[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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:
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; or
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:
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; or
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