[Federal Register: September 22, 2003 (Volume 68, Number 183)]
[Rules and Regulations]
[Page 54992-54994]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22se03-6]
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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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