[Federal Register: April 16, 2003 (Volume 68, Number 73)]
[Proposed Rules]
[Page 18565-18567]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16ap03-16]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-05-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747 Series 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 Boeing Model 747 series
airplanes. This proposal would require identification of the valves
installed on the engine struts as hydraulic supply (fire) shutoff
valves for the engine-driven pump, corrective action if necessary, and
eventual replacement of discrepant valves with serviceable parts. This
action is necessary to prevent leakage of hydraulic (flammable) fluid
into an engine fire, which could result in an uncontrolled fire. This
action is intended to address the identified unsafe condition.
DATES: Comments must be received by June 2, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-05-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-05-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 for Windows or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: Kenneth W. Frey, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6468; fax (425) 917-6590.
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-05-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.
[[Page 18566]]
2003-NM-05-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.
Discussion
The FAA has received reports indicating that various intermittent
limit switch functioning problems have caused the failure of certain
``Circle Seal'' valves installed as the engine-driven pump (EDP)
direct-current (DC) motor-operated shutoff valves on certain Boeing
Model 747 series airplanes. This particular valve may malfunction if
the motor limit switches are not actuated, causing the motor to run at
the stop until the clutch fails. If the clutch fails, the valve cannot
open and close for the affected hydraulic system. This failure mode was
discovered during production testing on Model 747 series airplanes. The
subject valve was incorrectly identified by the manufacturer as an
acceptable optional part for Model 747 series airplanes. This valve may
have been installed during production or normal maintenance. The EDP
valve is intended to prevent hydraulic fluid from being supplied to an
engine fire, which could result in an uncontrolled fire.
Related Rulemaking
The FAA previously issued similar rulemaking for the same unsafe
condition on certain Boeing Model 737, 757, and 767 series airplanes.
AD 2001-11-07, amendment 39-12249 (66 FR 31135, June 11, 2001),
requires repetitive operational checks to detect malfunctioning of
certain motor-operated hydraulic shutoff valves, and their eventual
replacement with new valves as terminating action for the repetitive
inspections.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
747-29A2102, including an Evaluation Form, dated June 29, 2000, which
describes procedures for determining, by a records check or inspection,
whether certain Circle Seal valves have been installed on the engine
struts as the EDP DC motor-operated shutoff valves. Corrective action
for discrepant valves includes repetitive tests of the hydraulic supply
(fire) shutoff valves, immediate replacement of failed valves, and
eventual replacement of all subject valves with serviceable valves.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition.
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.
Cost Impact
There are approximately 681 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 130 airplanes of U.S. registry
would be affected by this proposed AD, that it would take approximately
1 work hour per airplane to identify the valve, and that the average
labor rate is $60 per work hour. Based on these figures, the cost
impact of the proposed AD on U.S. operators is estimated to be $7,800,
or $60 per airplane.
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.
Replacing a valve, if required, would take approximately 6 work
hours, at an average labor rate of $60 per work hour. Required parts
and hydraulic fluid would cost approximately $4,438 per valve. Based on
these figures, the cost impact of replacing a valve is estimated to be
$4,798.
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:
Boeing: Docket 2003-NM-05-AD.
Applicability: Model 747 series airplanes, certificated in any
category, as listed in Boeing Alert Service Bulletin 747-29A2102,
dated June 29, 2000.
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 leakage of hydraulic (flammable) fluid into an engine
fire, which could result in an uncontrolled fire, accomplish the
following:
Part Identification
(a) Within 6 months after the effective date of this AD, check
maintenance records or perform a general visual inspection of each
engine strut to determine whether any discrepant valve is installed
as a hydraulic supply (fire) shutoff valve for the engine-driven
pump. A discrepant valve is a Circle Seal valve part number (P/N)
S270T010-3 or a valve that cannot be readily identified.
[[Page 18567]]
Identify the part in accordance with Boeing Alert Service Bulletin
747-29A2102, excluding the Evaluation Form, dated June 29, 2000. If
no discrepant valve is installed, no further work is required by
this paragraph.
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.''
Corrective Actions for Discrepant Valves
(b) For any discrepant valve found during the part
identification required by paragraph (a) of this AD:
(1) Within 6 months after the effective date of this AD, do a
hydraulic supply (fire) shutoff valve test, in accordance with
paragraph 3.J. of the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-29A2102, dated June 29, 2000.
(i) If the valve passes the test, repeat the test in accordance
with paragraph (b)(2) of this AD.
(ii) If the valve does not pass the test: Before further flight,
replace the valve and do a hydraulic supply (fire) shutoff valve
test, in accordance with paragraph 3.I. of the Accomplishment
Instructions of the service bulletin.
(2) Repeat the test specified in paragraph (b)(1) of this AD on
each discrepant valve at least every 6 months, until the actions
specified by paragraph (b)(3) of this AD have been accomplished.
(3) Within 4 years after identifying the valve as required by
paragraph (a) of this AD: Replace each discrepant valve with a
serviceable valve and do a hydraulic supply (fire) shutoff valve
test, in accordance with paragraph 3.I. of the Accomplishment
Instructions of the service bulletin. Replacement of the valve
terminates the repetitive tests required by paragraph (b)(2) of this
AD for that valve.
Part Installation
(c) As of the effective date of this AD, no person may install a
Circle Seal valve P/N S270T010-3 on any airplane unless the
requirements of this AD are accomplished for that valve.
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, Seattle Aircraft Certification
Office (ACO), FAA. Operators shall submit their requests through an
appropriate FAA Principal Maintenance Inspector, who may add
comments and then send it to the Manager, Seattle ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
Special Flight Permits
(e) Special flight permits may be issued in accordance with
Sec. Sec. 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.
Issued in Renton, Washington, on April 8, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-9301 Filed 4-15-03; 8:45 am]
BILLING CODE 4910-13-P