[Federal Register Volume 60, Number 161 (Monday, August 21, 1995)]
[Proposed Rules]
[Pages 43417-43420]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-20631]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-39-AD]


Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
Airplanes and Model DC-10-30, DC-10-40, and KC-10A (Military) Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
MD-11 series airplanes and Model DC-10-30, DC-10-40, and KC-10A 
(military) airplanes. For Model MD-11 series airplanes, this proposal 
would require an inspection to determine the serial number of the 
forward trunnion bolts on the main landing gear (MLG), and rework or 
replacement of the bolts, if necessary. For Model DC-10-30, DC-

[[Page 43418]]
10-40, and KC-10A (military) airplanes, this proposal would require an 
inspection for evidence of missing chrome and for corrosion on the 
chrome surfaces, or verification that the forward trunnion bolts have 
been chrome plated in a specific manner; and rework or replacement of 
the bolts, if necessary. This proposal is prompted by reports of chrome 
flaking on the bearing surface of the trunnion bolts due to improper 
cleaning of the base material prior to chrome plating. The actions 
specified by the proposed AD are intended to prevent premature failure 
of the trunnion bolts and subsequent collapse of the MLG as a result of 
severe corrosion on the bearing surface and in the mechanical fuse due 
to chrome flaking.

DATES: Comments must be received by October 17, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-39-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 McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, 
California 90801-1771, Attention: Business Unit Manager, Technical 
Administrative Support, Dept. L51, M.C. 2-98. 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: Maureen Moreland, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712; telephone (310) 627-5238; fax (310) 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 95-NM-39-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-103, Attention: Rules 
Docket No. 95-NM-39-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of chrome flaking on the bearing 
surface of the forward trunnion bolts installed on the main landing 
gear (MLG) of McDonnell Douglas Model MD-11 series airplanes and Model 
DC-10-30 and -40 airplanes. Such chrome flaking has resulted in severe 
corrosion on the bearing surface and in the mechanical fuse. This 
condition has been attributed to improper cleaning of the base material 
prior to chrome plating. This condition, if not corrected, could result 
in premature failure of the trunnion bolts and subsequent collapse of 
the MLG.
    The FAA has reviewed and approved McDonnell Douglas MD-11 Service 
Bulletin 32-45, Revision 1, dated May 1, 1995, which describes 
procedures for a visual inspection of Model MD-11 series airplanes to 
determine the serial number of the forward trunnion bolts, part number 
ARG7558-503 or ARG7558-505, on the right and left MLG's. The service 
bulletin also provides procedures for rework or replacement of the 
bolts with serviceable parts, if necessary. Accomplishment of the 
rework or replacement will minimize the possibility of chrome flaking 
on the forward trunnion bolts.
    The FAA also has reviewed and approved McDonnell Douglas Service 
Bulletin DC10-32-239, Revision 1, dated June 6, 1995, which describes 
procedures for a visual inspection of Model DC-10-30, DC-10-40, and KC-
10A (military) airplanes for evidence of missing chrome and for 
corrosion on the chrome surfaces of the trunnion bolts, or verification 
that the forward trunnion bolts have been chrome plated in a specific 
manner. The service bulletin also provides procedures for certain 
rework or replacement of the bolts with serviceable parts, if 
necessary.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, this 
proposal would require the following:
    For Model MD-11 series airplanes, this proposal would require an 
inspection to determine the serial number of the forward trunnion 
bolts, and rework or replacement of the bolts with serviceable parts, 
if necessary. The actions would be required to be accomplished in 
accordance with the MD-11 service bulletin described previously.
    For Model DC-10-30, DC-10-40, and KC-10A (military) airplanes, this 
proposal would require an inspection for evidence of missing chrome and 
for corrosion on the chrome surfaces, or verification that the forward 
trunnion bolts have been chrome plated in a specific manner; and rework 
or replacement of the bolts with serviceable parts, if necessary. A 
portion of the rework would be required to be accomplished in 
accordance with the Component Maintenance Manual or a method approved 
by the FAA. Other corrective actions would be required to be 
accomplished in accordance with the DC-10 service bulletin described 
previously.
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that provides for such approvals. A note has 

[[Page 43419]]
been included in this notice to clarify this long-standing requirement.
    There are approximately 414 Model MD-11 series airplanes and Model 
DC-10-30, DC-10-40, and KC-10A (military) airplanes of the affected 
design in the worldwide fleet. The FAA estimates that 196 airplanes of 
U.S. registry would be affected by this proposed AD, that it would take 
approximately 1 work hour per airplane to accomplish the proposed 
actions, and that the average labor rate is $60 per work hour. Based on 
these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $11,760, or $60 per airplane.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

McDonnell Douglas: Docket 95-NM-39-AD.

    Applicability: Model MD-11 series airplanes, as listed in 
McDonnell Douglas MD-11 Service Bulletin 32-45, Revision 1, dated 
May 1, 1995; and Model DC-10-30, DC-10-40, and KC-10A (military) 
airplanes, as listed in McDonnell Douglas DC-10 Service Bulletin 
DC10-32-239, Revision 1, dated June 6, 1995; 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 use the authority 
provided in paragraph (e) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent premature failure of the trunnion bolts and 
subsequent collapse of the main landing gear (MLG), accomplish the 
following:
    (a) For Model MD-11 series airplanes: Within 18 months after the 
effective date of this AD, perform a visual inspection to determine 
the serial number of the forward trunnion bolts, part number 
ARG7558-503 or ARG7558-505, on the right and left MLG's, in 
accordance with McDonnell Douglas MD-11 Service Bulletin 32-45, 
Revision 1, dated May 1, 1995.
    (1) If the serial number of the trunnion bolt is STR0217, 
STR0232, STR0237 through STR0242 inclusive, or STR0244 through 
STR0284 inclusive; or if the trunnion bolt has been chrome plated in 
accordance with the Component Maintenance Manual (CMM), Chapter 20-
10-02, Revision 31, dated September 1, 1991, since original 
manufacture: No further action is required by this AD.
    (2) For trunnion bolts other than those identified in paragraph 
(a)(1) of this AD: Prior to further flight, remove the chrome 
plating on the trunnion bolt, replace the plating, and reinstall the 
reworked trunnion bolt; or replace the trunnion bolt with a 
serviceable part; in accordance with McDonnell Douglas MD-11 Service 
Bulletin 32-45, Revision 1, dated May 1, 1995.
    (b) For Model MD-11 series airplanes: As of the effective date 
of this AD, no person shall install a trunnion bolt having part 
number ARG7558-503 or ARG7558-505 on the right or left MLG of any 
airplane unless the bolt meets the condition specified in either 
paragraph (b)(1), (b)(2), or (b)(3) of this AD.
    (1) The trunnion bolt bears the serial number STR0217, STR0232, 
STR0237 through STR0242 inclusive, or STR0244 through STR0284 
inclusive; or
    (2) The trunnion bolt has been chrome plated in accordance with 
the CMM, Chapter 20-10-02, Revision 31, dated September 1, 1991, 
since original manufacture; or
    (3) The trunnion bolt has been reworked in accordance with 
McDonnell Douglas MD-11 Service Bulletin 32-45, Revision 1, dated 
May 1, 1995.
    (c) For Model DC-10-30, DC-10-40, and KC-10A (military) 
airplanes: Within 18 months after the effective date of this AD, 
accomplish either paragraph (c)(1) or (c)(2) of this AD, as 
applicable, in accordance with McDonnell Douglas DC-10 Service 
Bulletin DC10-32-239, Revision 1, dated June 6, 1995.
    (1) For airplanes on which the forward trunnion bolts, part 
number (P/N) ARG7558-501, installed on the left and right MLG's, 
have accumulated 6,000 or more total flight hours or 2,000 or more 
total flight cycles as of the date of the inspection: Remove the 
bolts and perform a visual inspection for evidence of missing chrome 
and for corrosion on the chrome surfaces, in accordance with the 
service bulletin.
    (i) If no evidence of missing chrome and no corrosion on the 
chrome surfaces are found, no further action is required by this AD.
    (ii) If any evidence of missing chrome or any corrosion on the 
chrome surfaces is found, prior to further flight, accomplish either 
paragraph (c)(1)(ii)(A) or (c)(1)(ii)(B) of this AD.
    (A) Remove the chrome plating on the trunnion bolt in accordance 
with the service bulletin; replace the plating in accordance with 
the CMM, Chapter 20-10-02, Revision 31, dated September 1, 1991, or 
in accordance with a method approved by a McDonnell Douglas 
Designated Engineering Representative (DER) who has been given a 
special delegation by the Manager, Los Angeles Aircraft 
Certification Office (ACO), FAA, Transport Airplane Directorate, to 
make such a finding; and reinstall the reworked bolt in accordance 
with the service bulletin. Or
    (B) Replace the trunnion bolt with a serviceable part in 
accordance with the service bulletin.
    (2) For airplanes other than those identified in paragraph 
(c)(1) of this AD: Verify whether the forward trunnion bolts, part 
number (P/N) ARG7558-501, installed on the left and right MLG's, 
have been chrome plated since original manufacture, in accordance 
with the CMM, Chapter 20-10-02, Revision 31, dated September 1, 
1991, or 

[[Page 43420]]
in accordance with a method approved by a McDonnell Douglas DER who has 
been given a special delegation by the Manager, Los Angeles ACO, to 
make such a finding.
    (i) If the bolts have been chrome plated since original 
manufacture, in accordance with the CMM, Chapter 20-10-02, Revision 
31, dated September 1, 1991, or in accordance with a method approved 
by a McDonnell Douglas DER who has been given a special delegation 
by the Manager, Los Angeles ACO, to make such a finding: No further 
action is required by this AD.
    (ii) If any bolt has not been chrome plated since original 
manufacture, in accordance with the CMM, Chapter 20-10-02, Revision 
31, dated September 1, 1991, or in accordance with a method approved 
by a McDonnell Douglas DER who has been given a special delegation 
by the Manager, Los Angeles ACO, to make such a finding: Prior to 
further flight, accomplish the requirements of either paragraph 
(c)(1)(ii)(A) or (c)(1)(ii)(B) of this AD in accordance with the 
service bulletin.
    (d) For Model DC-10-30, DC-10-40, and KC-10A (military) 
airplanes: As of the effective date of this AD, no person shall 
install a trunnion bolt, having part number ARG7558-501, on the 
right or left MLG of any airplane unless the bolt meets the 
condition specified in either paragraph (d)(1), (d)(2), (d)(3), or 
(d)(4) of this AD.
    (1) The trunnion bolt has been chrome plated in accordance with 
the CMM, Chapter 20-10-02, Revision 31, dated September 1, 1991, 
since original manufacture; or
    (2) The trunnion bolt has been chrome plated in accordance with 
a method approved by a McDonnell Douglas DER who has been given a 
special delegation by the Manager, Los Angeles ACO, to make such 
findings; or
    (3) The bolt has been reworked in accordance with McDonnell 
Douglas DC-10 Service Bulletin DC10-32-239, Revision 1, dated June 
6, 1995; or
    (4) The bolt has accumulated 6,000 or more total flight hours or 
2,000 or more total flight cycles and has been visually inspected 
for evidence of missing chrome and for corrosion on the chrome 
surfaces, in accordance with McDonnell Douglas DC-10 Service 
Bulletin DC10-32-239, Revision 1, dated June 6, 1995, and no 
evidence of missing chrome or corrosion on the chrome surfaces was 
found.
    (e) 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 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

    (f) 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.

    Issued in Renton, Washington, on August 15, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-20631 Filed 8-18-95; 8:45 am]
BILLING CODE 4910-13-U