[Federal Register Volume 63, Number 146 (Thursday, July 30, 1998)]
[Rules and Regulations]
[Pages 40640-40643]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-19924]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-212-AD; Amendment 39-10676; AD 98-16-01]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain McDonnell Douglas Model MD-11 series 
airplanes. This action requires repetitive inspections to measure for 
free play (wear on nut assembly) of the horizontal stabilizer actuator 
assembly, and corrective actions, if necessary. This amendment is 
prompted by reports of wear of the horizontal stabilizer actuator 
assembly due to a jackscrew surface finish that was manufactured 
incorrectly. The actions specified in this AD are intended to prevent 
excessive free play and wear of the horizontal stabilizer actuator 
assembly, which could result in a free-floating horizontal stabilizer, 
and consequent loss of aircraft pitch control.

DATES: Effective August 14, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 14, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before September 28, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-212-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The service information referenced in this AD may be obtained from 
The Boeing Company, Douglas Products

[[Page 40641]]

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; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: David Y. J. Hsu, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5323; fax (562) 
627-5210.

SUPPLEMENTARY INFORMATION: The FAA has received numerous reports of the 
actuator nut assembly of the horizontal stabilizer prematurely wearing 
out on McDonnell Douglas Model MD-11 series airplanes. In one of these 
incidents, the nut assembly had completely worn through. The cause of 
such wear and resultant excessive free play has been attributed to a 
jackscrew surface finish that was out of design specification 
tolerance, as a result of a manufacturing process error. If not 
corrected, this condition, in conjunction with a failure of the 
opposite side jackscrew assembly, could result in a free-floating 
horizontal stabilizer, and consequent loss of aircraft pitch control.

Explanation of Relevant Service Information

    The FAA has reviewed and approved McDonnell Douglas Service 
Bulletin MD11-27-067, dated July 31, 1997; McDonnell Douglas Service 
Bulletin MD11-27-067, Revision 01, dated February 24, 1998; McDonnell 
Douglas Alert Service Bulletin MD11-27A067, Revision 02, dated May 18, 
1998; and McDonnell Douglas Alert Service Bulletin MD11-27A067, 
Revision 03, dated June 9, 1998. These service bulletins describe 
procedures for repetitive inspections to measure for free play (wear on 
nut assembly) of the horizontal stabilizer actuator assembly, and 
corrective actions, if necessary. These corrective actions include 
replacing the actuator assembly with a new actuator assembly, repairing 
the jackscrew assembly, and replacing the nut assembly with a new nut 
assembly. Accomplishment of the actions specified in these service 
bulletins is intended to adequately address the identified unsafe 
condition.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD is 
being issued to prevent excessive free play and wear of the horizontal 
stabilizer actuator assembly, which could result in a free-floating 
horizontal stabilizer, and consequent loss of aircraft pitch control. 
The actions are required to be accomplished in accordance with the 
service bulletins described previously, except as discussed below. This 
AD also requires that operators submit a report of the results of the 
initial inspection required by this AD to the FAA.

Differences Between Proposed Rule and Service Bulletins

    Operators should note that although the service bulletins specify 
that the manufacturer may be contacted for disposition of certain 
repair/modification conditions, this AD requires the repair of those 
conditions to be accomplished in accordance with a method approved by 
the FAA.

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 98-NM-212-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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:

[[Page 40642]]

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:

98-16-01  McDonnell Douglas: Amendment 39-10676. Docket 98-NM-212-
AD.

    Applicability: Model MD-11 series airplanes, as listed in 
McDonnell Douglas MD-11 Alert Service Bulletin MD11-27A067, Revision 
03, dated June 9, 1998; 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 (i) 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 excessive play and wear on the horizontal stabilizer 
actuator assembly, which could result in a free-floating horizontal 
stabilizer, and consequent loss of aircraft pitch control, 
accomplish the following:

    Note 2: Where there are differences between the service 
bulletins and the AD, the AD prevails.

    (a) Within 30 days after the effective date of this AD: Perform 
an inspection to measure for free play (wear on nut assembly) of the 
horizontal stabilizer actuator assembly, left and right sides, in 
accordance with any of the following McDonnell Douglas service 
bulletins:
    <bullet> McDonnell Douglas Service Bulletin MD11-27-067, dated 
July 31, 1997;
    <bullet> McDonnell Douglas Service Bulletin MD11-27-067, 
Revision 01, dated February 24, 1998;
    <bullet> McDonnell Douglas Alert Service Bulletin MD11-27A067, 
Revision 02, dated May 18, 1998; or
    <bullet> McDonnell Douglas Alert Service Bulletin MD11-27A067, 
Revision 03, dated June 9, 1998.
    (b) For airplanes that have accumulated 2,000 or more total 
landings at the time of accomplishment of the inspection required by 
paragraph (a) of this AD: If any wear is detected during the 
inspection required by paragraph (a) of this AD, and it is less than 
or within the limits identified in Table 1, Condition 1, of the Work 
Instructions of any service bulletin listed in paragraph (a) of this 
AD, no further action is required by this AD.
    (c) For airplanes that have accumulated less than 2,000 total 
landings at the time of accomplishment of the inspection required by 
paragraph (a) of this AD: If any wear is detected during any 
inspection required by paragraph (a) of this AD, and it is less than 
or within the limits identified in Table 1, Condition 1, of the Work 
Instructions of any service bulletin listed in paragraph (a) of this 
AD, repeat the inspection required by paragraph (a) of this AD prior 
to the accumulation of 2,400 total landings.
    (d) Condition 2. If any wear is detected during any inspection 
required by paragraph (a) or (c) of this AD, and it is within the 
limits identified in Table 1, Condition 2, of the Work Instructions 
of any service bulletin listed in paragraph (a) of this AD, within 
500 landings following accomplishment of the inspection required by 
paragraph (a) of this AD, accomplish paragraph (d)(1), (d)(2), 
(d)(3), (d)(4), or (d)(5) of this AD.
    (1) Option 1. Replace the actuator assembly with a new actuator 
assembly, in accordance with any service bulletin listed in 
paragraph (a) of this AD.
    (2) Option 2. Repair the jackscrew assembly of the horizontal 
stabilizer and install it utilizing the existing nut assembly in 
accordance with either:
    (i) A method approved by the Manager, Los Angeles Aircraft 
Certification Office (ACO), FAA, Transport Airplane Directorate; or
    (ii) Option 2, Procedure 2, of the Work Instructions of any 
service bulletin listed in paragraph (a) of this AD.
    (3) Option 3. Repair the jackscrew assembly of the horizontal 
stabilizer and install it utilizing a new nut assembly in accordance 
with either:
    (i) A method approved by the Manager, Los Angeles ACO; or
    (ii) Option 3, Procedure 2, of the Work Instructions of any 
service bulletin listed in paragraph (a) of this AD.
    (4) Option 4. Replace the nut assembly with a new nut assembly, 
in accordance with any service bulletin listed in paragraph (a) of 
this AD. Within 1,500 landings following accomplishment of the 
replacement, repeat the inspection required by paragraph (a) of this 
AD.
    (5) Option 5. Repeat the inspection required by paragraph (a) of 
this AD thereafter at intervals not to exceed 500 landings.
    (e) Condition 3. If any wear is detected during the inspection 
required by paragraph (a) or (c) of this AD, and it is within the 
limits identified in Table 1, Condition 3, of the Work Instructions 
of any service bulletin listed in paragraph (a) of this AD, within 
250 landings following accomplishment of the inspection required by 
paragraph (a) of this AD, accomplish either paragraph (e)(1), 
(e)(2), (e)(3), (e)(4), or (e)(5) of this AD.
    (1) Option 1. Replace the actuator assembly with a new actuator 
assembly, in accordance with any service bulletin listed in 
paragraph (a) of this AD.
    (2) Option 2. Repair the jackscrew assembly of the horizontal 
stabilizer and install it utilizing the existing nut assembly in 
accordance with either:
    (i) A method approved by the Manager, Los Angeles ACO; or
    (ii) Option 2, Procedure 2, of the Work Instructions of any 
service bulletin listed in paragraph (a) of this AD.
    (3) Option 3. Repair the jackscrew assembly of the horizontal 
stabilizer and install it utilizing a new nut assembly in accordance 
with either:
    (i) A method approved by the Manager, Los Angeles ACO; or
    (ii) Option 3, Procedure 2, of the Work Instructions of any 
service bulletin listed in paragraph (a) of this AD.
    (4) Option 4. Replace the nut assembly with a new nut assembly, 
in accordance with any service bulletin listed in paragraph (a) of 
this AD. Within 1,500 landings following accomplishment of the 
replacement, repeat the inspection required by paragraph (a) of this 
AD.
    (5) Option 5. Repeat the inspection required by paragraph (a) of 
this AD thereafter at intervals not to exceed 250 landings.
    (f) Condition 4. If any wear is detected during the inspection 
required by paragraph (a) or (c) of this AD, and it is within the 
limits identified in Table 1, Condition 4, of the Work Instructions 
of any service bulletin listed in paragraph (a) of this AD, within 
100 landings following accomplishment of the inspection required by 
paragraph (a) of this AD, accomplish paragraph (f)(1), (f)(2), or 
(f)(3) of this AD.
    (1) Option 1. Replace the actuator assembly with a new actuator 
assembly, in accordance with any service bulletin listed in 
paragraph (a) of this AD.
    (2) Option 3. Repair the jackscrew assembly of the horizontal 
stabilizer and install it utilizing a new nut assembly in accordance 
with either:
    (i) A method approved by the Manger, Los Angeles ACO; or
    (ii) Option 3, Procedure 2, of the Work Instructions of any 
service bulletin listed in paragraph (a) of this AD.
    (3) Option 4. Replace the nut assembly with a new nut assembly, 
in accordance with any service bulletin listed in paragraph (a) of 
this AD.
    (i) For airplanes that have accumulated 1,500 or more landings 
at the time of the last inspection: Within 1,500 landings following 
accomplishment of the replacement, repeat the inspection required by 
paragraph (a) of this AD.
    (ii) For airplanes that have accumulated less than 1,500 
landings at the time of the last inspection: Following 
accomplishment of the replacement, repeat the inspection required by 
paragraph (a) of this AD within the number of landings accumulated 
at the time of the last inspection.
    (g) If any wear is detected during the inspection required by 
paragraph (a) or (c) of this AD, and it exceeds the limits 
identified in Table 1, Condition 4, of the Work Instructions of any 
service bulletin listed in paragraph (a) of this AD, prior to 
further flight, repair in accordance with a method approved by the 
Manager, Los Angeles ACO.
    (h) Within 10 days after accomplishment of the initial 
inspection required by paragraph (a) of this AD, submit a report of 
the inspection results (positive or negative) to the Manager, Los 
Angeles Aircraft Certification

[[Page 40643]]

Office, FAA, Transport Airplane Directorate, 3960 Paramount 
Boulevard, Lakewood, California 90712; 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.
    (i) 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. 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

    (j) 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.
    (k) Except as provided by paragraphs (d)(2)(i), (e)(2)(i), and 
(g) of this AD, the actions shall be done in accordance with the 
following service bulletins:
    <bullet> McDonnell Douglas Service Bulletin MD11-27-067, dated 
July 31, 1997;
    <bullet> McDonnell Douglas Service Bulletin MD11-27-067, 
Revision 01, dated February 24, 1998;
    <bullet> McDonnell Douglas Alert Service Bulletin MD11-27A067, 
Revision 02, dated May 18, 1998; or
    <bullet> McDonnell Douglas Alert Service Bulletin MD11-27A067, 
Revision 03, dated June 9, 1998.

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 The Boeing Company, Douglas Products 
Division, 3855 Lakewood Boulevard, Long Beach, California 90846, 
Attention: Technical Publications Business Administration, Dept. C1-
151 (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.

    (l) This amendment becomes effective on August 14, 1998.

    Issued in Renton, Washington, on July 21, 1998.
S. R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-19924 Filed 7-29-98; 8:45 am]
BILLING CODE 4910-13-P