[Federal Register Volume 61, Number 146 (Monday, July 29, 1996)]
[Rules and Regulations]
[Pages 39312-39314]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-19012]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-39-AD; Amendment 39-9701; AD 96-16-01]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10 and 
DC-10-15 Series 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 DC-10-10 and DC-10-15 
series airplanes, that 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 a report 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 main landing gear (MLG) as a result of 
chrome flaking and severe corrosion on the bearing surface and in the 
mechanical fuse.

DATES: Effective September 3, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 3, 1996.

ADDRESSES: The service information referenced in this AD may be 
obtained 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, Transport Airplane Directorate, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
California; or at the Office of the Federal

[[Page 39313]]

Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Maureen Moreland or Ron Atmur, 
Aerospace Engineers, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
California 90712; telephone (310) 627-5238 or (310) 627-5224; 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 
DC-10-10 and DC-10-15 series airplanes was published in the Federal 
Register on April 10, 1996 (61 FR 15904). That action proposed to 
require a visual 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 two comments received.
    Both commenters support the proposed rule.

Conclusion

    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 as proposed.

Cost Impact

    There are approximately 139 McDonnell Douglas Model DC-10-10 and 
DC-10-15 series airplanes of the affected design in the worldwide 
fleet. The FAA estimates that 121 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 $7,260, 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.

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.
    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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13   [Amended]

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

96-16-01  McDonnell Douglas: Amendment 39-9701. Docket 96-NM-39-AD.

    Applicability: Model DC-10-10 and DC-10-15 series airplanes, as 
listed in McDonnell Douglas Service Bulletin DC10-32-241, dated 
December 13, 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 request approval for an 
alternative method of compliance in accordance with paragraph (c) 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 premature failure of the trunnion bolts and 
subsequent collapse of the main landing gear (MLG), accomplish the 
following:
    (a) For airplanes on which the forward trunnion bolts, part 
number (P/N) ARG7557-501, 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 or 
verification required by paragraph (a)(1) or (a)(2), respectively, 
of this AD: Within 18 months after the effective date of this AD, 
accomplish either paragraph (a)(1) or (a)(2) of this AD, in 
accordance with McDonnell Douglas Service Bulletin DC10-32-241, 
dated December 13, 1995.
    (1) 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 (a)(1)(ii)(A) or (a)(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 Component Maintenance Manual (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.
    (B) Replace the trunnion bolt with a serviceable part in 
accordance with the service bulletin. -
    (2) Verify whether the forward trunnion bolts, P/N ARG7557-501, 
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 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

[[Page 39314]]

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 
(a)(1)(ii)(A) or (a)(1)(ii)(B) of this AD in accordance with the 
service bulletin.
    (b) For airplanes other than those identified in paragraph (a) 
of this AD: Within 18 months after the effective date of this AD, 
verify whether the forward trunnion bolts, P/N ARG7557-501, 
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.
    (1) 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.
    (2) 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 
(b)(2)(i) or (b)(2)(ii) of this AD in accordance with McDonnell 
Douglas Service Bulletin DC10-32-241, dated December 13, 1995. -
    (i) Remove the chrome plating on the trunnion bolt in accordance 
with the service bulletin; replace the plating in accordance with 
the Component Maintenance Manual (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 
ACO, to make such a finding; and reinstall the reworked bolt in 
accordance with the service bulletin. Or -
    (ii) Replace the trunnion bolt with a serviceable part in 
accordance with the service bulletin. -
    (c) 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.

    -(d) 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. -
    (e) The actions shall be done in accordance with McDonnell 
Douglas Service Bulletin DC10-32-241, dated December 13, 1995. 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, 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. -
    (f) This amendment becomes effective on September 3, 1996.

    Issued in Renton, Washington, on July 22, 1996.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-19012 Filed 7-26-96; 8:45 am]
BILLING CODE 4910-13-P