[Federal Register Volume 64, Number 207 (Wednesday, October 27, 1999)]
[Proposed Rules]
[Pages 57811-57814]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-27941]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-168-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness

[[Page 57812]]

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. That AD was 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. For certain airplanes, this action would 
require the installation or modification of a flapper door ramp 
deflector on the forward entry drop ceiling structure. For certain 
other airplanes, this action would require inspection of the wire 
assembly support installation for evidence of chafing, and corrective 
actions, if necessary; and modification of the subject area. The 
actions specified by the proposed AD are intended to prevent such 
chafing, which could result in an electrical fire in the passenger 
compartment.

DATES: Comments must be received by December 13, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-168-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule 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 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.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-168-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 99-NM-168-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On December 31, 1998, the FAA issued AD 98-25-11 R1, amendment 39-
10988 (64 FR 1502, January 11, 1999), applicable to all McDonnell 
Douglas Model MD-11 series airplanes, 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. That action was 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 required by that 
AD are intended to prevent chafing of certain wires above the forward 
passenger doors, which could result in an electrical fire in the 
passenger compartment. [AD 98-25-11 R1 was issued as a correction to AD 
98-25-11, amendment 39-10937 (63 FR 68172, December 10, 1998).]

Actions Since Issuance of Previous Rule

    In the preamble to AD 98-25-11, the FAA specified that the actions 
required by that AD were considered ``interim action'' until final 
action is identified at which time the FAA may consider further 
rulemaking. The manufacturer has since developed a modification, and 
the FAA has determined that further rulemaking action is indeed 
necessary; this proposed AD follows from that determination.

Other Related Rulemaking

    The FAA, in conjunction with Boeing and operators of Model MD-11 
series airplanes, is continuing to review all aspects of the service 
history of those airplanes to identify potential unsafe conditions and 
to take appropriate corrective actions. This proposed AD is one of a 
series of actions identified during that process. The process is 
continuing and the FAA may consider additional rulemaking actions as 
further results of the review become available.

Explanation of Relevant Service Information

    The FAA has reviewed and approved McDonnell Douglas Alert Service 
Bulletin MD11-25A194, Revision 05, dated June 21, 1999, which describes 
procedures for the installation or modification of the flapper door 
ramp deflector on the forward entry drop ceiling structure. The 
modification involves reworking the current middle angle support, part 
number 4223570-5, of the ramp deflector and reidentifying it as part 
number 4223570-9.
    The FAA also has reviewed and approved McDonnell Douglas Alert 
Service Bulletin MD11-24A068, Revision 01, dated March 8, 1999. The 
service bulletin describes procedures for a visual inspection of the 
wire assembly support installation for evidence of chafing, and 
corrective actions, if necessary; and modification of the wire assembly 
support installation above the entry door (L1) sliding panel. The 
corrective actions involve either repairing any chafed part or 
replacing any discrepant part with a new part.
    Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same

[[Page 57813]]

type design, the proposed AD would 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 necessary. The 
proposed AD also would require accomplishment of the actions specified 
in the service bulletins described previously.

Explanation of Change Made to Applicability

    Since the issuance of AD 98-25-11 R1, the FAA has determined that 
the unsafe condition is not likely to exist or develop on McDonnell 
Douglas Model MD-11 series airplanes delivered new as freighter 
aircraft since the flapper door ramp deflector on the forward entry 
drop ceiling was not installed. Therefore, the applicability of the 
proposed AD does not include those airplanes.

Explanation of Changes to Requirements of AD 98-25-11 R1

    The FAA has clarified the inspection requirement contained in AD 
98-25-11 R1. Whereas that AD specified a visual inspection, the FAA has 
revised this proposed AD to clarify that its intent is to require a 
detailed visual inspection. Additionally, a note has been added to the 
proposed AD to define that inspection.
    Operators should note that although AD 98-25-11 R1 requires 
operators to submit a report of the inspection results to the FAA, this 
proposed AD does not require such reporting. As a result of the 
reporting requirements in that AD, the FAA has received an adequate 
amount of inspection reports from operators to determine the proper 
corrective actions.

Cost Impact

    There are approximately 152 airplanes of the affected design in the 
worldwide fleet on which the proposed installation or modification of 
the flapper door ramp deflector on the forward entry drop ceiling 
structure would be required. The FAA estimates that this installation 
or modification would 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 proposed inspection and modification of 
the wire assembly support installation above the entry door (L1) 
sliding panel would be required. The FAA estimates that this inspection 
and modification would 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 that is proposed 
in this AD action would be required on three airplane groups.
     Group 1 (installation of a ramp deflector) affects 
approximately 23 airplanes of U.S. registry and would take 
approximately 8 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts would cost 
approximately $480 per airplane. Based on these figures, the cost 
impact of this proposed requirement of this AD on U.S. operators is 
estimated to be $22,080, or $960 per airplane.
     Group 2 (installation of a ramp deflector) affects 
approximately 4 airplanes of U.S. registry and would take approximately 
8 work hours per airplane to accomplish, at an average labor rate of 
$60 per work hour. Required parts would cost approximately $890 per 
airplane. Based on these figures, the cost impact of this proposed 
requirement of this AD on U.S. operators is estimated to be $5,480, or 
$1,370 per airplane.
     Group 3 (modification of a previously installed ramp 
deflector) affects approximately 2 airplanes of U.S. registry and would 
take approximately 2 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. The cost of required parts 
would be nominal. Based on these figures, the cost impact of this 
proposed 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 
would 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 proposed by this AD on U.S. operators is 
estimated to be $2,460, or $60 per airplane.
    The modification of the wire assembly support installation above 
entry door (L1) sliding panel affects approximately 41 airplanes and 
would take approximately 1 work hour per airplane to accomplish, at an 
average labor rate of $60 per work hour. The cost of required parts 
would be nominal. Based on these figures, the cost impact of this 
modification proposed 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 current or proposed 
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 proposed 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 proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this 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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 57814]]

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), to read as follows:

McDonnell Douglas: 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: Accomplish 
the actions specified in paragraphs (c)(4)(i) and (c)(4)(ii) of this 
AD in accordance with the service bulletin.
    (i) Perform a general visual inspection of the wire assembly 
support installation for evidence of chafing. 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 checked.''

    (ii) Modify the wire assembly support installation above the 
entry door (L1) sliding panel in accordance with the service 
bulletin.

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 
Secs.  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.

    Issued in Renton, Washington, on October 20, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-27941 Filed 10-26-99; 8:45 am]
BILLING CODE 4910-13-U