Airworthiness Directives; Boeing Model 767-300 Series Airplanes, 2339-2342 [05-538]
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
TABLE 4.—COMPLIANCE TIMES FOR BLADES P/NS FW12960, FW12961, FW12962, AND FW13175
Boeing 777
series
Engine series
Airplane maximum gross weight
(times 1,000 pounds)
(i) –884B, –892 ..................................................
–300
(ii) –884, –892, –892B, and –895 ......................
–200
(iii) –875 .............................................................
(iv) –877 .............................................................
–200
–200
(g) When engines containing blades P/Ns
FK30838, FK30840, FK30842, FW12960,
FW12961, FW12962, and FW13175 are
moved from one gross weight category to
another, the inspection schedule that is
applicable to the higher gross weight category
must be used.
Terminating Action
(h) As terminating action to the repetitive
inspection requirements of this AD, at the
next shop visit when the fan blades are
removed for repair or overhaul, but no later
than December 31, 2009:
(1) Replace LPC fan blades P/Ns FK30838,
FK30840, FK30842, FW12960, FW12961,
FW12962, or FW13175 with a complete set
of LPC fan blades that have been reworked,
relubricated, and remarked using RR SB No.
RB.211–72–D672, dated February 1, 2002; or;
(2) Replace LPC fan blades P/Ns FK30838,
FK30840, FK30842, FW12960, FW12961,
FW12962, or FW13175 with a complete set
of new LPC fan blades that feature additional
Initial
inspection
CSN
(A) 660 and 632.5 .............................................
(B) 580 ...............................................................
(A) 632.5 and 648 .............................................
(B) 656 ...............................................................
(C) 535 ..............................................................
535 .....................................................................
545 .....................................................................
blade root processing requirements found in
RR SB No. RB.211–72–D672, dated February
1, 2002.
Previous Credit
(i) Previous credit is allowed for initial
inspections of fan blades that were done
using RR ASB No. RB.211–72–AD344,
Revision 4, dated March 15, 2002, Revision
5, dated June 20, 2003, Revision 6, dated
February 27, 2004, or Revision 7, dated
March 12, 2004, before the effective date of
this AD.
Alternative Methods of Compliance
(j) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Material Incorporated by Reference
(k) You must use the Rolls-Royce plc
service information specified in Table 5 of
Repetitive
inspection
CSLI
600
2,400
2,400
600
2,400
2,400
2,400
100
1,200
125
100
1,200
1,200
600
this AD to perform the blade inspections and
replacements required by this AD. The
Director of the Federal Register approved the
incorporation by reference of the documents
listed in Table 5 of this AD in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. You
can get a copy from Rolls-Royce plc, P.O. Box
31, Derby DE24 6BJ, UK; telephone 44 (0)
1332 242424; fax 44 (0) 1332 249936. You
may review copies at the FAA, New England
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2001–NE–17–
AD, 12 New England Executive Park,
Burlington, MA; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html. Table 5 follows:
TABLE 5.—INCORPORATION BY REFERENCE
Service Bulletin No.
Page
Revision
RB.211–72–AD344 ...............................................................
Total Pages: 11
RB.211–72–AD344, Appendices 1 through 5 ......................
Total Pages: 18
RB.211–72–D672 .................................................................
Total Pages: 24
ALL ........................................
7 ............................................
March 12, 2004.
ALL ........................................
7 ............................................
March 12, 2004.
ALL ........................................
Original ..................................
February 1, 2002.
Related Information
DEPARTMENT OF TRANSPORTATION
(l) Civil Aviation Authority (CAA)
airworthiness directive G–2004–0008, dated
April 29, 2004, also addresses the subject of
this AD.
Issued in Burlington, Massachusetts, on
January 3, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–485 Filed 1–12–05; 8:45 am]
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20010; Directorate
Identifier 2003–NM–224–AD; Amendment
39–13938; AD 2005–01–13]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–300 Series Airplanes
BILLING CODE 4910–13–P
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 767–300 series airplanes.
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Date
This AD requires repetitive functional
tests and repetitive replacements of the
auxiliary power unit (APU) and engine
fire shutoff switches. This proposal also
provides an optional terminating action
for the repetitive functional tests and
replacements. This AD is prompted by
a report of the failure of the engine fire
shutoff switch in the engine fire control
module. We are issuing this AD to
prevent mineral build-up on the APU
and engine fire shutoff switches, which
could lead to the switches failing to
discharge fire suppressant to the
affected fire zone and result in an
uncontrolled engine or APU fire and
consequent loss of the airplane.
Effective January 28, 2005. The
incorporation by reference of a certain
publication listed in the AD is approved
DATES:
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
by the Director of the Federal Register
as of January 28, 2005.
We must receive comments on this
AD by March 14, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
room PL–401, Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
20010; the directorate identifier for this
docket is 2003–NM–224–AD.
Examining the Dockets
You can examine the AD docket on
the Internet at https://dms.dot.gov, or in
person in the Docket Management
Facility office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket
Management Facility office (telephone
(800) 647–5227) is located on the plaza
level of the Nassif Building at the DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the Docket
Management System (DMS) receives
them.
FOR FURTHER INFORMATION CONTACT:
Bernie Gonzalez, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6498; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: This AD is
prompted by a report of the failure of
the engine fire shutoff switch in the
engine fire control module, which
resulted in the inability to stow the
thrust reverser on a certain Boeing
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Model 767 series airplane. On this
installation the thrust reverser is
operated by engine pneumatic bleed air,
which is regulated by a spring-loadedclosed pressure regulating and shutoff
valve (PRSOV). The PRSOV requires
electrical power to stay open against the
spring force. Its power supply is routed
through the engine fire shutoff switch.
The electrical contacts for the thrust
reverser inside the engine fire shutoff
switch are normally in the closed
position. When the engine fire shutoff
switch is pulled, during a fire or test,
the power supplied to the thrust
reverser PRSOV is removed and the
valve closes off the engine bleed air,
leaving the thrust reverser in the last
commanded position. Investigation of
the reported incident revealed that
certain flight deck humidifiers
distribute unfiltered air containing
minerals from the potable water supply.
The humidified air contaminates the
auxiliary power unit (APU) and engine
fire shutoff switches and may result in
mineral build-up on switch contacts.
The contamination within the fire
shutoff switch gradually builds up,
causing an increase in contact
resistance. In the case of the thrust
reverser, this contact resistance was
high enough that the power supplied to
the PRSOV was insufficient to hold the
valve open. The PRSOV closed, leaving
the thrust reverser in the deployed state.
This same contamination can build up
on the fire extinguishing switch contacts
inside the APU and engine fire
switches. Mineral build-up on the APU
and engine fire shutoff switches, if not
corrected, could lead to the switches
failing to discharge fire suppressant to
the affected fire zone and result in an
uncontrolled engine or APU fire and
consequent loss of the airplane.
adequately address the unsafe
condition.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other airplanes of the same type
design that may be registered in the U.S.
at some time in the future. Therefore,
this AD is being issued to prevent
mineral build-up on APU and engine
fire shutoff switches, which could lead
to the switches failing to discharge fire
suppressant to the affected fire zone and
result in an uncontrolled engine fire and
consequent loss of the airplane. This AD
requires repetitive functional tests and
repetitive replacements of the APU and
engine fire shutoff switches. This
proposal also provides an optional
terminating action for the repetitive
functional tests and replacements. You
must do these actions in accordance
with the service information described
previously, except as discussed under
‘‘Differences Between the AD and the
Service Bulletin.’’
Differences Between the AD and the
Service Bulletin
Operators should note that the service
bulletin specifies the initial compliance
time as ‘‘after the airplane has 12
calendar months of service but within
18 calendar months since airplane
delivery. * * *’’ This AD, however,
specifies the initial compliance time as
within 18 months since the date of
issuance of the original Airworthiness
Certificate or the original Export
Certificate of Airworthiness. This
decision is based on our determination
that ‘‘since airplane delivery’’ may be
interpreted differently by different
operators. We find that this terminology
is generally understood within the
Relevant Service Information
industry and records will always exist
that establish these dates with certainty.
We have reviewed Boeing Alert
This AD also omits reference to ‘‘after
Service Bulletin 767–26A0127, dated
the airplane has 12 calendar months of
July 17, 2003. The service bulletin
service,’’ since accomplishing the initial
describes the following procedures:
actions within 18 months of service
1. Doing repetitive functional tests of
provides an acceptable level of safety.
the APU and engine fire shutoff
Thus the compliance time specified in
switches;
this AD includes any airplanes that may
2. Doing repetitive replacements of
have been operating since delivery.
the APU and engine fire shutoff
Operators should also note that the
switches with new or serviceable
service bulletin states, ‘‘Operators who
switches; and
3. Deactivating the Lucas (also known perform the 90 calendar day inspection
and the 18 calendar month switch
as TRW Systemes Aeronautiques) flight
servicing can avoid the required test
deck humidifier, part numbers (P/N)
M01AA0101, M01AB0101, M01AB0102, interval shown in Figure 1, by
deactivation of the Lucas (also known as
or M01AB0103, which eliminates the
TRW Systemes Aeronautiques) Flight
need for the repetitive functional tests
Deck Humidifier.’’ This AD, however,
and replacements.
specifies that if an operator deactivates
We have determined that
accomplishment of the actions specified the flight deck humidifier, all APU and
engine fire shutoff switches must be
in the service information will
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Federal Register / Vol. 70, No. 9 / Thursday, January 13, 2005 / Rules and Regulations
replaced with new or serviceable
switches before further flight. We have
determined that if a flight deck
humidifier is deactivated shortly before
any required replacement or required
functional test, it might be possible for
any switch to have a latent type of
failure due to the previous exposure to
moisture and minerals from the
humidifier. To address this unsafe
condition, we have added a requirement
to paragraph (j) of this AD to replace all
switches after deactivating the flight
deck humidifier. We have also added
requirements to paragraph (k) of this AD
to ensure an operator performs the
repetitive functional tests and
replacements of switches after
reactivating the flight deck humidifier.
Costs of Compliance
None of the airplanes affected by this
action are on the U.S. Register. All
airplanes affected by this AD are
currently operated by non-U.S.
operators under foreign registry;
therefore, they are not directly affected
by this AD action. However, we
consider this AD necessary to ensure
that the unsafe condition is addressed if
any affected airplane is imported and
placed on the U.S. Register in the future.
If an affected airplane is imported and
placed on the U.S. Register in the future,
the required functional test would take
about 2 work hours per switch, at an
average labor rate of $65 per work hour.
We estimate there are 3 switches per
airplane. No parts would be required.
Based on these figures, the estimated
cost of the AD would be $390 per
airplane, per testing cycle.
If an affected airplane is imported and
placed on the U.S. Register in the future,
the required switch replacement would
take about 2 work hours per switch, at
an average labor rate of $65 per work
hour. Required parts would cost about
$1,000 per switch, if replaced with a
serviceable switch. Based on these
figures, the estimated cost of the AD
would be $1,130 per switch, per
replacement.
FAA’s Determination of the Effective
Date
No airplane affected by this AD is
currently on the U.S. Register.
Therefore, providing notice and
opportunity for public comment is
unnecessary before this AD is issued,
and this AD may be made effective in
less than 30 days after it is published in
the Federal Register.
Comments Invited
Although this is a final rule that was
not preceded by notice and an
opportunity for public comment, we
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invite you to submit any written
relevant data, views, or arguments
regarding this AD. Send your comments
to an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2005–20010;
Directorate Identifier 2003–NM–224AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the AD. We will consider all comments
received by the closing date and may
amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of our docket Web site,
anyone can find and read the comments
in any of our dockets, including the
name of the individual who sent the
comment (or signed the comment on
behalf of an association, business, labor
union, etc.). You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78), or you may visit
https://dms.dot.gov.
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. 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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
Subtitle I, section 106 describes the
authority of the FAA Administrator.
Subtitle VII, Aviation Programs,
describes in more detail the scope of the
agency’s authority.
This rulemaking is promulgated
under the authority described in subtitle
VII, part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this AD.
Authority: 49 U.S.C. 106(g), 40113, 44701.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD 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.
For the reasons discussed above, I
certify that the regulation:
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2005–01–13 Boeing: Amendment 39–13938.
Docket No. FAA–2005–20010;
Directorate Identifier 2003–NM–224–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 28, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767–
300 series airplanes, certificated in any
category; as listed in Boeing Alert Service
Bulletin 767–26A0127, dated July 17, 2003.
Unsafe Condition
(d) This AD was prompted by a report of
the failure of the engine fire shutoff switch
in the engine fire control module. The
Federal Aviation Administration is issuing
this AD to prevent mineral build-up on the
auxiliary power unit (APU) and engine fire
shutoff switches, which could lead to the
switches failing to discharge fire suppressant
to the affected fire zone and result in an
uncontrolled engine or APU fire and
consequent loss of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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Service Bulletin Reference
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–26A0127, dated July 17, 2003.
Initial and Repetitive Functional Tests
(g) At the later of the compliance times
specified in paragraphs (g)(1) and (g)(2) of
this AD, do a functional test of the APU and
engine fire shutoff switches, in accordance
with the service bulletin. Repeat the
functional test thereafter at intervals not to
exceed 18 months.
(1) Within 18 months since the date of
issuance of the original Airworthiness
Certificate or the original Export Certificate of
Airworthiness.
(2) Within 90 days after the effective date
of this AD.
Corrective Action for Failure of a Fire
Shutoff Switch
(h) If any APU or engine fire shutoff switch
fails during any functional test required by
paragraph (g) or (k) of this AD, before further
flight, replace the switch with a new or
serviceable switch, in accordance with the
service bulletin. Repeat the switch
replacement thereafter at intervals not to
exceed 36 months.
Initial and Repetitive Replacements of Fire
Shutoff Switches
(i) Within 18 months after the effective
date of this AD, replace all APU and engine
fire shutoff switches that have not been
previously replaced in accordance with
paragraph (h) of this AD with new or
serviceable switches, in accordance with the
service bulletin. Repeat the switch
replacement thereafter at intervals not to
exceed 36 months.
Optional Terminating Action: Deactivation
of Humidifier
(j) Accomplishment of the actions specified
in paragraphs (j)(1) and (j)(2) of this AD,
terminates the repetitive requirements of
paragraphs (g), (h), and (i) of this AD, except
as provided by paragraph (k) of this AD.
(1) Deactivate the Lucas humidifier, part
number (P/N) M01AA0101, M01AB0101,
M01AB0102, or M01AB0103, in accordance
with the service bulletin.
(2) Before further flight following the
deactivation specified in paragraph (j)(1) of
this AD, replace all APU and engine fire
shutoff switches with new or serviceable
switches, in accordance with the service
bulletin.
Reactivation of Lucas Humidifier
(k) For any airplane on which Lucas
humidifier, P/N M01AA0101, M01AB0101,
M01AB0102, or M01AB0103, is reactivated
after the effective date of this AD: Do the
actions required by paragraphs (k)(1) and
(k)(2) of this AD at the specified compliance
times.
(1) Within 18 months after reactivating the
humidifier, and thereafter at intervals not to
exceed 18 months, do the functional tests
required by paragraph (g) of this AD.
(2) Within 36 months after reactivating the
humidifier, and thereafter at intervals not to
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exceed 36 months, replace all APU and
engine fire shutoff switches that have not
been previously replaced in accordance with
paragraph (h) of this AD. Do the
replacements in accordance with paragraph
(i) of this AD.
Alternative Methods of Compliance (AMOC)
(l) The Manager, Seattle Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(m) You must use Boeing Alert Service
Bulletin 767–26A0127, dated July 17, 2003,
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
The Director of the Federal Register approved
the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. You can get copies of the
document from Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207. You can review
copies at the Docket Management Facility
office, U.S. Department of Transportation,
400 Seventh Street SW, room PL–401, Nassif
Building, Washington, DC; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call (202) 741–
6030, or go to: https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on
December 29, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–538 Filed 1–12–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2004–19357; Airspace
Docket No. 04–AAL–17]
Establishment of Class E Airspace;
Annette Island, Metlakatla, AK
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action establishes Class
E airspace at Annette Island, Metlakatla,
AK to provide adequate controlled
airspace to contain aircraft executing
Special Instrument Approach
Procedures. This Rule results in new
Class E airspace upward from 700 feet
(ft.) above the surface at Annette Island
Airport, AK.
DATES: Effective Date: 0901 UTC, March
17, 2005.
FOR FURTHER INFORMATION CONTACT:
Jesse Patterson, AAL–538G, Federal
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Aviation Administration, 222 West 7th
Avenue, Box 14, Anchorage, AK 99513–
7587; telephone number (907) 271–
5898; fax: (907) 271–2850; e-mail:
Jesse.ctr.Patterson@faa.gov. Internet
address: https://www.alaska.faa.gov/at.
SUPPLEMENTARY INFORMATION:
History
On Wednesday, November 3, 2004,
the FAA proposed to revise part 71 of
the Federal Aviation Regulations (14
CFR part 71) to create new Class E
airspace upward from 700 ft. above the
surface at Annette Island, AK (69 FR
63973). The action was proposed in
order to establish Class E airspace
sufficient in size to contain aircraft
while executing Special Instrument
Approach Procedures at the Annette
Island Airport. New Class E controlled
airspace extending upward from 700 ft.
above the surface within a 4.5-mile
radius of the Annette Island Airport is
established by this action. Interested
parties were invited to participate in
this rulemaking proceeding by
submitting written comments on the
proposal to the FAA. No public
comments have been received, thus, the
rule is adopted as proposed.
The area will be depicted on
aeronautical charts for pilot reference.
The coordinates for this airspace docket
are based on North American Datum 83.
The Class E airspace areas designated as
700/1200 foot transition areas are
published in paragraph 6005 of FAA
Order 7400.9M, Airspace Designations
and Reporting Points, dated August 30,
2004, and effective September 16, 2004,
which is incorporated by reference in 14
CFR 71.1. The Class E airspace
designation listed in this document will
be published subsequently in the Order.
The Rule
This revision to 14 CFR part 71
establishes Class E airspace at Annette
Island Airport, Alaska. This additional
Class E airspace was created to
accommodate aircraft executing Special
Instrument Flight Procedures and will
be depicted on aeronautical charts for
pilot reference. The intended effect of
this rule is to provide adequate
controlled airspace for IFR operations at
Annette Island Airport, Alaska.
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. It, therefore—(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)
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[Federal Register Volume 70, Number 9 (Thursday, January 13, 2005)]
[Rules and Regulations]
[Pages 2339-2342]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-538]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20010; Directorate Identifier 2003-NM-224-AD;
Amendment 39-13938; AD 2005-01-13]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 767-300 series airplanes. This AD requires
repetitive functional tests and repetitive replacements of the
auxiliary power unit (APU) and engine fire shutoff switches. This
proposal also provides an optional terminating action for the
repetitive functional tests and replacements. This AD is prompted by a
report of the failure of the engine fire shutoff switch in the engine
fire control module. We are issuing this AD to prevent mineral build-up
on the APU and engine fire shutoff switches, which could lead to the
switches failing to discharge fire suppressant to the affected fire
zone and result in an uncontrolled engine or APU fire and consequent
loss of the airplane.
DATES: Effective January 28, 2005. The incorporation by reference of a
certain publication listed in the AD is approved
[[Page 2340]]
by the Director of the Federal Register as of January 28, 2005.
We must receive comments on this AD by March 14, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This
docket number is FAA-2005-20010; the directorate identifier for this
docket is 2003-NM-224-AD.
Examining the Dockets
You can examine the AD docket on the Internet at https://
dms.dot.gov, or in person in the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
(DMS) receives them.
FOR FURTHER INFORMATION CONTACT: Bernie Gonzalez, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6498; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: This AD is prompted by a report of the
failure of the engine fire shutoff switch in the engine fire control
module, which resulted in the inability to stow the thrust reverser on
a certain Boeing Model 767 series airplane. On this installation the
thrust reverser is operated by engine pneumatic bleed air, which is
regulated by a spring-loaded-closed pressure regulating and shutoff
valve (PRSOV). The PRSOV requires electrical power to stay open against
the spring force. Its power supply is routed through the engine fire
shutoff switch. The electrical contacts for the thrust reverser inside
the engine fire shutoff switch are normally in the closed position.
When the engine fire shutoff switch is pulled, during a fire or test,
the power supplied to the thrust reverser PRSOV is removed and the
valve closes off the engine bleed air, leaving the thrust reverser in
the last commanded position. Investigation of the reported incident
revealed that certain flight deck humidifiers distribute unfiltered air
containing minerals from the potable water supply. The humidified air
contaminates the auxiliary power unit (APU) and engine fire shutoff
switches and may result in mineral build-up on switch contacts. The
contamination within the fire shutoff switch gradually builds up,
causing an increase in contact resistance. In the case of the thrust
reverser, this contact resistance was high enough that the power
supplied to the PRSOV was insufficient to hold the valve open. The
PRSOV closed, leaving the thrust reverser in the deployed state. This
same contamination can build up on the fire extinguishing switch
contacts inside the APU and engine fire switches. Mineral build-up on
the APU and engine fire shutoff switches, if not corrected, could lead
to the switches failing to discharge fire suppressant to the affected
fire zone and result in an uncontrolled engine or APU fire and
consequent loss of the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 767-26A0127, dated
July 17, 2003. The service bulletin describes the following procedures:
1. Doing repetitive functional tests of the APU and engine fire
shutoff switches;
2. Doing repetitive replacements of the APU and engine fire shutoff
switches with new or serviceable switches; and
3. Deactivating the Lucas (also known as TRW Systemes
Aeronautiques) flight deck humidifier, part numbers (P/N) M01AA0101,
M01AB0101, M01AB0102, or M01AB0103, which eliminates the need for the
repetitive functional tests and replacements.
We have determined that accomplishment of the actions specified in
the service information will adequately address the unsafe condition.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design that may be
registered in the U.S. at some time in the future. Therefore, this AD
is being issued to prevent mineral build-up on APU and engine fire
shutoff switches, which could lead to the switches failing to discharge
fire suppressant to the affected fire zone and result in an
uncontrolled engine fire and consequent loss of the airplane. This AD
requires repetitive functional tests and repetitive replacements of the
APU and engine fire shutoff switches. This proposal also provides an
optional terminating action for the repetitive functional tests and
replacements. You must do these actions in accordance with the service
information described previously, except as discussed under
``Differences Between the AD and the Service Bulletin.''
Differences Between the AD and the Service Bulletin
Operators should note that the service bulletin specifies the
initial compliance time as ``after the airplane has 12 calendar months
of service but within 18 calendar months since airplane delivery. * *
*'' This AD, however, specifies the initial compliance time as within
18 months since the date of issuance of the original Airworthiness
Certificate or the original Export Certificate of Airworthiness. This
decision is based on our determination that ``since airplane delivery''
may be interpreted differently by different operators. We find that
this terminology is generally understood within the industry and
records will always exist that establish these dates with certainty.
This AD also omits reference to ``after the airplane has 12 calendar
months of service,'' since accomplishing the initial actions within 18
months of service provides an acceptable level of safety. Thus the
compliance time specified in this AD includes any airplanes that may
have been operating since delivery.
Operators should also note that the service bulletin states,
``Operators who perform the 90 calendar day inspection and the 18
calendar month switch servicing can avoid the required test interval
shown in Figure 1, by deactivation of the Lucas (also known as TRW
Systemes Aeronautiques) Flight Deck Humidifier.'' This AD, however,
specifies that if an operator deactivates the flight deck humidifier,
all APU and engine fire shutoff switches must be
[[Page 2341]]
replaced with new or serviceable switches before further flight. We
have determined that if a flight deck humidifier is deactivated shortly
before any required replacement or required functional test, it might
be possible for any switch to have a latent type of failure due to the
previous exposure to moisture and minerals from the humidifier. To
address this unsafe condition, we have added a requirement to paragraph
(j) of this AD to replace all switches after deactivating the flight
deck humidifier. We have also added requirements to paragraph (k) of
this AD to ensure an operator performs the repetitive functional tests
and replacements of switches after reactivating the flight deck
humidifier.
Costs of Compliance
None of the airplanes affected by this action are on the U.S.
Register. All airplanes affected by this AD are currently operated by
non-U.S. operators under foreign registry; therefore, they are not
directly affected by this AD action. However, we consider this AD
necessary to ensure that the unsafe condition is addressed if any
affected airplane is imported and placed on the U.S. Register in the
future.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required functional test would take about 2 work
hours per switch, at an average labor rate of $65 per work hour. We
estimate there are 3 switches per airplane. No parts would be required.
Based on these figures, the estimated cost of the AD would be $390 per
airplane, per testing cycle.
If an affected airplane is imported and placed on the U.S. Register
in the future, the required switch replacement would take about 2 work
hours per switch, at an average labor rate of $65 per work hour.
Required parts would cost about $1,000 per switch, if replaced with a
serviceable switch. Based on these figures, the estimated cost of the
AD would be $1,130 per switch, per replacement.
FAA's Determination of the Effective Date
No airplane affected by this AD is currently on the U.S. Register.
Therefore, providing notice and opportunity for public comment is
unnecessary before this AD is issued, and this AD may be made effective
in less than 30 days after it is published in the Federal Register.
Comments Invited
Although this is a final rule that was not preceded by notice and
an opportunity for public comment, we invite you to submit any written
relevant data, views, or arguments regarding this AD. Send your
comments to an address listed under ADDRESSES. Include ``Docket No.
FAA-2005-20010; Directorate Identifier 2003-NM-224-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
AD. We will consider all comments received by the closing date and may
amend the AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of our docket
Web site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You may review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you may visit
https://dms.dot.gov.
Authority for This Rulemaking
The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. Subtitle I, section 106
describes the authority of the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more detail the scope of the agency's
authority.
This rulemaking is promulgated under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this AD.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that the 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. 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2005-01-13 Boeing: Amendment 39-13938. Docket No. FAA-2005-20010;
Directorate Identifier 2003-NM-224-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
28, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 767-300 series airplanes,
certificated in any category; as listed in Boeing Alert Service
Bulletin 767-26A0127, dated July 17, 2003.
Unsafe Condition
(d) This AD was prompted by a report of the failure of the
engine fire shutoff switch in the engine fire control module. The
Federal Aviation Administration is issuing this AD to prevent
mineral build-up on the auxiliary power unit (APU) and engine fire
shutoff switches, which could lead to the switches failing to
discharge fire suppressant to the affected fire zone and result in
an uncontrolled engine or APU fire and consequent loss of the
airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
[[Page 2342]]
Service Bulletin Reference
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
26A0127, dated July 17, 2003.
Initial and Repetitive Functional Tests
(g) At the later of the compliance times specified in paragraphs
(g)(1) and (g)(2) of this AD, do a functional test of the APU and
engine fire shutoff switches, in accordance with the service
bulletin. Repeat the functional test thereafter at intervals not to
exceed 18 months.
(1) Within 18 months since the date of issuance of the original
Airworthiness Certificate or the original Export Certificate of
Airworthiness.
(2) Within 90 days after the effective date of this AD.
Corrective Action for Failure of a Fire Shutoff Switch
(h) If any APU or engine fire shutoff switch fails during any
functional test required by paragraph (g) or (k) of this AD, before
further flight, replace the switch with a new or serviceable switch,
in accordance with the service bulletin. Repeat the switch
replacement thereafter at intervals not to exceed 36 months.
Initial and Repetitive Replacements of Fire Shutoff Switches
(i) Within 18 months after the effective date of this AD,
replace all APU and engine fire shutoff switches that have not been
previously replaced in accordance with paragraph (h) of this AD with
new or serviceable switches, in accordance with the service
bulletin. Repeat the switch replacement thereafter at intervals not
to exceed 36 months.
Optional Terminating Action: Deactivation of Humidifier
(j) Accomplishment of the actions specified in paragraphs (j)(1)
and (j)(2) of this AD, terminates the repetitive requirements of
paragraphs (g), (h), and (i) of this AD, except as provided by
paragraph (k) of this AD.
(1) Deactivate the Lucas humidifier, part number (P/N)
M01AA0101, M01AB0101, M01AB0102, or M01AB0103, in accordance with
the service bulletin.
(2) Before further flight following the deactivation specified
in paragraph (j)(1) of this AD, replace all APU and engine fire
shutoff switches with new or serviceable switches, in accordance
with the service bulletin.
Reactivation of Lucas Humidifier
(k) For any airplane on which Lucas humidifier, P/N M01AA0101,
M01AB0101, M01AB0102, or M01AB0103, is reactivated after the
effective date of this AD: Do the actions required by paragraphs
(k)(1) and (k)(2) of this AD at the specified compliance times.
(1) Within 18 months after reactivating the humidifier, and
thereafter at intervals not to exceed 18 months, do the functional
tests required by paragraph (g) of this AD.
(2) Within 36 months after reactivating the humidifier, and
thereafter at intervals not to exceed 36 months, replace all APU and
engine fire shutoff switches that have not been previously replaced
in accordance with paragraph (h) of this AD. Do the replacements in
accordance with paragraph (i) of this AD.
Alternative Methods of Compliance (AMOC)
(l) The Manager, Seattle Aircraft Certification Office, FAA, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin 767-26A0127,
dated July 17, 2003, to perform the actions that are required by
this AD, unless the AD specifies otherwise. The Director of the
Federal Register approved the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You
can get copies of the document from Boeing Commercial Airplanes,
P.O. Box 3707, Seattle, Washington 98124-2207. You can review copies
at the Docket Management Facility office, U.S. Department of
Transportation, 400 Seventh Street SW, room PL-401, Nassif Building,
Washington, DC; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to: https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on December 29, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-538 Filed 1-12-05; 8:45 am]
BILLING CODE 4910-13-P
