AD 2000-03-51

[Federal Register Volume 65, Number 39 (Monday, February 28, 2000)]
[Rules and Regulations]
[Pages 10379-10381]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-4337]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-58-AD; Amendment 39-11595; AD 2000-03-51]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-9, Model MD-
90-30, Model 717-200, and Model MD-88 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) 2000-NM-58-AD that was sent 
previously to all known U.S. owners and operators of McDonnell Douglas 
Model DC-9, Model MD-90-30, Model 717-200, and Model MD-88 airplanes by 
individual telegrams. This AD requires inspecting the general condition 
of the jackscrew assembly and the area around the jackscrew assembly to 
detect the presence of metal shavings and flakes. This action is 
prompted by a report from an operator that indicated two instances of 
metallic shavings in the vicinity of the jackscrew assembly and gimbal 
nut of the horizontal stabilizer. The actions specified by this AD are 
intended to prevent loss of pitch trim capability due to excessive wear 
of the jackscrew assembly of the horizontal stabilizer, which could 
result in loss of vertical control of the airplane.

DATES: Effective March 6, 2000, to all persons except those persons to 
whom it was made immediately effective by telegraphic AD 2000-03-51, 
issued February 11, 2000, which contained the requirements of this 
amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 6, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before April 28, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-58-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The applicable service information may be obtained from Boeing 
Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-
2207. 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 90712-4137; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Michael E. O'Neil, Senior Engineer, 
Structures Branch, ANM-120L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5320; Fax (562) 
627-5210.

SUPPLEMENTARY INFORMATION: On February 11, 2000, the FAA issued 
telegraphic AD 2000-03-51, which is applicable to all Model DC-9, Model 
MD-90-30, Model 717-200, and Model MD-88 airplanes; certificated in any 
category.

Background

    On January 31, 2000, a McDonnell Douglas Model DC-9-83 (MD-83) 
airplane was involved in an accident near Los Angeles, California, on a 
flight from Puerto Vallarta, Mexico, to San Francisco, California. The 
FAA has participated in the subsequent accident investigation to 
determine possible causes of the accident. One area of interest in the 
investigation has been the jackscrew assembly of the horizontal 
stabilizer. The FAA has received a report from an operator that 
indicated two instances of metallic shavings in the vicinity of the 
jackscrew assembly and gimbal nut of the horizontal stabilizer. 
Metallic shavings in the vicinity of the horizontal stabilizer indicate 
excessive wear of the jackscrew assembly. Such excessive wear, if not 
corrected, could result in possible loss of pitch trim capability, 
which could result in loss of vertical control of the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
DC9-27A362 (for Model DC-9 and Model MD-88 airplanes), Boeing Alert 
Service Bulletin MD90-27A034 (for Model MD-90-30 airplanes), and Boeing 
Alert Service Bulletin 717-27A0002 (for Model 717-200 airplanes), all 
dated February 11, 2000, which describe procedures for inspecting the 
general condition of the jackscrew assembly and the area around the 
jackscrew assembly to detect the presence of metal shavings and flakes.

Explanation of Requirements of the Rule

    Since the unsafe condition described is likely to exist or develop 
on other airplanes of the same type design, the FAA issued telegraphic 
AD 2000-03-51 to prevent loss of pitch trim capability due to excessive 
wear of the jackscrew assembly of the horizontal stabilizer, which 
could result in loss of vertical control of the airplane. Since an 
unsafe condition has been identified that is likely to exist or develop 
on other airplanes of this same type design, this airworthiness 
directive requires the accomplishment of the previously referenced 
alert service bulletins.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual telegrams 
issued on February 11, 2000, to all known U.S. owners and operators of 
McDonnell Douglas Model DC-9, Model MD-90-30, Model 717-200, and Model 
MD-88 airplanes. These conditions still exist, and the AD is hereby 
published in the Federal Register as an amendment to section 39.13 of 
the Federal Aviation Regulations (14 CFR 39.13) to make it effective to 
all persons.

Interim Action

    This is considered to be interim action until final action is 
identified.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or

[[Page 10380]]

arguments as they may desire. Communications shall identify the Rules 
Docket number and be submitted in triplicate to the address specified 
under the caption ADDRESSES. All communications received on or before 
the closing date for comments will be considered, and this rule may be 
amended in light of the comments received. Factual information that 
supports the commenter's ideas and suggestions is extremely helpful in 
evaluating the effectiveness of the AD action and determining whether 
additional rulemaking action would be needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-58-AD.'' The postcard will be date stamped and 
returned to the commenter.

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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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 adding the following new 
airworthiness directive:

2000-03-51  McDonnell Douglas: Amendment 39-11595. Docket 2000-NM-
58-AD.

    Applicability: All Model DC-9, Model MD-90-30, Model 717-200, 
and Model MD-88 airplanes; 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 loss of pitch trim capability due to excessive wear 
of the jackscrew assembly of the horizontal stabilizer, which could 
result in loss of vertical control of the airplane, accomplish the 
following:

Inspections and Test

    (a) Prior to the accumulation of 650 hours total time-in-service 
(TTIS), or within 72 hours after the effective date of this AD, 
whichever occurs later, accomplish the actions required by 
paragraphs (a)(1), (a)(2), (a)(3), (a)(4), and (a)(5) of this AD; in 
accordance with Boeing Alert Service Bulletin DC9-27A362 (for Model 
DC-9 and Model MD-88 airplanes), Boeing Alert Service Bulletin MD90-
27A034 (for Model MD-90-30 airplanes), and Boeing Alert Service 
Bulletin 717-27A0002 (for Model 717-200 airplanes), all dated 
February 11, 2000. Repeat the inspections, thereafter, at intervals 
not to exceed 650 flight hours.
    (1) Perform a general visual inspection of the lubricating 
grease on the jackscrew assembly and the area directly below the 
jackscrew and surrounding areas for the presence of metal shavings 
and flakes in accordance with paragraph 3.B.2. of the Accomplishment 
Instructions of the applicable alert service bulletin. If the 
presence of metal shavings or flakes is detected, prior to further 
flight, remove and replace the jackscrew assembly with a new or 
serviceable assembly, in accordance with the applicable alert 
service bulletin.
    (2) Perform a general visual inspection of the jackscrew 
assembly to detect the presence of corrosion, pitting, or distress 
in accordance with paragraph 3.B.3. of the Accomplishment 
Instructions of the applicable alert service bulletin. If any 
corrosion, pitting, or distress is detected, prior to further 
flight, replace the jackscrew assembly with a new or serviceable 
assembly, in accordance with the applicable alert service bulletin.
    (3) Check the condition of the jackscrew assembly lubricant in 
accordance with paragraph 3.B.4. of the Accomplishment Instructions 
of the applicable alert service bulletin. If the jackscrew assembly 
is dry, lubricate the assembly in accordance with the applicable 
alert service bulletin.
    (4) Inspect the horizontal stabilizer jackscrew upper and lower 
mechanical stops for general condition in accordance with paragraph 
3.B.5. of the Accomplishment Instructions of the applicable alert 
service bulletin, and record the condition.
    (5) Perform a test of the horizontal stabilizer shutoff controls 
in accordance with paragraph 3.B.6. of the Accomplishment 
Instructions of the applicable alert service bulletin. If the 
mechanical stop on the jackscrew contacts the mechanical stop on the 
acme nut prior to limit switch shutoff, prior to further flight, 
adjust the horizontal stabilizer trim system in accordance with 
operator-approved maintenance instructions.

    Note 2: 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.''

Wear Check

    (b) Within 2,000 flight hours since the last acme screw and nut 
wear check conducted in accordance with the DC9 McDonnell Douglas 
Maintenance Manual, Chapter 27-41-1; MD80 McDonnell Douglas 
Maintenance Manual, Chapter 27-41-01; MD90 McDonnell Douglas 
Maintenance Manual, Chapter 27-41-10; or 717 McDonnell Douglas 
Maintenance Manual, Chapter 27-41-04; or within 30 days after the 
effective date of this AD, whichever occurs later: Perform an acme 
screw and nut wear check in accordance with paragraph 3.B., Phase 2, 
paragraph 2. of the Accomplishment Instructions of Boeing Alert 
Service Bulletin DC9-27A362 (for Model DC-9 and Model MD-88 
airplanes), Boeing Alert Service

[[Page 10381]]

Bulletin MD90-27A034 (for Model MD-90-30 airplanes), and Boeing 
Alert Service Bulletin 717-27A0002 (for Model 717-200 airplanes), 
all dated February 11, 2000. Repeat the inspections, thereafter, at 
intervals not to exceed 2,000 flight hours.

    Note 3: Accomplishment of paragraphs (c), (d), and (e) of the 
Boeing Service Engineering Message Number M-7200-00-00456, dated 
February 9, 2000, constitutes compliance with paragraphs (a)(2), 
(a)(3), and (a)(4) of this AD. Accomplishment of paragraph (a) of 
Boeing Service Engineering Message Number M-7200-00-00456 
constitutes compliance with paragraph (b) of this AD.

Reporting Requirement

    (c) If any damage is detected during any inspection required by 
paragraphs (a) and (b) of this AD, within 48 hours after 
accomplishing the inspections, report the inspection results in 
accordance with Boeing Alert Service Bulletin DC9-27A362 (for Model 
DC-9 and Model MD-88 airplanes), Boeing Alert Service Bulletin MD90-
27A034 (for Model MD-90-30 airplanes), and Boeing Alert Service 
Bulletin 717-27A0002 (for Model 717-200 airplanes), all dated 
February 11, 2000. If no damage is detected during any inspection 
required by this AD, report the inspection results within 10 days of 
accomplishing that inspection in accordance with the appropriate 
alert service bulletin. For airplanes that are inspected after the 
effective date of this AD, include in the report the serial number 
of the airplane, the number of total flight hours and flight cycles 
accumulated on the airplane to the Manager, Los Angeles Aircraft 
Certification Office (ACO), FAA, Transport Airplane Directorate, 
3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone 
(562) 627-5320; Fax (562) 627-5210. Information collection 
requirements contained in this regulation have been approved by the 
Office of Management and Budget (OMB) under the provisions of the 
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have 
been assigned OMB Control Number 2120-0056.

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 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Manager, 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) The actions shall be done in accordance with Boeing Alert 
Service Bulletin DC9-27A362 (for Model DC-9 and Model MD-88 
airplanes), dated February 11, 2000; Boeing Alert Service Bulletin 
MD90-27A034 (for Model MD-90-30 airplanes), dated February 11, 2000; 
and Boeing Alert Service Bulletin 717-27A0002 (for Model 717-200 
airplanes), dated February 11, 2000. 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 Airplane Group, P.O. Box 3707, Seattle, Washington 
98124-2207. 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 6, 2000, to all 
persons except those persons to whom it was made immediately 
effective by telegraphic AD 2000-03-51, issued on February 11, 2000, 
which contained the requirements of this amendment.

    Issued in Renton, Washington, on February 17, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-4337 Filed 2-25-00; 8:45 am]
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