[Federal Register: January 20, 2004 (Volume 69, Number 12)]
[Rules and Regulations]
[Page 2657-2659]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20ja04-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-164-AD; Amendment 39-13431; AD 2004-01-17]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F
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 and -11F airplanes,
that requires an initial general visual inspection of the power feeder
cables of the integrated drive generator (IDG) and the fuel feed lines
of engine pylons No. 1 and No. 3 on the wings for proper clearance and
damage; corrective actions if necessary; and repetitive general visual
inspections and a terminating action for the repetitive inspections.
This action is necessary to prevent potential chafing of the power
feeder cables of the IDG in engine pylons No. 1 and No. 3 on the wings,
and consequent arcing on the fuel lines in the engine pylons and
possible fuel fire. This action is intended to address the identified
unsafe condition.
DATES: Effective February 24, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 24, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplanes, 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,
[[Page 2658]]
California 90712; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Brett Portwood, Aerospace Engineer,
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California
90712; telephone (562) 627-5350; 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
MD-11 and -11F airplanes was published in the Federal Register on June
18, 2003 (68 FR 36520). That action proposed to require an initial
general visual inspection of the power feeder cables of the integrated
drive generator (IDG) and the fuel feed lines of engine pylons No. 1
and No. 3 on the wings for proper clearance and damage; corrective
actions if necessary; and repetitive general visual inspections and a
terminating action for the repetitive inspections.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comment received.
Request To Allow Accomplishment of Previous Service Bulletin Revision
One commenter requests that actions accomplished before the
effective date of the AD, per Revision 01 of Boeing Alert Service
Bulletin MD11-54A011, dated August 22, 2001, be considered acceptable
for compliance with the requirements of this AD. The commenter also
asks whether, when an AD mandates a service bulletin that contains the
statement ``No more work is necessary on airplanes changed as shown in
Revision 01 of the service bulletin,'' it can assume that the AD allows
actions to be accomplished per the earlier revision of the service
bulletin.
The FAA partially agrees. We agree that actions accomplished before
the effective date of this AD per Revision 01 of Boeing Alert Service
Bulletin MD11-54A011, dated August 22, 2001, are acceptable for
compliance with the requirements of this AD. Because paragraph (e) of
this AD already provides this option, no change to the final rule is
necessary in this regard.
We do not agree that an operator may assume that the AD allows
actions to be accomplished per an earlier revision of the service
bulletin when the service bulletin includes the statement that ``No
more work is necessary on airplanes changed as shown in Revision * * *
of the service bulletin.'' The AD must specifically address whether or
not a previous version of a service bulletin will satisfy the intent of
the AD. No change to the final rule is necessary in this regard.
Explanation of Changes Made to the Proposed AD
For clarification, the FAA has revised the definition of a
``general visual inspection'' in this final rule.
We have also revised the citation for Boeing Alert Service Bulletin
MD11-54A011, dated August 22, 2001, to correctly cite the issue date of
that service bulletin.
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 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.
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. However, for clarity and consistency in this final rule, we
have retained the language of the NPRM regarding that material.
Increase in Labor Rate
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 195 Model MD-11 and -11F airplanes of the
affected design in the worldwide fleet. The FAA estimates that 74
airplanes of U.S. registry will be affected by this, that it will take
approximately 1 work hour per airplane to accomplish the required
inspection, and that the average labor rate is $65 per work hour. Based
on these figures, the cost impact of the AD on U.S. operators is
estimated to be $4,810, or $65 per airplane, per inspection cycle.
It will take approximately 4 work hours per airplane to accomplish
the terminating action, at an average labor rate of $65 per work hour.
Required parts will cost approximately $91 per airplane. Based on these
figures, the cost impact of this terminating action is estimated to be
$25,974, or $351 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. Manufacturer warranty remedies may be available
for labor costs associated with this proposed AD. As a result, the
costs attributable to the proposed AD may be less than stated above.
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.
[[Page 2659]]
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:
2004-01-17 McDonnell Douglas: Amendment 39-13431. Docket 2001-NM-
164-AD.
Applicability: Model MD-11 and -11F airplanes, as listed in
Boeing Alert Service Bulletin MD11-54A011, Revision 02, dated May
31, 2002; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent potential chafing of the power feeder cables of the
integrated drive generator (IDG) in engine pylons No. 1 and No. 3 on
the wings, and consequent arcing on the fuel lines in the engine
pylons and possible fuel fire, accomplish the following:
Note 1: Boeing has issued Information Notice MD11-54A011 R02 IN
02, dated July 11, 2002. The information notice informs operators of
a typographical error for the string tie part number (P/N) specified
in the Boeing Alert Service Bulletin MD11-54A011, Revision 02. The
service bulletin specifies string tie P/N 190L0F21G/A; the correct
P/N is 109 LOF 21G/A.
Initial Inspection
(a) Within 30 days after the effective date of this AD, do a
general visual inspection of the power feeder cables of the IDG and
the fuel feed lines of engine pylons No. 1 and No. 3 on the wings
for proper clearance and damage, per Boeing Alert Service Bulletin
MD11-54A011, Revision 02, dated May 31, 2002.
Note 2: 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.''
Condition 1: Proper Clearance and No Damage
(b) If proper clearance exists and no damage is detected during
any inspection required by paragraph (a) of this AD, do the
action(s) specified in paragraphs (b)(1), (b)(2), and (b)(3) of this
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011,
Revision 02, dated May 31, 2002.
(1) For Group 1 and Group 2 airplanes identified in the service
bulletin: Repeat the inspection required by paragraph (a) of this AD
every 6 months until the modification required by paragraph (b)(2)
or (b)(3) of this AD, as applicable, has been done.
(2) For Group 1 airplanes identified in the service bulletin:
Within 18 months after the effective date of this AD, install the
brackets to support the IDG harness, and install new clamps on the
power feeder cables of the IDG of the No. 1 and No. 3 pylons.
(3) For Group 2 airplanes identified in the service bulletin:
Within 18 months after the effective date of this AD, replace the
existing fairlead with a new clamp, and install new tape.
Condition 2: Improper Clearance and No Damage
(c) If improper clearance exists and no damage is detected
during any inspection required by paragraph (a) of this AD, do the
action(s) specified in paragraphs (c)(1), (c)(2), and (c)(3) of this
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011,
Revision 02, dated May 31, 2002.
(1) For Group 1 and Group 2 airplanes identified in the service
bulletin: Before further flight, reposition cables, and repeat the
inspection required by paragraph (a) of this AD every 6 months until
the modification required by paragraph (c)(2) or (c)(3) of this AD,
as applicable, has been done.
(2) For Group 1 airplanes identified in the service bulletin:
Within 18 months after the effective date of this AD, install the
brackets to support the IDG harness, and install new clamps on the
power feeder cables of the IDG of engine pylons No. 1 and No. 3.
(3) For Group 2 airplanes identified in the service bulletin:
Within 18 months after the effective date of this AD, replace the
existing fairlead with a new clamp, and install new tape.
Condition 3: Improper Clearance and Damage Detected
(d) If improper clearance exists and any damage is detected
during any inspection required by paragraph (a) of this AD, do the
action(s) specified in paragraphs (d)(1), (d)(2), and (d)(3) of this
AD, as applicable, per Boeing Alert Service Bulletin MD11-54A011,
Revision 02, dated May 31, 2002.
(1) For Group 1 and Group 2 airplanes identified in the service
bulletin: Before further flight, reposition cables; repair damage or
replace damaged cables or fuel feed lines with new or serviceable
cables or fuel feed lines; and repeat the inspection required by
paragraph (a) of this AD every 6 months until the modification
required by paragraph (d)(2) or (d)(3) of this AD, as applicable,
has been done.
(2) For Group 1 airplanes identified in the service bulletin:
Within 18 months after the effective date of this AD, install the
brackets to support the IDG harness, and install new clamps on the
power feeder cables of the IDG of engine pylons No. 1 and No. 3.
(3) For Group 2 airplanes identified in the service bulletin:
Within 18 months after the effective date of this AD, replace the
existing fairlead with a new clamp, and install new tape.
Credit for Earlier Service Bulletin
(e) Accomplishment of the actions specified in this AD before
the effective date of this AD per Boeing Alert Service Bulletin
MD11-54A011, Revision 01, dated August 22, 2001, is acceptable for
compliance with the requirements of this AD.
Alternative Methods of Compliance
(f) In accordance with 14 CFR 39.19, the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance for this AD.
Incorporation by Reference
(g) Unless otherwise specified in this AD, the actions shall be
done in accordance with Boeing Alert Service Bulletin MD11-54A011,
Revision 02, dated May 31, 2002. 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 Airplanes, 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 90712; 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 February 24, 2004.
Issued in Renton, Washington, on January 2, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-762 Filed 1-16-04; 8:45 am]
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