[Federal Register Volume 65, Number 233 (Monday, December 4, 2000)]
[Rules and Regulations]
[Pages 75612-75615]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-30436]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-31-AD; Amendment 39-12018; AD 2000-24-11]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
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 series 
airplanes, that currently requires 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, and repair, if 
necessary. For certain airplanes, that AD also requires installation or 
modification of a flapper door ramp deflector on the forward entry drop 
ceiling structure. For certain other airplanes, that AD requires 
inspection of the wire assembly support installation for evidence of 
chafing, and corrective actions, if necessary. For certain airplanes 
subject to the existing AD, as well as additional airplanes being added 
to the applicability of this AD, this action adds a requirement for 
modification of a support bracket for the ramp deflector assembly. This 
action is necessary to prevent chafing of electrical wire assemblies 
above the forward passenger doors, which could result in an electrical 
fire in the passenger compartment. This action is intended to address 
the identified unsafe condition.

DATES: Effective January 8, 2001.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-25A194, Revision 06, dated January 27, 2000, as listed in 
the regulations, is approved by the Director of the Federal Register as 
of January 8, 2001.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-25A194, Revision 05, dated June 21, 1999; and McDonnell 
Douglas Alert Service Bulletin MD11-24A068, Revision 01, dated March 8, 
1999, as listed in the regulations, was approved previously by the 
Director of the Federal Register as of March 23, 2000 (65 FR 8034, 
February 17, 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: 
Technical Publications Business Administration, Dept. C1-L51 (2-60). 
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-

[[Page 75613]]

130L, FAA, Transport Airplane Directorate, 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 2000-03-10, 
amendment 39-11569 (65 FR 8034, February 17, 2000), which is applicable 
to certain McDonnell Douglas Model MD-11 series airplanes, was 
published in the Federal Register on July 27, 2000 (65 FR 46206). That 
action proposed to continue to require 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, and repair, if 
necessary. For certain airplanes, that action also proposed to continue 
to require installation or modification of a flapper door ramp 
deflector on the forward entry drop ceiling structure. For certain 
other airplanes, that action also proposed to continue to require 
inspection of the wire assembly support installation for evidence of 
chafing, and corrective actions, if necessary. For certain airplanes 
subject to the existing AD, as well as additional airplanes being added 
to the applicability of this new AD, that action proposed to add a 
requirement for modification of a support bracket for the ramp 
deflector assembly.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 110 airplanes of the affected design in the 
worldwide fleet. 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 
that is currently required by AD 2000-03-10 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 McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06 (approximately 16 airplanes 
of U.S. registry), the installation of the flapper door ramp deflector 
that is currently required by AD 2000-03-10 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 McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06 (approximately 8 airplanes of 
U.S. registry), the installation of the flapper door ramp deflector 
that is currently required by AD 2000-03-10 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 that is currently required by AD 2000-03-10 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 McDonnell Douglas 
Alert Service Bulletin MD11-25A194, Revision 06 (approximately 18 
airplanes of U.S. registry), the new modification that is required in 
this AD action will take 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 required modification on U.S. 
operators is estimated to be $2,160, or $120 per airplane.
    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

    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

    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 removing amendment 39-11569 (65 FR 
8034, February 17, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-12018, to read as follows:

2000-24-11  McDonnell Douglas: Amendment 39-12018. Docket 2000-NM-
31-AD. Supersedes AD 2000-03-10, Amendment 39-11569.


[[Page 75614]]


    Applicability: Model MD-11 series airplanes; as listed in 
McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, 
dated January 27, 2000; and MD11-24A068, Revision 01, dated March 8, 
1999; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (f) 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, which could result in an electrical fire in 
the passenger compartment, accomplish the following:

Restatement of the Requirements of AD 2000-03-10

Detailed Visual 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 visual 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 visual 
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 visual 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 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)(3), and (c)(4) 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; or 
McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, 
dated January 27, 2000. After the effective date of this AD, only 
Revision 06 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; or 
McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, 
dated January 27, 2000. After the effective date of this AD, only 
Revision 06 of the alert service bulletin shall be used.

    Note 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.

    (3) 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; or McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000. 
After the effective date of this AD, only Revision 06 of the alert 
service bulletin shall be used.
    (4) 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 4: 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 under normally 
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 check.''

New Requirements of this AD

One-Time Inspection

    (d) For airplanes other than those identified in paragraph (a) 
of this AD: Within 10 days after the effective date of this AD, 
perform a detailed visual 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.

    Note 5: 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

    (e) For airplanes listed in Group 3 of McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000: 
Within 6 months after the effective date of this AD, 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.

Alternative Methods of Compliance

    (f) 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 6: 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

    (g) 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

    (h) The actions provided by paragraphs (c)(1), (c)(2), (c)(3), 
(c)(4), and (e) of this AD 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; or McDonnell Douglas 
Alert Service Bulletin MD11-24A068, Revision 01, dated March 8, 
1999; as applicable.

[[Page 75615]]

    (1) The incorporation by reference of McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000, 
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; and 
McDonnell Douglas Alert Service Bulletin MD11-24A068, Revision 01, 
dated March 8, 1999, was approved previously by the Director of the 
Federal Register as of March 23, 2000 (65 FR 8034, February 17, 
2000).
    (3) Copies may be obtained from Boeing Commercial Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Technical Publications Business 
Administration, Dept. C1-L51 (2-60). Copies may be inspected at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Los Angeles ACO, 3960 Paramount 
Boulevard, Lakewood, California; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (i) This amendment becomes effective on January 8, 2001.

    Issued in Renton, Washington, on November 22, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 00-30436 Filed 12-1-00; 8:45 am]
BILLING CODE 4910-13-P