[Federal Register Volume 65, Number 153 (Tuesday, August 8, 2000)]
[Rules and Regulations]
[Pages 48355-48358]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-19671]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-89-AD; Amendment 39-11847; AD 2000-15-15]
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 amendment supersedes an existing airworthiness directive 
(AD), applicable to all McDonnell Douglas Model DC-9, Model MD-90-30, 
Model 717-200, and Model MD-88 airplanes, that currently 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 amendment also requires inspecting for metallic 
particles in the lubrication for the jackscrew assembly of the 
horizontal stabilizer and surrounding area to detect any discrepancy; 
follow-on actions; and corrective actions, if necessary. This amendment 
is prompted by numerous reports from operators that indicate instances 
of metallic shavings in the vicinity of the jackscrew assembly and 
gimbal nut of the horizontal stabilizer. The actions specified in 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 reduced controllability of the airplane.

DATES: Effective August 23, 2000.
    The incorporation by reference of Boeing Alert Service Bulletin 
DC9-27A362, Revision 02, dated March 30, 2000; Boeing Alert Service 
Bulletin MD90-27A034, Revision 02, dated March 30, 2000; and Boeing 
Alert Service Bulletin 717-27A0002, Revision 02, dated March 30, 2000; 
as listed in the regulations; is approved by the Director of the 
Federal Register as of August 23, 2000.
    The incorporation by reference of Boeing Alert Service Bulletin 
DC9-27A362, dated February 11, 2000; Boeing Alert Service Bulletin 
MD90-27A034, dated February 11, 2000; and Boeing Alert Service Bulletin 
717-27A0002, dated February 11, 2000; as listed in the regulations; was 
approved previously by the Director of the Federal Register as of March 
6, 2000 (65 FR 10379, February 28, 2000).
    Comments for inclusion in the Rules Docket must be received on or 
before October 10, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000- NM-89-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments sent via the Internet as 
attached electronic files must be formatted in Microsoft Word 97 for 
Windows or ASCII text.
    The service information referenced in this AD may be obtained from 
The Boeing Company, Long Beach Division, 3855 Lakewood Boulevard, Long 
Beach, California 90846, Attention: Technical Publications Business 
Administration, Dept. C1-L52 (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 90712-4137; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mike Lee, Aerospace Engineer, 
Structures Branch, ANM-120L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5325; fax (562) 
627-5210.

SUPPLEMENTARY INFORMATION: On February 17, 2000, the FAA issued AD 
2000-03-51, amendment 39-11595 (65 FR 10379, February 28, 2000), 
applicable to all McDonnell Douglas Model DC-9, Model MD-90-30, Model 
717-200, and Model MD-88 airplanes, to require inspecting the general 
condition of the jackscrew assembly and the area around the jackscrew 
assembly to detect the presence of metal shavings and flakes. That 
action was 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 
required by that 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.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 2000-03-51, the FAA has received numerous 
reports of incidents in which metallic particles (including slivers and 
dust, as well as shavings and flakes) were found imbedded within the 
grease on the threaded portion of the jackscrew assembly of the 
horizontal stabilizer actuator and on the area directly below the 
jackscrew assembly. Findings by the manufacturer indicate that such 
metallic particles can be identified as a non-magnetic metallic 
substance which is golden in color.

New Service Information

    Since the issuance of the previous rule, the FAA has reviewed and 
approved the following new Boeing Alert Service Bulletins, which have 
been approved as alternative methods of compliance to the requirements 
of AD 2000-03-51:
     DC9-27A362, Revision 02, dated March 30, 2000 (for Model 
DC-9 and Model MD-88 airplanes);
     MD90-27A034, Revision 02, dated March 30, 2000 (for Model 
MD-90-30 airplanes); and
     717-27A0002, Revision 02, dated March 30, 2000 (for Model 
717-200 airplanes).
    Revision 02 of the alert service bulletins revises certain 
procedures included in the original issue of the alert service 
bulletins, which were referenced in AD 2000-03-51 as the appropriate 
sources of service information. Revision 02 describes new procedures 
for detailed visual inspections to detect the presence of metallic 
particles (including slivers and dust, as well as shavings and flakes) 
in the lubrication for the jackscrew assembly. In addition, Revision 02 
revises certain follow-on and corrective actions. Follow-on actions 
include performing repetitive inspections, testing the horizontal 
shutoff controls, and lubricating the jackscrew of the horizontal 
stabilizer actuator. Corrective actions include removing dirt/grease 
from exposed jackscrew threads, performing wear checks of the jackscrew 
(endplay and freeplay checks), adjusting the trim system and shutoff 
control system of the horizontal stabilizer, and replacing the 
jackscrew assembly of the horizontal stabilizer actuator with a new or 
serviceable unit.

[[Page 48356]]

    Revision 02 also revises certain replacement procedures. For 
certain discrepancies, although the original issue of the alert service 
bulletins specifies replacement of the jackscrew assembly with a new or 
serviceable assembly, Revision 02 specifies such replacement action 
only if the wear check results are found to be outside specified 
limits.
    Revision 02 describes procedures for follow-on and corrective 
actions, if necessary, following accomplishment of the inspection of 
the horizontal stabilizer actuator jackscrew and nut specified in Phase 
2 of the Accomplishment Instructions. The original issue of the alert 
service bulletins did not specifically include the follow-on and 
corrective actions; however, the original issue referenced certain 
airplane maintenance manuals as additional sources of service 
information for accomplishing the follow-on and corrective actions, as 
well as the inspection.

FAA's Determination

    In consideration of new findings by the manufacturer regarding the 
types of material found in the jackscrew assembly of the horizontal 
stabilizer since issuance of AD 2000-03-51, the FAA has determined that 
the required inspections should be expanded to include metallic 
particles such as slivers and dust, as well as the metal shavings and 
flakes identified in AD 2000-03-51. The inspections, tests, and follow-
on and corrective actions of the applicable alert service bulletins 
described previously are intended to minimize the possibility of 
failure of the horizontal stabilizer jackscrew assembly to maintain 
controllability of the airplane.
    In addition, the FAA has determined that it is necessary for 
operators to report the results of the endplay checks required by 
paragraphs (a) and (b) of this AD to the manufacturer. These results 
are necessary to provide information regarding the wear rates of the 
jackscrew assembly. The FAA will use these data to confirm that the 
repetitive intervals of 650 flight hours, as specified by paragraph (a) 
of this AD, and the repetitive intervals of 2,000 flight hours, as 
specified by paragraph (b) of this AD, are appropriate compliance times 
for accomplishment of the endplay check and are adequate for ensuring 
the safety of the fleet.

Explanation of Requirements of Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of this same type design, this AD 
supersedes AD 2000-03-51. This AD continues to require 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 amendment also requires inspecting for metallic particles 
(including slivers and dust, as well as shavings and flakes) in the 
lubrication for the jackscrew assembly of the horizontal stabilizer and 
surrounding area to detect any discrepancy; follow-on actions; and 
corrective actions, if necessary. The actions are required to be 
accomplished in accordance with the alert service bulletins described 
previously. This AD also requires operators to submit the results of 
the endplay check to the manufacturer.

Interim Action

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

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

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 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-89-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 removing amendment 39-11595 (65 FR 
10379, March 6, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-11847, to read as follows:


[[Page 48357]]


2000-15-15  McDonnell Douglas: Amendment 39-11847. Docket 2000-NM-
89-AD. Supersedes AD 2000-03-51, Amendment 39-11595.

    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.

    Note 2: Inspections and follow-on and corrective actions 
accomplished prior to the effective date of this AD in accordance 
with Revision 1 of Boeing Alert Service Bulletin MD90-27A034, 
Revision 01, DC9-27A362, Revision 01, and 717-27A0002, Revision 01; 
all dated February 12, 2000; are considered acceptable for 
compliance with the applicable actions required by this AD that are 
specified in the original issue of the applicable alert service 
bulletin.

    To prevent loss of pitch trim capability due to excessive wear 
of the jackscrew assembly of the horizontal stabilizer, which could 
result in reduced controllability of the airplane, accomplish the 
following:

Inspections, Check, and Test (Phase 1)

    (a) Prior to the accumulation of 650 hours total time-in-service 
(TTIS), or within 72 hours after March 6, 2000 (the effective date 
of AD 2000-03-51, amendment 39-11595), 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 Phase 1 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
DC9-27A362, dated February 11, 2000 (original issue), or Revision 
02, dated March 30, 2000 (for Model DC-9 and Model MD-88 airplanes); 
MD90-27A034, dated February 11, 2000 (original issue), or Revision 
02, dated March 30, 2000 (for Model MD-90-30 airplanes); or 717-
27A0002, dated February 11, 2000 (original issue), or Revision 02, 
dated March 30, 2000 (for Model 717-200 airplanes); as applicable. 
Repeat the actions required by paragraph (a) of this AD thereafter 
at intervals not to exceed 650 flight hours. As of the effective 
date of this AD, the repetitive inspections required by this 
paragraph must be accomplished as detailed visual inspections in 
accordance with Phase 1 of the Accomplishment Instructions of 
Revision 02 of the applicable alert service bulletin.
    (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 metallic 
particles (including slivers, dust, shavings, and flakes) in 
accordance with Phase 1 of the Accomplishment Instructions of either 
the original issue or Revision 02 of the applicable alert service 
bulletin. If the presence of metallic particles is detected, prior 
to further flight, remove and replace the jackscrew assembly with a 
new or serviceable assembly; or accomplish the detailed visual 
inspections, follow-on actions, and corrective actions, as 
applicable; in accordance with Phase 1 of the Accomplishment 
Instructions of Revision 02 of 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 Phase 1 of the Accomplishment Instructions of 
either the original issue or Revision 02 of the applicable alert 
service bulletin. If any corrosion, pitting, or distress is 
detected, prior to further flight, remove and replace the jackscrew 
assembly with a new or serviceable assembly; or accomplish the 
detailed visual inspections, follow-on actions, and corrective 
actions, as applicable; in accordance with Phase 1 of the 
Accomplishment Instructions of Revision 02 of the applicable alert 
service bulletin.
    (3) During any inspection conducted prior to the effective date 
of this AD, check the condition of the jackscrew assembly lubricant 
in accordance with Phase 1 of the Accomplishment Instructions of the 
original issue of the applicable alert service bulletin. If the 
jackscrew assembly is dry, prior to further flight, lubricate the 
assembly in accordance with Phase 1 of the Accomplishment 
Instructions of Revision 02 of the applicable alert service 
bulletin.

    Note 3: During other inspections required by this AD, 
lubrication of the jackscrew is checked in accordance with Phase 1 
of the Accomplishment Instructions of Revision 02 of the applicable 
alert service bulletin.

    (4) Inspect the horizontal stabilizer jackscrew upper and lower 
mechanical stops for general condition in accordance with the Phase 
1 of the Accomplishment Instructions of either the original issue or 
Revision 02 of the applicable alert service bulletin; and record the 
condition.
    (5) Perform a test of the horizontal stabilizer shutoff controls 
in accordance with Phase 1 of the Accomplishment Instructions of 
either the original issue or Revision 02 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 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.''


    Note 5: 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.''


    Note 6: Accomplishment of steps (b) through (e) of BOECOM 
message number M-7200-00-00456, dated February 9, 2000, constitutes 
compliance with paragraphs (a)(2), (a)(3), (a)(4), and (a)(5) of 
this AD.

Wear Checks (Phase 2)

    (b) Within 2,000 flight hours since the last endplay check of 
the jackscrew and acme nut conducted in accordance with the 
McDonnell Douglas DC-9 Maintenance Manual, Chapter 27-40-1; 
McDonnell Douglas MD-80 Maintenance Manual, Chapter 27-40-01; 
McDonnell Douglas MD-90 Maintenance Manual, Chapter 27-41-10; or 
Boeing 717 Maintenance Manual, Chapter 27-41-04; or within 30 days 
after March 6, 2000, whichever occurs later: Perform endplay and 
freeplay checks of the jackscrew and acme nut in accordance with 
Phase 2 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin DC9-27A362, dated February 11, 2000, or Revision 02, dated 
March 30, 2000 (for Model DC-9 and Model MD-88 airplanes); MD90-
27A034, dated February 11, 2000, or Revision 02, dated March 30, 
2000 (for Model MD-90-30 airplanes); or 717-27A0002, dated February 
11, 2000, or Revision 02, dated March 30, 2000 (for Model 717-200 
airplanes); as applicable. Repeat the endplay and freeplay checks 
thereafter at intervals not to exceed 2,000 flight hours. As of the 
effective date of this AD, only Phase 2 of the Accomplishment 
Instructions of Revision 02 of the applicable alert service bulletin 
shall be used to accomplish the requirements of this paragraph 
(including the corrective actions specified in Phase 2 of the 
Accomplishment Instructions of Revision 02 of the applicable alert 
service bulletin).

    Note 7: Accomplishment of step (a) of BOECOM message number M-
7200-00-00456, dated February 9, 2000, constitutes compliance with 
paragraph (b) of this AD.

Reporting Requirement

    (c) At intervals not to exceed 90 days after accomplishing the 
endplay checks required by paragraphs (a) and (b) of this AD, submit 
a report of the results of the endplay checks to The Boeing Company, 
Long Beach Division, P.O. Box 1771, Long Beach, California 90801, 
Attention: Senior Manager--Systems, Technical and Fleet Support, 
Service Engineering D035-0035; fax: (562) 497-5811. Results of the 
endplay checks may be accumulated and submitted at the intervals 
required by this paragraph. Information collection requirements 
contained in this regulation have been

[[Page 48358]]

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 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 8: 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) Except as provided by paragraph (a)(5) of this AD for 
adjusting the horizontal stabilizer trim system, the actions shall 
be done in accordance with Boeing Alert Service Bulletin DC9-27A362, 
dated February 11, 2000; Boeing Alert Service Bulletin DC9-27A362, 
Revision 02, dated March 30, 2000; Boeing Alert Service Bulletin 
MD90-27A034, dated February 11, 2000; Boeing Alert Service Bulletin 
MD90-27A034, Revision 02, dated March 30, 2000; Boeing Alert Service 
Bulletin 717-27A0002, dated February 11, 2000; or Boeing Alert 
Service Bulletin 717-27A0002, Revision 02, dated March 30, 2000.
    (1) The incorporation by reference of Boeing Alert Service 
Bulletin DC9-27A362, Revision 02, dated March 30, 2000; Boeing Alert 
Service Bulletin MD90-27A034, Revision 02, dated March 30, 2000; and 
Boeing Alert Service Bulletin 717-27A0002, Revision 02, dated March 
30, 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 Boeing Alert Service 
Bulletin DC9-27A362, dated February 11, 2000; Boeing Alert Service 
Bulletin MD90-27A034, dated February 11, 2000; and Boeing Alert 
Service Bulletin 717-27A0002, dated February 11, 2000; was approved 
previously by the Director of the Federal Register as of March 6, 
2000 (65 FR 10379, February 28, 2000).
    (3) Copies may be obtained from The Boeing Company, Long Beach 
Division, 3855 Lakewood Boulevard, Long Beach, California 90846, 
Attention: Technical Publications Business Administration, Dept. C1-
L52 (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.

Effective Date

    (g) This amendment becomes effective on August 23, 2000.

    Issued in Renton, Washington, on July 28, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-19671 Filed 8-7-00; 8:45 am]
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