AD 2000-03-10

[Federal Register Volume 65, Number 33 (Thursday, February 17, 2000)]
[Rules and Regulations]
[Pages 8034-8037]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-3620]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-168-AD; Amendment 39-11569; AD 2000-03-10]
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 all 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, this amendment requires the 
installation or modification of a flapper door ramp deflector on the 
forward entry drop ceiling structure. For certain other airplanes, this 
amendment requires inspection of the wire assembly support installation 
for evidence of chafing, and corrective actions, if necessary. This 
amendment is prompted by a report indicating that damaged electrical 
wires were found above the forward passenger doors due to flapper 
panels moving inboard and chafing the electrical wire assemblies of 
this area. The actions specified by this AD are intended to prevent 
such chafing, which could result in an electrical fire in the passenger 
compartment.

DATES: Effective March 23, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 23, 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, Transport Airplane Directorate, 
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, 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 98-25-11 R1, 
amendment 39-10988 (64 FR 1502, January 11, 1999), which is applicable 
to all McDonnell Douglas Model MD-11 series airplanes, was published in 
the Federal Register on October 27, 1999 (64 FR 57811). The action 
proposed to supersede AD 98-25-11 R1 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

[[Page 8035]]

necessary. For certain airplanes, the action proposed to require the 
installation or modification of a flapper door ramp deflector on the 
forward entry drop ceiling structure. For certain other airplanes, the 
action proposed to require inspection of the wire assembly support 
installation for evidence of chafing, and corrective actions, if 
necessary; and modification of the subject area.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    Two commenters support the proposed rule.

Interim Action

    Since the issuance of the proposed rule, the manufacturer has 
advised the FAA that modifying the wire assembly support installation 
above the entry door (L1) sliding panel in accordance with McDonnell 
Douglas Alert Service Bulletin MD11-24A068, Revision 01, dated March 8, 
1999, may cause further damage of the wire assembly due to the 
possibility of the wire assembly chafing on adjacent brackets. Further, 
the manufacturer advises that it is currently planning to revise the 
alert service bulletin to alleviate the potential chafing problem.
    In light of this new information, the FAA has removed reference to 
this modification requirement [reference paragraph (c)(4)(ii) of the 
proposed rule] from this final rule. The final rule has been 
reformatted to accommodate this change. This AD is now considered to be 
interim action until final action is identified, at which time the FAA 
may consider further rulemaking to address the modification of the 
referenced wire assembly support installation.

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

    There are approximately 152 Model MD-11 series airplanes of the 
affected design in the worldwide fleet on which the installation or 
modification of the flapper door ramp deflector on the forward entry 
drop ceiling structure will be required. The FAA estimates that this 
installation or modification will be required on 29 airplanes of U.S. 
registry.
    There are approximately 152 airplanes of the affected design in the 
worldwide fleet on which the inspection and modification of the wire 
assembly support installation above the entry door (L1) sliding panel 
will be required. The FAA estimates that this inspection and 
modification will be required on 41 airplanes of U.S. registry.
    The actions that are currently required by AD 98-25-11 R1 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 the currently required actions on U.S. operators is estimated 
to be $7,800, or $120 per airplane.
    The new installation or modification of the flapper door ramp 
deflector on the forward entry drop ceiling structure required by this 
AD action will be required on three airplane groups.
    <bullet> Group 1 (installation of a ramp deflector) affects 
approximately 23 airplanes of U.S. registry and will take approximately 
8 work hours per airplane to accomplish, at an average labor rate of 
$60 per work hour. Required parts will cost approximately $480 per 
airplane. Based on these figures, the cost impact of this requirement 
of this AD on U.S. operators is estimated to be $22,080, or $960 per 
airplane.
    <bullet> Group 2 (installation of a ramp deflector) affects 
approximately 4 airplanes of U.S. registry and will take approximately 
8 work hours per airplane to accomplish, at an average labor rate of 
$60 per work hour. Required parts will cost approximately $890 per 
airplane. Based on these figures, the cost impact of this requirement 
of this AD on U.S. operators is estimated to be $5,480, or $1,370 per 
airplane.
    <bullet> Group 3 (modification of a previously installed ramp 
deflector) affects approximately 2 airplanes of U.S. registry and will 
take approximately 2 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. The cost of required parts 
will be nominal. Based on these figures, the cost impact of this 
requirement of this AD on U.S. operators is estimated to be $240, or 
$120 per airplane.
    The inspection of the wire assembly support installation above 
entry door (L1) sliding panel affects approximately 41 airplanes and 
will take 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 inspection required by this AD on U.S. operators is 
estimated to be $2,460, or $60 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. However, the FAA has been advised 
that manufacturer warranty remedies are available for some labor 
associated with accomplishing the required actions. Therefore, the 
future economic cost impact of this rule on U.S. operators may be less 
than the cost impact figures indicated above.

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.

[[Page 8036]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-10988 (64 FR 
1502, January 11, 1999), and by adding a new airworthiness directive 
(AD), amendment 39-11569, to read as follows:

2000-03-10  McDonnell Douglas: Amendment 39-11569. Docket 99-NM-168-
AD. Supersedes AD 98-25-11 R1, Amendment 39-10988.

    Applicability: Model MD-11 series airplanes, as listed in 
McDonnell Douglas Alert Service Bulletins MD11-25A194, Revision 05, 
dated June 21, 1999, 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 (d) 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 certain electrical wires 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 98-25-11 R1

Detailed Visual Inspection

    (a) 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.

New Requirements of This AD

Inspection, Installation, and Modification

    (c) Within 6 months after the effective date of this AD, 
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.
    (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.

    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.
    (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.''

Alternative Methods of Compliance

    (d) 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, Transport Airplane Directorate. 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 5: 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

    (e) 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

    (f) Except as provided by paragraphs (a) and (b) of this AD, the 
actions shall be done in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999; or 
McDonnell Douglas Alert Service Bulletin MD11-24A068, Revision 01, 
dated March 8, 1999; 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 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, Transport 
Airplane Directorate, 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.
    (g) This amendment becomes effective on March 23, 2000.

    Issued in Renton, Washington, on February 10, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-3620 Filed 2-16-00; 8:45 am]
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