[Federal Register Volume 65, Number 98 (Friday, May 19, 2000)]
[Proposed Rules]
[Pages 31837-31839]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-12674]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-163-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to all Boeing Model 777 series 
airplanes, that currently requires repetitive testing of the engine 
fire shutoff switch (EFSS) to determine if the override mechanism and 
the switch handle are operational, and replacement of the EFSS, if 
necessary. That AD also requires, for certain airplanes, installation 
of a collar on a specific circuit breaker of the standby power 
management panel, and installation of placards to advise the flightcrew 
that the override mechanism must be pushed in order to pull the fire 
switch. That AD was prompted by a report indicating that a solenoid and 
an override mechanism of the EFSS were not operational due to 
overheating of the solenoid. The actions specified by the proposed AD 
are intended to prevent damage to the EFSS solenoid and to the override 
mechanism, and consequent failure of the EFSS due to overheating of the 
solenoid; such failure could result in the inability of the flightcrew 
to discharge the fire extinguishing agent in the event of an engine 
fire. This action would add various actions that would terminate the 
repetitive testing requirements.

DATES: Comments must be received by July 3, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-163-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays.
    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: Larry Reising, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Transport Airplane Directorate, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2683; fax (425) 227-1181.

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 notice may be changed in 
light of the comments received.
    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 notice must submit a self-addressed, 
stamped

[[Page 31838]]

postcard on which the following statement is made: ``Comments to Docket 
Number 99-NM-163-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. 99-NM-163-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On May 5, 1997, the FAA issued AD 97-10-11, amendment 39-10023 (62 
FR 25837, May 12, 1997), applicable to all Boeing Model 777 series 
airplanes, to require repetitive testing of the engine fire shutoff 
switch (EFSS) to determine if the override mechanism and the switch 
handle are operational, and replacement of the EFSS, if necessary. That 
AD also requires, for certain airplanes, installation of a collar on a 
specific circuit breaker of the standby power management panel, and 
installation of placards to advise the flightcrew that the override 
mechanism must be pushed in order to pull the fire switch. That action 
was prompted by a report indicating that a solenoid and an override 
mechanism of the EFSS were not operational due to overheating of the 
solenoid. The actions specified by that AD are intended to prevent 
damage to the EFSS solenoid and to the override mechanism due to 
overheating of the solenoid; such failure of the EFSS could result in 
the inability of the flightcrew to discharge the fire extinguishing 
agent in the event of an engine fire.

Actions Since Issuance of Previous Rule

    In the preamble to AD 97-10-11, the FAA specified that the actions 
required by that AD were considered ``interim action'' and that once a 
final action is identified, the FAA may consider additional rulemaking 
action. The FAA has determined that further rulemaking action is indeed 
necessary; this proposed AD follows from that determination.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
777-26A0009, dated October 23, 1997. The service bulletin describes 
procedures for activating the circuit breaker C26612 in the P310 panel; 
removing the placards in the flight compartment; and replacing the EFSS 
with a new EFSS. Accomplishment of these actions eliminates the need 
for repetitive testing of the EFSS required by AD 97-10-11. 
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 supersede AD 97-10-11 to continue require repetitive 
testing of the EFSS to determine if the override mechanism and the 
switch handle are operational, and replacement of the EFSS, if 
necessary. The proposed AD also would continue to require, for certain 
airplanes, installation of a collar on a specific circuit breaker of 
the standby power management panel, and installation of placards to 
advise the flightcrew that the override mechanism must be pushed in 
order to pull the fire switch. In addition, the proposed AD would 
require accomplishment of the actions specified in the service bulletin 
described previously, except as discussed below.

Differences Between the Proposed AD and the Service Bulletin

    Operators should note that the effectivity listing of Boeing Alert 
Service Bulletin 777-26A0009 affects airplanes having line positions 1 
through 93 inclusive. The FAA has determined that, although the engine 
fire control switches, part number (P/N) 233W6201-1, and P/N's 
S231W263-1 and -2, were installed on affected airplanes during 
manufacture, it may be possible that these switches have been installed 
on Model 777 series airplanes during maintenance activities. Therefore, 
the FAA has determined that the applicability of the proposed AD would 
affect all Model 777 series airplanes.

Cost Impact

    There are approximately 196 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 48 airplanes of U.S. registry 
would be affected by this proposed AD.
    The actions that are currently required by AD 97-10-11, and 
retained in this proposed AD, take approximately 1 work hour per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the currently required 
actions on the U.S. operators is estimated to be $2,880, or $60 per 
airplane, per testing cycle.
    The new actions that are proposed in this AD action would take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts would cost 
approximately $4,054 per airplane. Based on these figures, the cost 
impact of the new proposed requirements of this AD on U.S. operators is 
estimated to be $197,472, or $4,114 per airplane.
    The cost impact figures discussed above is based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.

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 removing amendment 39-10023 (62 FR 
25837, May 12, 1997), and by adding a new airworthiness directive (AD), 
to read as follows:


[[Page 31839]]


Boeing: Docket 99-NM-163-AD. Supersedes AD 97-10-11, Amendment 39-
10023.

    Applicability: All Model 777 series airplanes, certificated in 
any category.

    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 (e) 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 damage to the engine fire shutoff switch (EFSS) 
solenoid and to the override mechanism, and consequent failure of 
the EFSS, which could result in the inability of the flightcrew to 
discharge the fire extinguishing agent in the event of an engine 
fire, accomplish the following:

Restatement of Actions Required by AD 97-10-11

Repetitive Testing of the EFSS

    (a) For all airplanes: Within 14 days after May 27, 1997 (the 
effective date of AD 97-10-11, amendment 39-10023), perform a test 
of the EFSS of both the left-and right-hand engines to determine if 
the override mechanism and the switch handle are operational, in 
accordance with Boeing Alert Service Bulletin 777-26A0012, dated May 
1, 1997.
    (1) If the override mechanism and the switch handle of the EFSS 
are operational, prior to further flight, accomplish the 
requirements of paragraph (a)(1)(i) or (a)(1)(ii) of this AD, as 
applicable, in accordance with the alert service bulletin.
    (i) For Group 1 airplanes identified in the alert service 
bulletin: Install a collar on circuit breaker C26612 of panel P310 
of the standby power management panel. Following accomplishment of 
this installation, prior to further flight, install placards near 
the EFSS of both engines and near the auxiliary power unit (APU) 
EFSS to advise the flightcrew that the override mechanism must be 
pushed in order to pull the fire switch.
    (ii) For Group 2 airplanes identified in the alert service 
bulletin: Ensure that a collar is installed on circuit breaker 
C26612 of panel P310 of the standby power management panel. If a 
collar is not installed, prior to further flight, install a collar 
on circuit breaker C26612 of panel P310 of the standby power 
management panel.
    (2) If the override mechanism or the switch handle of the EFSS 
is not operational, prior to further flight, replace the EFSS with a 
new or serviceable EFSS, in accordance with the alert service 
bulletin.
    (b) For all airplanes: Repeat the requirements of paragraph (a) 
of this AD thereafter at intervals not to exceed 500 flight hours.

New Actions Required by This AD

Terminating Action

    (c) For all airplanes: Within 2 years after the effective date 
of this AD, accomplish the actions specified in paragraphs (c)(1), 
(c)(2), and (c)(3) of this AD in accordance with Boeing Alert 
Service Bulletin 777-26A0009, dated October 23, 1997. Accomplishment 
of all three actions constitutes terminating action for the 
repetitive testing requirements of paragraph (b) of this AD.
    (1) Replace the engine fire control module.
    (2) Activate the circuit breaker C26612 in the P310 panel.
    (3) Remove the placards in the flight compartment.

Spares

    (d) As of the effective date of this AD, no person shall install 
an engine fire control module, part number (P/N) 233W6201-1, or 
engine fire switches P/N S231W263-1 or -2, on any airplane.

Alternative Methods of Compliance

    (e) 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, Transport Airplane Directorate. 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 2: 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

    (f) Special flight permits may be issued in accordance with 
Secs. 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 May 15, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-12674 Filed 5-18-00; 8:45 am]
BILLING CODE 4910-13-P