[Federal Register Volume 62, Number 91 (Monday, May 12, 1997)]
[Rules and Regulations]
[Pages 25837-25839]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-12249]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-90-AD; Amendment 39-10023; AD 97-10-11]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 777 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to all Boeing Model 777 series airplanes. This action
requires repetitive testing of the engine fire shutoff switch (EFSS) to
determine that the override mechanism and the switch handle are
operational, and replacement of the EFSS, if necessary. This action
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. This
amendment is 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 in this 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 of the EFSS could result in the inability of the flightcrew to
discharge the fire extinguishing agent in the event of an engine fire.
DATES: Effective May 27, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 27, 1997.
Comments for inclusion in the Rules Docket must be received on or
before July 11, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 97-NM-90-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
The service information referenced in this AD 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; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Larry Reising, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington; telephone (425) 227-
2683; fax (425) 227-1181.
SUPPLEMENTARY INFORMATION: The FAA has received a report indicating
that a solenoid and an override mechanism of the engine fire shutoff
switch (EFSS) were not operational. Investigation revealed that an
overheating condition in the solenoid damaged the solenoid and the
override mechanism of the EFSS. Further investigation revealed that the
overheating condition of the solenoid may be caused when power is
applied to the EFSS solenoid for long
[[Page 25838]]
periods of time, such as when the airplane is on the ground with the
power on and the engine fuel control switch is in the ``Cutoff''
position. Damage to the EFSS solenoid and to the override mechanism due
to overheating of the solenoid could result in failure of the EFSS.
Such failure, if not corrected, could result in the inability of the
flightcrew to discharge the fire extinguishing agent in the event of an
engine fire.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
777-26A0012, dated May 1, 1997, which describes procedures for
repetitive testing of the EFSS of both the left- and right-hand engines
to determine if the override mechanism and the switch handle are
operational, and replacement of the EFSS, if necessary. For any
airplanes on which a collar on circuit breaker C26612 of panel P310 of
the standby power management panel has not been installed, the alert
service bulletin also describes procedures to perform that
installation, and to 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.
Installation of the collar on circuit breaker C26612 of panel P310,
which is the circuit breaker that supplies power to the EFSS solenoids,
will prevent damage to the EFSS due to overheating of the solenoid.
Explanation of the Requirements of the Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other Boeing Model 777 series airplanes of the same
type design, this AD is being issued 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 AD requires repetitive
testing of the EFSS of both the left- and right-hand engines to
determine if the override mechanism and the switch handle are
operational, and replacement of the EFSS, if necessary. For certain
airplanes, this AD requires installation of a collar on circuit breaker
C26612 of panel P310 of the standby power management panel, and
installation of placards near the EFSS of both engines and near the APU
EPSS to advise the flightcrew that the override mechanism must be
pushed in order to pull the fire switch. The actions are required to be
accomplished in accordance with the alert service bulletin described
previously.
Interim Action
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-NM-90-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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
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:
97-10-11 Boeing: Amendment 39-10023. Docket 97-NM-90-AD.
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 otherwise
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 (c) of this AD.
[[Page 25839]]
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:
(a) For all airplanes: Within 14 days after the effective date
of this AD, 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.
(c) 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.
(d) Special flight permits may be issued in accordance with
sections 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.
(e) The actions shall be done in accordance with Boeing Alert
Service Bulletin 777-26A0012, dated May 1, 1997. 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 Airplane Group, P.O. Box 3707,
Seattle, Washington 98124-2207. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
(f) This amendment becomes effective on May 27, 1997.
Issued in Renton, Washington, on May 5, 1997.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-12249 Filed 5-9-97; 8:45 am]
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