[Federal Register Volume 61, Number 29 (Monday, February 12, 1996)]
[Rules and Regulations]
[Pages 5281-5284]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-1518]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-39-AD; Amendment 39-9502; AD 96-03-05]


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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
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, the AD requires 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-10-40, and KC-10A (military) 
airplanes, the AD requires 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 amendment 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 this 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: Effective March 13, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 13, 1996.

ADDRESSES: The service information referenced in this AD may be 
obtained 

[[Page 5282]]
from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long 
Beach, California 90846, Attention: Technical Publications Business 
Administration, Department C1-L51 (2-60). This information may be 
examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue SW., Renton, 
Washington; or at the FAA, Los Angeles Aircraft Certification Office, 
Transport Airplane Directorate, 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: 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an 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 was published in the Federal Register on August 
21, 1995 (60 FR 43417). For Model MD-11 series airplanes, that action 
proposed to 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-10-40, 
and KC-10A (military) airplanes, that action proposed to 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter supports the proposed rule.
    Three commenters request that the proposed rule be revised to 
specify that unmodified parts may not be installed as of 18 months 
after the effective date of the AD. [Paragraphs (b) and (d) of the 
proposed rule specify currently that unmodified parts may not be 
installed as of the effective date of the AD.] The commenters point out 
that, although these parts that are currently installed on an airplane 
would be allowed to continued in service for 18 months prior to 
modification, those same parts currently in stock as spares would not 
be permitted to be installed prior to modification, regardless of the 
cumulative time on the spare part or the circumstances under which an 
operator may need temporary use of unmodified spare parts. The 
commenters indicate that the availability of adequate numbers of 
replacement or modified parts is an issue in meeting the compliance 
date; in such cases, there is often a need to take low-time or zero-
time spare parts and rotate them temporarily into installed positions 
so that the intent of the AD can be accomplished without disrupting 
service to the traveling and shipping public. Along this same line, one 
commenter asks whether the manufacturer has ensured that adequate 
quantities of the ARG7558 bolts are available for procurement in order 
to support ``on condition'' replacements necessary as a result of 
accomplishing the intent of the proposed rule. This commenter suggests 
that, if such bolts are not available, the FAA should delay 
implementation of the rule until an adequate stock exists.
    The FAA concurs with the commenters' request. At the time the 
proposed rule was issued, the FAA had obtained information indicating 
that sufficient spare parts would be available to support a requirement 
that trunnion bolts not meeting the requirements of the AD not be 
installed on an airplane. However, since the issuance of the proposed 
rule, the manufacturer has advised the FAA that, due to delays in the 
manufacture of new trunnion bolts, only a limited number of replacement 
trunnion bolts would be available for use as spares at the time the AD 
becomes effective. The manufacturer has advised further that sufficient 
trunnion bolts will be available to support an 18-month compliance 
time. Accordingly, the FAA has removed paragraphs (b) and (d) from the 
final rule.
    One commenter requests that installation of a trunnion bolt having 
part number ARG7558-507 be considered terminating action for the 
requirements of paragraph (c) of the proposed rule. The FAA concurs. 
Subsequent to the issuance of the proposed rule, the FAA determined 
that trunnion bolts having part numbers ARG7558-507 (for Model DC-10 
series airplanes), ARG7558-509 (for Model MD-11 series airplanes), and 
ARG7008-511 (for Model MD-11 series airplanes) are superseding parts 
that have been manufactured using an improved process that eliminates 
the problem of severe corrosion on the bearing surface and mechanical 
fuse due to chrome flaking. These parts have been plated with nickel 
prior to being plated with chrome. In light of this information, the 
FAA has added new paragraphs (b) and (d) to this final rule to specify 
that installation of a trunnion bolt having part number ARG7558-507 on 
the MLG of Model DC-10 series airplanes, or part number ARG7558-509 or 
ARG7008-511 on the MLG of Model MD-11 series airplanes, constitutes 
terminating action for the requirements of this AD for that MLG.
    One commenter asks if the FAA is considering including a provision 
in the AD to specify that visual inspections accomplished prior to the 
effective date of the final rule satisfy the requirement of paragraph 
(c) of the proposed AD. The FAA finds that no change to the final rule 
is necessary to provide such a provision. The AD contains a statement 
that reads, ``Compliance: Required as indicated, unless accomplished 
previously.'' That statement provides credit for actions accomplished 
in accordance with the requirements of the AD prior to the effective 
date of the final rule.
    One commenter requests that the economic impact information that 
was presented in the preamble to the notice be revised to increase the 
number of estimated necessary work hours from 1 to 33.5. The commenter 
states that when defective bolts are found the time required to 
accomplish the action proposed by this AD is approximately 33.5 work 
hours. The FAA does not concur with the commenter's request. The 
economic impact information presented is limited only to the cost of 
actions actually required by the rule (e.g., the inspection of the 
trunnion bolts). It does not consider the costs of ``on condition'' 
actions, e.g., ``rework or replacement of the bolts, if necessary,'' 
since those actions would be required to be accomplished, regardless of 
AD direction, in order to correct an unsafe condition identified in an 
airplane and to ensure operation of that airplane in an airworthy 
condition, as required by the Federal Aviation Regulations.
    Subsequent to issuance of the proposal, McDonnell Douglas issued 
DC-10 Service Bulletin DC10-32-239, Revision 2, dated January 8, 1996. 
This revision is essentially identical to Revision 1, which was cited 
in the proposal as the appropriate source of service information; 
Revision 2 differs only in that it clarifies certain work instructions. 
The FAA has revised the final rule to include Revision 2 of the service 
bulletin as an additional source of service information. 

[[Page 5283]]

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    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 will be affected by this AD, that it will take 
approximately 1 work hour per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Based on 
these figures, the cost impact of the AD on U.S. operators is estimated 
to be $11,760, or $60 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.
    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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

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

96-03-05  McDonnell Douglas: Amendment 39-9502. 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, and Revision 2, dated 
January 8, 1996; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 (P/N) 
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: Installation of a trunnion 
bolt having P/N ARG7558-509 or ARG7008-511 on the MLG constitutes 
terminating action for the requirements of this AD for that MLG.
    (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, or Revision 2, 
dated January 8, 1996.
    (1) For airplanes on which the forward trunnion bolts, 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, 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 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 

[[Page 5284]]
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: Installation of a trunnion bolt having P/N ARG7558-507 on 
the MLG constitutes terminating action for the requirements of this 
AD for that MLG.
    (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.
    (g) The actions shall be done in accordance with McDonnell 
Douglas MD-11 Service Bulletin 32-45, Revision 1, dated May 1, 1995; 
McDonnell Douglas DC-10 Service Bulletin DC10-32-239, Revision 1, 
dated June 6, 1995; and McDonnell Douglas DC-10 Service Bulletin 
DC10-32-239, Revision 2, dated January 8, 1996. 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 McDonnell Douglas Corporation, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Technical 
Publications Business Administration, Department C1-L51 (2-60). 
Copies may be inspected at the FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los 
Angeles Aircraft Certification Office, Transport Airplane 
Directorate, 3960 Paramount Boulevard, Lakewood, California; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.
    (h) This amendment becomes effective on March 13, 1996.

    Issued in Renton, Washington, on January 23, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-1518 Filed 2-9-96;8:45am]
BILLING CODE 4910-13-U