[Federal Register Volume 65, Number 229 (Tuesday, November 28, 2000)]
[Rules and Regulations]
[Pages 70787-70789]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-29799]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-163-AD; Amendment 39-12001; AD 2000-23-28]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes 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. This amendment adds various 
actions that would terminate the repetitive testing requirements. 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 by 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 could result in the inability of the flightcrew to discharge 
the fire extinguishing agent in the event of an engine fire.

DATES: Effective January 2, 2001.
    The incorporation by reference of Boeing Alert Service Bulletin 
777-26A0009, dated October 23, 1997, as listed in the regulations, is 
approved by the Director of the Federal Register as of January 2, 2001.
    The incorporation by reference of Boeing Alert Service Bulletin 
777-26A0012, dated May 1, 1997, as listed in the regulations, was 
approved previously by the Director of the Federal Register as of May 
27, 1997 (62 FR 25837, May 12, 1997).

ADDRESSES: 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 Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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 98055-4056; telephone 
(425) 227-2683; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 97-10-11, 
amendment 39-10023 (62 FR 25837, May 12, 1997), which is applicable to 
all Boeing Model 777 series airplanes, was published in the Federal 
Register on May 19, 2000 (65 FR 31837). The action proposed to 
terminate the repetitive testing of the engine fire shutoff switch 
(EFSS) required by AD 97-10-11.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Supportive Comment

    One commenter concurs with the proposed rule and indicates that it 
has almost completed the terminating action on its entire fleet.

Request for Exemption

    One commenter, an operator, requests that an exemption be added to 
the proposed rule for airplanes recently delivered, if the operator can 
prove by inventory records that it has at no time purchased or borrowed 
the EFSS with the part numbers specified in this proposed rule. The 
commenter states that the proposal does not affect operators with 
recently delivered airplanes that were not affected by AD 97-10-11. 
Additionally, the commenter notes that at no time did it have the old 
EFSS in its system nor did it replace an EFSS on any of its in-service 
airplanes. The commenter concludes that this proposed rule should not 
be applicable to it.
    The FAA is unable to grant an exemption in light of the fact that 
paragraph (d) of this final rule prohibits future installation of the 
defective EFSS [engine fire control module having part number (P/N) 
233W6201-1, or engine fire switches having P/N S231W263-1 or -2]. 
Therefore, this requirement affects any airplanes delivered after this 
final rule is issued. However, the FAA recognizes from the commenter's 
interpretation of paragraph (c) of the final rule that this paragraph 
requires further clarification. The FAA's intent is to require removal 
and replacement of the engine fire control module only if it contains a 
defective EFSS. Therefore, paragraph (c) of this final rule has been 
revised to add an option to verify that the improved engine fire 
control module is installed, which would constitute terminating action 
for the repetitive testing requirements in paragraph (b) of the final 
rule.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change

[[Page 70788]]

previously described. The FAA has determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

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 
will be affected by this AD.
    The actions that are currently required by AD 97-10-11, and 
retained in this 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 required by this AD action take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$4,054 per airplane. Based on these figures, the cost impact of the new 
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 are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this 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 adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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 removing amendment 39-10023 (62 FR 
25837, May 12, 1997), and by adding a new airworthiness directive (AD), 
amendment 39-12001, to read as follows:

2000-23-28  Boeing: Amendment 39-12001. 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 either paragraph 
(c)(1) or (c)(2) of this AD, in accordance with Boeing Alert Service 
Bulletin 777-26A0009, dated October 23, 1997.
    (1) Verify that the airplane does not have an engine fire 
control module having part number (P/N) 233W6201-1, and that the 
airplane configuration is equivalent to that specified in the alert 
service bulletin. If the airplane meets the requirements in this 
paragraph, no further action is required by this AD.
    (2) If the airplane does not meet the requirements specified in 
paragraph (c)(1) of this AD: Remove the engine fire control module, 
P/N 233W6201-1, and replace it with P/N 233W6201-5; activate the 
circuit breaker C26612 in the P310 panel; and remove the placards in 
the flight deck compartment; in accordance with the alert service 
bulletin. Accomplishment of this paragraph constitutes terminating 
action for the repetitive testing requirements of paragraph (b) of 
this AD.

Spares

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

[[Page 70789]]

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. 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 
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.

Incorporation by Reference

    (g) The actions shall be done in accordance with Boeing Alert 
Service Bulletin 777-26A0012, dated May 1, 1997, and Boeing Alert 
Service Bulletin 777-26A0009, dated October 23, 1997.
    (1) The incorporation by reference of Boeing Alert Service 
Bulletin 777-26A0009, dated October 23, 1997, is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The incorporation by reference of Boeing Alert Service 
Bulletin 777-26A0012, dated May 1, 1997, was approved previously by 
the Director of the Federal Register as of May 27, 1997 (62 FR 
25837, May 12, 1997).
    (3) 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.

Effective Date

    (h) This amendment becomes effective on January 2, 2001.

    Issued in Renton, Washington, on November 15, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-29799 Filed 11-27-00; 8:45 am]
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