[Federal Register Volume 65, Number 162 (Monday, August 21, 2000)]
[Rules and Regulations]
[Pages 50621-50623]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-20774]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-50-AD; Amendment 39-11866; AD 2000-16-10]
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 adopts a new 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 requires 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 AD 
also requires replacing all bolts with bolts made from Inconel, which 
constitutes terminating action for the repetitive inspection 
requirements. This amendment is prompted by an in-flight loss of the 
inboard flap assembly on an airplane during approach for landing. 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 September 25, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 25, 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: 
Technical Publications Business Administration, Dept. 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 Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ron Atmur, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, 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) to include an airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
DC-10-10, -15, -30, -30F (KC-10A military), and -40 series airplanes 
was published in the Federal Register on May 10, 2000 (65 FR 30021). 
That action proposed to require 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. That action also proposed to 
require replacing all bolts with bolts made from Inconel, which 
constitutes terminating action for the repetitive inspection 
requirements.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for Proposed AD

    One commenter supports the proposed AD.

Request To Revise Compliance Time

    One commenter requests that the threshold of both the initial and 
repetitive inspections of the flap hinge bolts be provided in terms of 
landings rather than calendar days. The commenter did not offer a 
reason for its request. The FAA does not concur. We assume that 
specifying the compliance time in flight hours or landings would fit 
more easily into a maintenance program. We have determined that the 
cause of the identified unsafe condition is stress corrosion cracking 
of the attachment bolts. Stress corrosion cracking is dependent upon 
calendar time not on flight hours or landings accumulated on an 
airplane. Therefore, no change to the final rule is necessary.

[[Page 50622]]

Explanation of Change to the Applicability of the Proposed AD

    On May 9, 2000 (i.e., after issuance of the NPRM), the FAA issued a 
Type Certificate (TC) for McDonnell Douglas Model MD-10-10F and MD-10-
30F series airplanes. Model MD-10 series airplanes are Model DC-10 
series airplanes that have been modified with an Advanced cockpit. The 
H-11 attaching bolts on the inboard and outboard support on the inboard 
and outboard flap assembly installed on Model MD-10-10F and MD-10-30F 
series airplanes (before or after the modifications necessary to meet 
the type design of a Model MD-10 series airplane) are identical to 
those on the affected Model DC-10-10, -15, -30, and -40 series 
airplanes, and KC-10A (military) airplanes. Therefore, all of these 
airplanes may be subject to the same unsafe condition. In addition, the 
manufacturer's fuselage number and factory serial number are not 
changed during the conversion from a Model DC-10 to Model MD-10. We 
find that Model MD-10-10F and MD-10-30F series airplanes were not 
specifically identified by model in the applicability of the NPRM; 
however, they were identified by manufacturer's fuselage numbers in 
McDonnell Douglas Alert Service Bulletin DC10-57A143, dated December 
20, 1999 (which was referenced in the applicability statement of the AD 
for determining the specific affected airplanes). Therefore, we have 
revised the applicability throughout the final rule to include Model 
MD-10-10F and MD-10-30F series airplanes.

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 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.

Cost Impact

    There are approximately 412 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.
    It will take between 2 and 8 work hours per airplane to accomplish 
the required inspection/torque verification, at an average labor rate 
of $60 per work hour. Based on these figures, the cost impact of the 
inspection/torque verification required by this AD on U.S. operators is 
estimated to be between $29,280 and $117,120, or between $120 and $480 
per airplane, per inspection cycle.
    It will take approximately 288 work hours per airplane to 
accomplish the required bolt replacement, 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 replacement 
required by this AD on U.S. operators is estimated to be $4,945,148, or 
$20,267 per airplane.
    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 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 adding the following new 
airworthiness directive:

2000-16-10  McDonnell Douglas: Amendment 39-11866. Docket 2000-NM-
50-AD.

    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 (d) 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 and Corrective Actions

    (a) Within 2 months after the effective date of this AD, perform 
an ultrasonic inspection of the attaching bolts on the inboard and 
outboard support on the inboard and outboard flap assembly to detect 
failed bolts, or verify the torque of the attaching bolts on the 
inboard support on the outboard flap, in accordance with McDonnell 
Douglas Alert Service Bulletin DC10-57A143, dated December 20, 1999.
    (1) If no failed bolt is found, repeat the ultrasonic inspection 
thereafter at intervals not to exceed 6 months.
    (2) If any failed bolt is found, prior to further flight, 
replace the bolt and associated parts with a new Inconel bolt and 
new associated parts in accordance with 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 inspection requirements of paragraph (a)(1) of this 
AD for that bolt.
    (i) If an Inconel bolt is not available for accomplishment of 
the replacement,

[[Page 50623]]

replacement with a new H-11 steel bolt is acceptable provided that 
operators repeat the ultrasonic inspection thereafter at intervals 
not to exceed 6 months until the requirements of paragraph (b) 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 in accordance with the service bulletin.

Bolt Replacement

    (b) Within 2 years after accomplishing the initial inspection 
required by paragraph (a) of this AD, accomplish 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

    (c) 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

    (d) 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, Transport Airplane Directorate. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Los Angles 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.

Special Flight Permits

    (e) 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.

Incorporation by Reference

    (f) The actions shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin DC10-57A143, dated December 20, 1999. 
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 Boeing Commercial Aircraft Group, 
Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 
90846, Attention: Technical Publications Business Administration, 
Dept. 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.
    (g) This amendment becomes effective on September 25, 2000.

    Issued in Renton, Washington, on August 10, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-20774 Filed 8-18-00; 8:45 am]
BILLING CODE 4910-13-U