: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an 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 enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight 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.''

One-Time Inspection

    (d) For airplanes other than those identified in paragraph (a) 
of this AD: Within 10 days after January 8, 2001 (the effective date 
of AD 2000-24-11, amendment 39-12018), perform a detailed inspection 
of the aircraft wiring to detect discrepancies that include but are 
not limited to frayed, chafed, or nicked wires and wire insulation 
in the areas specified in paragraphs (a)(1) and (a)(2) of this AD. 
If any discrepancy is found, prior to further flight, repair in 
accordance with the requirements of paragraph (b) of this AD.
    (e) Accomplishment of the inspection required by paragraph (a) 
of AD 98-25-11 R1, amendment 39-10988, prior to the effective date 
of this AD, is acceptable for compliance with paragraph (d) of this 
AD.

Modification

    (f) For airplanes listed in Group 3 of McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000: 
Within 6 months after January 8, 2001, modify the ramp deflector 
assembly support bracket on the right side forward entry door drop 
ceiling structure, in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000; 
or Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated 
January 9, 2002. After the effective date of this AD, only Revision 
07 of the alert service bulletin shall be used.

New Actions Required by This AD

Inspection, Corrective Action, if Necessary, and Replacement

    (g) For airplanes listed in Groups 1 and 2 in Boeing Alert 
Service Bulletin MD11-24A068, Revision 02, dated May 16, 2001: 
Within 6 months after the effective date of this AD, do the actions 
specified in paragraphs (g)(1) and (g)(2) of this AD.
    (1) Do a general visual inspection of the wire assembly support 
installation above the entry door (L1) sliding panel of the forward 
drop ceiling of the passenger compartment for chafing per the 
service bulletin. If any chafing is found, before further flight, 
repair per the service bulletin.
    (2) Replace the wire support bracket with new support clip 
assemblies and ensure adequate clearance exists for all parts of the 
wire assembly, including breakouts to module blacks and grounds, per 
the service bulletin.

Alternative Methods of Compliance

    (h) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Los Angeles Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Los Angeles ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (i) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (j) Unless otherwise specified in this AD, the actions shall be 
done in accordance with McDonnell Douglas Alert Service Bulletin 
MD11-25A194, Revision 05, dated June 21, 1999; McDonnell Douglas 
Alert Service Bulletin MD11-25A194, Revision 06, dated January 27, 
2000; Boeing Alert Service Bulletin MD11-25A194, Revision 07, dated 
January 9, 2002; and Boeing Alert Service Bulletin MD11-24A068, 
Revision 02, dated May 16, 2001; as applicable.
    (1) The incorporation by reference of Boeing Alert Service 
Bulletin MD11-24A068, Revision 02, dated May 16, 2001; and Boeing 
Alert Service Bulletin MD11-25A194, Revision 07, dated January 9, 
2002; is approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999, was 
previously approved by the Director of the Federal Register as of 
March 23, 2000 (65 FR 8034, February 17, 2000).
    (3) The incorporation by reference of McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000, 
was previously approved by the Director of the Federal Register as 
of January 8, 2001 (65 FR 75612, December 4, 2000).
    (4) Copies may be obtained from Boeing Commercial Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
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

    (k) This amendment becomes effective on May 27, 2003.


[[Page 19334]]


    Issued in Renton, Washington, on April 10, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-9429 Filed 4-18-03; 8:45 am]
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