[Federal Register Volume 68, Number 183 (Monday, September 22, 2003)]
[Rules and Regulations]
[Pages 54992-54994]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-23670]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-164-AD; Amendment 39-13308; AD 2003-19-05]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, -10F, 
-15, -30, -30F (KC-10A and KDC-10), -40, and -40F Airplanes; and Model 
MD-10-10F and -30F 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, -10F, -15, -30, 
-30F (KC-10A and KDC-10), -40, and -40F airplanes; and certain Model 
MD-10-10F and -30F airplanes, that requires inspections for cracking 
and corrosion of the bolt assemblies and bushings on the hinge fittings 
of the inboard and outboard flaps of the left and right wings, and 
follow-on and corrective actions. This action is necessary to prevent 
failure of the bolt and bushing that attach the hinge fitting to the 
flap, which could result in loss of the flap and consequent reduced 
controllability of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Effective October 27, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 27, 2003.

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) to include an airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F 
airplanes; and certain Model MD-10-10F and -30F airplanes, was 
published in the Federal Register on June 10, 2003 (68 FR 34557). That 
action proposed to require inspections for cracking and corrosion of 
the bolt assemblies and bushings on the hinge fittings of the inboard 
and outboard flaps of the left and right wings, and follow-on and 
corrective actions.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

[[Page 54993]]

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance (AMOCs). Because we have now included this material in part 
39, only the office authorized to approve AMOCs is identified in each 
individual AD.

Change to Labor Rate Estimate

    We have reviewed the figures we have used over the past several 
years to calculate AD costs to operators. To account for various 
inflationary costs in the airline industry, we find it necessary to 
increase the labor rate used in these calculations from $60 per work 
hour to $65 per work hour. The cost impact information, below, reflects 
this increase in the specified hourly labor rate.

Cost Impact

    There are approximately 402 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 297 airplanes of U.S. registry 
will be affected by this AD.
    It will take approximately 1 work hour per airplane to accomplish 
the required initial inspections, at an average labor rate of $65 per 
work hour. Based on these figures, the cost impact of the required 
initial inspections on U.S. operators is estimated to be $19,305, or 
$65 per airplane.
    It will take approximately 2 work hours per flap to accomplish the 
required replacement. Each wing has 2 flaps; therefore, it will take 
approximately 4 work hours per airplane to accomplish the required 
replacement, at an average labor rate of $65 per work hour. Required 
parts will cost approximately $2,982 for the outboard flap, and $2,825 
for the inboard flap. Based on these figures, the cost impact of the 
required replacement on U.S. operators is estimated to be $1,801,899, 
or $6,067 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

0
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

0
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]


0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-19-05 Boeing: Amendment 39-13308. Docket 2002-NM-164-AD.

    Applicability: Model DC-10-10, -10F, -15, -30, -30F (KC-10A and 
KDC-10), -40, and -40F airplanes; and Model MD-10-10F and -30F 
airplanes; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the bolt and bushing that attach the hinge 
fitting to the flap, which could result in loss of the flap and 
consequent reduced controllability of the airplane, accomplish the 
following:

Initial General Visual and Magnetic Particle Inspections

    (a) Within 6 months after the effective date of this AD: Do 
initial general visual and magnetic particle inspections for 
cracking and corrosion of the pivot bolt assemblies and bushings on 
the hinge fittings of the inboard and outboard flaps of the left and 
right wings, per Boeing Alert Service Bulletin DC10-57A148, Revision 
01, dated August 13, 2002; and Boeing Alert Service Bulletin DC10-
57A117, Revision 01, dated July 23, 2002; as applicable. Before 
further flight, do the applicable follow-on and corrective actions 
required by paragraphs (a)(1), (a)(2), and (a)(3) of this AD.

    Note 1: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Follow-On and Corrective Actions

    (1) If no cracking or corrosion is found: Before further flight, 
do the actions specified in either paragraph (a)(1)(i) or (a)(1)(ii) 
of this AD per Condition 1 of the Work Instructions of the 
applicable service bulletin.
    (i) Do the actions specified in Option 1 of Condition 1 per the 
applicable service bulletin. The actions include (for the inboard 
flaps) reinstalling each existing bushing, replacing each existing 
pivot bolt assembly with a new assembly made from corrosion-
resistant steel, and lubricating the assembly; (for the outboard 
flaps) replacing each existing pivot bolt assembly with a new 
assembly made from multi-phase material, and lubricating the 
assembly.
    (ii) Do the actions specified in Option 2 of Condition 1 per the 
applicable service bulletin. The actions include (for the inboard 
flaps) reinstalling the existing bushing and pivot bolt assembly, 
lubricating the assembly, repeating the lubrication at the intervals 
specified, and doing repetitive ultrasonic inspections of the 
assembly for cracking at the intervals specified; (for the outboard 
flaps) reinstalling the pivot bolt assembly, lubricating the 
assembly, repeating the lubrication at the intervals specified, and 
doing repetitive ultrasonic inspections of the assembly for cracking 
at the intervals specified. Accomplishment of paragraph (a)(1)(i) of 
this AD terminates the requirements of this paragraph.
    (2) If corrosion is found: Before further flight, do the actions 
specified in either paragraph (a)(2)(i) or (a)(2)(ii) of this AD per 
Condition 2 of the Work Instructions of the applicable service 
bulletin.
    (i) Do the actions specified in Option 1 of Condition 2 per the 
applicable service bulletin. The actions include (for the inboard 
flaps) replacing the affected bushing with a

[[Page 54994]]

new equivalent part, replacing the affected pivot bolt assembly with 
a new assembly made from corrosion-resistant steel, and lubricating 
each assembly; (for the outboard flaps) replacing the affected pivot 
bolt assembly with a new assembly made from multi-phase material, 
and lubricating each assembly.
    (ii) Do the actions specified in Option 2 of Condition 2 per the 
applicable service bulletin. The actions include (for the inboard 
flaps) repairing and re-installing the existing bushing and affected 
pivot bolt assembly, lubricating each assembly, repeating the 
lubrication at the intervals specified, and doing repetitive 
ultrasonic inspections of the assembly for cracking at the intervals 
specified; (for the outboard flaps) repairing and installing the 
existing pivot bolt assembly, lubricating each assembly, repeating 
the lubrication at the intervals specified, and doing repetitive 
ultrasonic inspections of the assembly for cracking, at the 
intervals specified. Do the inspections until paragraph (a)(2)(i) of 
this AD has been done.
    (3) If cracking is found: Before further flight, do the actions 
specified in either paragraph (a)(3)(i) or (a)(3)(ii) of this AD per 
Condition 3 of the Work Instructions of the applicable service 
bulletin.
    (i) Do the actions specified in Option 1 of Condition 3 per the 
applicable service bulletin. The actions include (for the inboard 
flaps) replacing the affected bushing with a new equivalent part, 
replacing the affected pivot bolt assembly with a new assembly made 
from corrosion-resistant steel, and lubricating each assembly; (for 
the outboard flaps) replacing the affected pivot bolt assembly with 
a new assembly made from multi-phase material, and lubricating each 
assembly.
    (ii) Do the actions specified in Option 2 of Condition 3 per the 
applicable service bulletin. The actions include (for the inboard 
flaps) replacing the affected bushing and pivot bolt assembly with 
new equivalent parts, lubricating each assembly, repeating the 
lubrication at the intervals specified, and doing repetitive 
ultrasonic inspections of the assembly for cracking at the intervals 
specified; (for the outboard flaps) replacing the affected pivot 
bolt assembly with a new equivalent part, lubricating each assembly, 
repeating the lubrication at the intervals specified, and doing 
repetitive ultrasonic inspections of the assembly for cracking at 
the intervals specified. Do the inspections until paragraph 
(a)(3)(i) of this AD has been done.

Credit for Actions Done per Previous Issue of Service Bulletins

    (b) Accomplishment of the specified actions before the effective 
date of this AD per Boeing Alert Service Bulletin DC10-57A148, dated 
June 14, 2002; or Boeing Alert Service Bulletin DC10-57A117, dated 
February 11, 1991; is considered acceptable for compliance with the 
applicable requirements of paragraph (a) of this AD.

Alternative Methods of Compliance

    (c) In accordance with 14 CFR 39.19, the Manager, Los Angeles 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance (AMOCs) for this AD.

Incorporation by Reference

    (d) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Boeing Alert Service Bulletin DC10-57A148, 
Revision 01, dated August 13, 2002; and Boeing Alert Service 
Bulletin DC10-57A117, Revision 01, dated July 23, 2002; as 
applicable. 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: 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

    (e) This amendment becomes effective on October 27, 2003.

    Issued in Renton, Washington, on September 11, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-23670 Filed 9-18-03; 12:01 pm]
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