[Federal Register Volume 66, Number 129 (Thursday, July 5, 2001)]
[Rules and Regulations]
[Pages 35371-35373]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-16739]



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  Federal Register / Vol. 66, No. 129 / Thursday, July 5, 2001 / Rules 
and Regulations  

[[Page 35371]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-396-AD; Amendment 39-12304; AD 2001-13-22]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, -15, 
-30, -30F (KC-10A Military), and -40 Series Airplanes; and Model MD-10-
10F and MD-10-30F Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, 
-30F (KC-10A military), and -40 series airplanes; and Model MD-10-10F 
and MD-10-30F series airplanes, that currently requires, among other 
actions, performing repetitive ultrasonic inspections of the attaching 
bolts on the inboard and outboard support on the inboard and outboard 
flap assembly to detect failed bolts, or verifying the torque of the 
attaching bolts on the inboard support on the outboard flap; and 
follow-on actions. This amendment, among other actions, adds a 
requirement to verify the torque of the attaching bolts on the outboard 
support on the inboard and outboard flaps, and allows repetitive torque 
verifications. This amendment is prompted by a review that revealed 
inadvertent omission of a requirement. The actions specified by this AD 
are intended to prevent in-flight loss of inboard and outboard flap 
assemblies due to failure of H-11 attaching bolts, which could result 
in reduced controllability of the airplane.

DATES: Effective August 9, 2001.
    The incorporation by reference of certain publications listed in 
the regulations has been approved previously by the Director of the 
Federal Register as of September 25, 2000 (65 FR 50621, August 21, 
2000).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data 
and Service Management, Dept. C1-L5A (D800-0024). 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, 
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: Ron Atmur, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5224; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-16-10, 
amendment 39-11866 (65 FR 50621, August 21, 2000), which is applicable 
to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A 
military), and -40 series airplanes; and Model MD-10-10F and MD-10-30F 
series airplanes, was published in the Federal Register on February 21, 
2001 (66 FR 10970). The action proposed to continue to require 
repetitive ultrasonic inspections of the attaching bolts on the inboard 
and outboard support on the inboard and outboard flap assembly to 
detect failed bolts, or verifying the torque of the attaching bolts on 
the inboard support on the outboard flap; and follow-on actions. The 
action also proposed to continue to require replacement of all 
attaching bolts with bolts made from Inconel, which would constitute 
terminating action for the repetitive inspection requirements. In 
addition, the action proposed to add a requirement to verify the torque 
of the attaching bolts on the outboard support on the inboard and 
outboard flaps, and to allow repetitive torque verification in lieu of 
the repetitive ultrasonic inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.

Conclusion

    After careful review of the available data, including the comment 
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 412 McDonnell Douglas Model DC-10-10, -15, 
-30, -30F (KC-10A military), and -40 series airplanes; and Model MD-10-
10F and MD-10-30F series airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 244 airplanes of U.S. registry 
will be affected by this AD.
    The inspection/torque verification that is currently required by AD 
2000-16-10, and retained in this new AD, takes approximately 2 to 8 
work hours per airplane to accomplish, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of the currently 
required actions on U.S. operators is estimated to be between $29,280 
and $117,120, or between $120 and $480 per airplane, per inspection 
cycle.
    The bolt replacement that is currently required by AD 2000-16-10, 
and retained in this new AD, takes approximately 288 work hours per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Required parts will cost approximately $2,987 per airplane. Based on 
these figures, the cost impact of the currently required replacement on 
U.S. operators is estimated to be $4,945,148, or $20,267 per airplane.
    The cost impact of the new torque verification required by this AD 
is included in the cost estimate above for the inspection/torque 
verification.
    The cost impact figures discussed above are 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

[[Page 35372]]

were not adopted. The cost impact figures discussed in AD rulemaking 
actions represent only the time necessary to perform the specific 
actions actually required by the AD. These figures typically do not 
include incidental costs, such as the time required to gain access and 
close up, planning time, or time necessitated by other administrative 
actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 removing amendment 39-11866 (65 FR 
50621, August 21, 2000), and by adding a new airworthiness directive 
(AD), amendment 39-12304, to read as follows:

2001-13-22  McDonnell Douglas: Amendment 39-12304. Docket 2000-NM-
396-AD. Supersedes AD 2000-16-10, Amendment 39-11866.

    Applicability: Model DC-10-10, -15, -30, -30F (KC-10A military), 
and -40 series airplanes; and Model MD-10-10F and MD-10-30F series 
airplanes; as listed in McDonnell Douglas Alert Service Bulletin 
DC10-57A143, dated December 20, 1999; 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 (e)(1) 
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 in-flight loss of inboard and outboard flap 
assemblies due to failure of H-11 attaching bolts, which could 
result in reduced controllability of the airplane, accomplish the 
following:

Inspection or Torque Verification, and Corrective Actions, if Necessary

    (a) Within 2 months after September 25, 2000, (the effective 
date of AD 2000-16-10, amendment 39-11866), do an ultrasonic 
inspection of the attaching bolts on the inboard and outboard 
support on the outboard flap assembly and on the outboard support on 
the inboard flap assembly to detect failed bolts, or verify the 
torque of the attaching bolts on the inboard support on the outboard 
flap, per McDonnell Douglas Alert Service Bulletin DC10-57A143, 
dated December 20, 1999.
    (1) If no failed bolt is found, repeat the ultrasonic inspection 
or torque verification every 6 months.
    (2) If any failed bolt is found, before further flight, replace 
the bolt and associated parts with a new Inconel bolt and new 
associated parts per the service bulletin, except as provided by 
paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. Accomplishment of 
the replacement constitutes terminating action for the repetitive 
requirements of paragraph (a)(1) of this AD for that bolt.
    (i) If an Inconel bolt is not available for accomplishment of 
the replacement, replacement with a new H-11 steel bolt is 
acceptable provided that operators repeat the ultrasonic inspection 
or torque verification every 6 months until the requirements of 
paragraph (c) of this AD are accomplished.
    (ii) If a PLI washer is not available for accomplishment of the 
Inconel replacement, a new Inconel bolt can be temporarily installed 
without a new PLI washer provided that the bolt is torqued to the 
applicable value specified in the service bulletin. Within 6,000 
flight hours after an Inconel bolt is torqued, replace the PLI 
washer with a new washer per the service bulletin.

Torque Verification

    (b) For airplanes on which the verification of the torque of the 
attaching bolts on the inboard support on the outboard flap was done 
per paragraph (a) of this AD: Within 2 months after the effective 
date of this AD, verify the torque of the attaching bolts on the 
outboard support on the inboard and outboard flaps, per McDonnell 
Douglas Alert Service Bulletin DC10-57A143, dated December 20, 1999; 
and do the applicable action(s) specified in paragraph (a)(1) or 
(a)(2) of this AD.

Bolt Replacement

    (c) Within 2 years after accomplishing the initial inspection 
required by paragraph (a) of this AD or the torque verification 
required by paragraphs (a) and (b) of this AD, do the action 
specified in paragraph (a)(2) of this AD for all H-11 bolts. 
Accomplishment of the replacement of all H-11 bolts with Inconcel 
bolts constitutes terminating action for the requirements of this 
AD.

Spares

    (d) As of 2 years after the effective date of this AD, no person 
shall install, on any airplane, an H-11 steel bolt, part number 
71658-8-44, 71658-7-44, 71658-7-54, 71658-7-56, 71658-7-29, 71658-9-
31, 71658-9-34, 71658-9-38, 71658-9-41, 71658-10-41, 71658-7-26, 
71658-7-27, or 71658-8-29, on the inboard or outboard flap assembly.

Alternative Methods of Compliance

    (e)(1) 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 Aircraft Certification 
Office (ACO), FAA. 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.

    (2) Alternative methods of compliance, approved previously per 
AD 2000-16-10, amendment 39-11866, are considered to be approved as 
alternative methods of compliance with this AD.

Special Flight Permits

    (f) Special flight permits may be issued in accordance with 
Secs. 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.

Incorporation by Reference

    (g) The actions shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin DC10-57A143, dated December 20, 1999. 
This incorporation by reference of that document was approved 
previously by the Director of the Federal Register as of September 
25, 2000 (65 FR 50621, August 21, 2000). Copies may be obtained from 
Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood 
Boulevard, Long

[[Page 35373]]

Beach, California 90846, Attention: Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024). 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, 3960 Paramount Boulevard, Lakewood, California; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on August 9, 2001.


    Issued in Renton, Washington, on June 27, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-16739 Filed 7-3-01; 8:45 am]
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