Airworthiness Directives; McDonnell Douglas Model MD-11 Series Airplanes

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

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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.

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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]

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