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

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.

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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]

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