[Federal Register: October 1, 2003 (Volume 68, Number 190)]
[Proposed Rules]
[Page 56594-56596]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01oc03-34]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-55-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model 717-200
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain McDonnell Douglas Model
717-200 airplanes. This proposal would require repetitive inspections
of the electric motor of the auxiliary hydraulic pump for electrical
resistance, continuity, mechanical rotation, and associated wiring
resistance/voltage; and corrective actions, if necessary. The actions
are intended to prevent various failures of the electric motor of the
auxiliary hydraulic pump and associated wiring, which could result in
fire at the auxiliary hydraulic pump and consequent damage to the
adjacent electrical equipment and/or structure. This action is intended
to address the identified unsafe condition.
DATES: Comments must be received by November 17, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-55-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address: 9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-55-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Boeing Commercial Aircraft Group, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 98046, Attention: Data
and Service Management, Dept. C1-L5A (D800-0024). This information may
be examined 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.
FOR FURTHER INFORMATION CONTACT: Albert Lam, Aerospace Engineer;
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California
90712-4137; telephone (562) 627-5346; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the proposed
AD is being requested.
[sbull] Include justification (e.g., reasons or data) for each
request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2003-NM-55-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2003-NM-55-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received reports that, during ground operations or when
powered in flight by the air driven generator, the electric motor of
the auxiliary hydraulic pump and associated motor feeder cables failed
on certain McDonnell Douglas Model MD-80, MD-90, DC-10, and MD-11
series airplanes. These failures consisted of a seized or difficult to
turn rotor on the pump assembly, burnt and shorted motor feeder cables,
and/or uncontained internal electric arcing failures with the electric
motor. Investigation revealed that these failures may be caused by
hydraulic fluid contamination to the electric motor portion of the
pump, a failed rotor bearing, and/or degradation of the stator's
encapsulation material. Failure of the electric motors of the hydraulic
pump and associated motor feeder cables, if not corrected, could result
in a fire at the auxiliary hydraulic pump and consequent damage to the
adjacent electrical equipment and/or structure.
The subject electric motor on certain McDonnell Douglas Model MD-
80, MD-90, DC-10, and MD-11 series airplanes is identical to that on
the affected Model 717-200 airplanes. Therefore, all of these models
may be subject to the same unsafe condition.
Other Relevant Rulemaking
The FAA has previously issued AD 2001-22-17, amendment 39-12496 (66
FR 56753, November 13, 2001), applicable to certain McDonnell Douglas
Model DC-9-81, -9-82, -9-83, and -9-87 series airplanes; Model MD-88
airplanes; and Model MD-90-30 series airplanes. We have also previously
issued AD 2001-14-08, amendment 39-12319 (66 FR 36441, July 12, 2001),
applicable to certain McDonnell Douglas Model DC-10 series airplanes,
Model MD-10 series airplanes, and Model MD-11 series airplanes. These
ADs require repetitive inspections of the electric motor of the
auxiliary hydraulic pump for electrical resistance, continuity,
mechanical
[[Page 56595]]
rotation, and associated wiring resistance/voltage. Those ADs prevent
various failures of electric motors of the auxiliary hydraulic pump and
associated wiring, which could result in fire at the auxiliary
hydraulic pump and consequent damage to the adjacent electrical
equipment and/or structure.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
717-29A0005, dated July 31, 2002, which describes procedures for
repetitive inspections of the electric motor of the auxiliary hydraulic
pump for electrical resistance, continuity, mechanical rotation, and
associated wiring resistance/voltage; and corrective actions, if
necessary. The corrective actions involve replacing the auxiliary
hydraulic pump with a serviceable pump, troubleshooting, and repairing
the wiring, as applicable.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require accomplishment of the actions specified in
the service bulletin described previously. Although the service
bulletin referenced in this AD specifies to submit certain information
to the manufacturer, this AD does not include such a requirement.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Changes to 14 CFR Part 39/Effect on the Proposed 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 95 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 67 airplanes of U.S. registry
would be affected by this proposed AD, that it would take approximately
1 work hour per airplane to accomplish the proposed inspection, and
that the average labor rate is $65 per work hour. Based on these
figures, the cost impact of the proposed AD on U.S. operators is
estimated to be $4,355, or $65 per airplane, per inspection cycle.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this proposed 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 proposed herein would 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 proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
McDonnell Douglas: Docket 2003-NM-55-AD.
Applicability: Model 717-200 airplanes, manufacturer's fuselage
numbers 5002 through 5200 inclusive, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent various failures of electric motor of the auxiliary
hydraulic pump and associated wiring, which could result in fire at
the auxiliary hydraulic pump and consequent damage to the adjacent
electrical equipment and/or structure, accomplish the following:
Service Bulletin References
(a) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Alert Service Bulletin 717-
29A0005, dated July 31, 2002. Although the service bulletin
referenced in this AD specifies to submit certain information to the
manufacturer, this AD does not include such a requirement.
Initial Inspection and Testing
(b) Prior to the accumulation of 3,000 total flight hours, or
within 12 months after the effective date of this AD, whichever
occurs later, do an inspection of the electric motor of the
auxiliary hydraulic pump for electrical resistance, continuity,
mechanical rotation, and associated writing resistance/voltage per
the service bulletin.
Condition 1, No Failures: Repetitive Inspections
(c) If no failures are detected during any inspection required
by paragraph (b) of this AD, repeat the inspection thereafter at
intervals not to exceed 5,000 flight hours.
Condition 2, Failure of Any Pump Motor: Replacement and Repetitive
Inspections
(d) If any pump motor fails during any inspection required by
paragraph (b) of this AD, before further flight, replace the failed
auxiliary hydraulic pump with a serviceable pump, per the service
bulletin. Repeat the inspection required by paragraph (b) of this AD
at intervals not to exceed 5,000 flight hours.
[[Page 56596]]
Condition 3, Failure of Any Wiring: Repair and Repetitive Inspection
(e) If any wiring fails during any inspection required by
paragraph (b) of this AD, before further flight, troubleshoot and
repair the failed wiring, per the service bulletin. Repeat the
inspection at intervals not to exceed 5,000 flight hours.
Alternative Methods of Compliance
(f) 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.
Issued in Renton, Washington, on September 24, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-24847 Filed 9-30-03; 8:45 am]
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