[Federal Register Volume 68, Number 73 (Wednesday, April 16, 2003)]
[Proposed Rules]
[Pages 18565-18567]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-9301]


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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: 
[email protected]. 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