Airworthiness Directives; Boeing Model 777-200, -300, and -300ER Series Airplanes, 34808-34811 [06-5428]
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34808
Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking 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 rulemaking
action.
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 this AD:
(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.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘AD Docket No. 95–ANE–10–
AD’’ in your request.
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 Federal Aviation Administration
amends 14 CFR part 39 as follows:
jlentini on PROD1PC65 with RULES
I
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
16:11 Jun 15, 2006
Jkt 208001
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–9346 (60 FR
46758, September 8, 1995) and by
adding a new airworthiness directive,
Amendment 39–14650, to read as
follows:
I
2006–12–24 General Electric Company:
Amendment 39–14650. Docket No. 95–
ANE–10–AD.
Effective Date
(a) This AD becomes effective July 21,
2006.
Affected ADs
(b) This AD supersedes AD 95–17–15,
Amendment 39–9346.
Applicability
(c) This AD applies to General Electric (GE)
CF6–45/–50 and CF6–80A turbofan engines
with left-hand side links part numbers (P/Ns)
9204M94P01, 9204M94P03, and
9346M99P01, and right-hand side links, P/Ns
9204M94P02, 9204M94P04, and
9346M99P02, installed on the five-link
forward engine mount assembly (also known
as Configuration 2). These engines are
installed on, but not limited to, Boeing
DC10–15, DC10–30, 767, and 747 series
airplanes and Airbus Industrie A300 and
A310 series airplanes.
Unsafe Condition
(d) This AD results from a report of a
cracked side link. We are issuing this AD to
prevent failure of the side links and possible
engine separation from the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed at
every exposure of the side link.
Inspecting and Refurbishing the Side Links
(f) Inspect and refurbish each side link at
every exposure of the side links. Use the
following GE Aircraft Engines (GEAE) service
bulletins (SBs):
(1) For CF6–45/–50 series engines, use 3.A.
through 3.E. of the Accomplishment
Instructions of GEAE SB CF6–50 S/B 72–
1255, dated January 26, 2005.
(2) For CF6–80A series engines, use 3.A.
through 3.E. of the Accomplishment
Instructions of GEAE SB CF6–80A S/B 72–
0797, dated January 26, 2005.
Definition of Exposure of Side Link
(g) A side link is exposed when one or
more bolts that attach the side links to the fan
frame—front high pressure compressor case
are removed, or when the bolt attaching the
side link to the mount platform is removed.
Alternative Methods of Compliance
(h) 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.
PART 39—AIRWORTHINESS
DIRECTIVES
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§ 39.13
Material Incorporated by Reference
(i) You must use General Electric Aircraft
Engines Service Bulletins CF6–50 S/B 72–
PO 00000
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1255, dated January 26, 2005, and CF6–80A
S/B 72–0797, dated January 26, 2005 to
perform the actions required by this AD. The
Director of the Federal Register approved the
incorporation by reference of these service
bulletins in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. You can get a copy of this
service information from General Electric
Aircraft Engines, CF6 Distribution Clerk,
Room 132, 111 Merchant Street, Cincinnati,
OH 45246, or at the Office of the Federal
Register, 800 North Capitol Street, NW., Suite
700, Washington, DC.
Related Information
(j) None.
Issued in Burlington, Massachusetts, on
June 8, 2006.
Thomas Boudreau,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 06–5426 Filed 6–15–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24173; Directorate
Identifier 2005–NM–262–AD; Amendment
39–14652; AD 2006–12–26]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 777–200, –300, and –300ER
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 777–200, –300, and
–300ER series airplanes. This AD
requires a one-time inspection of the
first bonding jumper aft of the bulkhead
fitting to detect damage or failure and to
determine the mechanical integrity of its
electrical bonding path, and repair if
necessary; measuring the bonding
resistance between the fitting for the
fuel feed tube and the front spar in the
left and right main fuel tanks, and
repairing the bonding if necessary; and
applying additional sealant to
completely cover the bulkhead fittings
inside the fuel tanks. This AD results
from fuel system reviews conducted by
the manufacturer. We are issuing this
AD to prevent arcing or sparking during
a lightning strike at the interface
between the bulkhead fittings of the
engine fuel feed tube and the front spar
inside the fuel tank. This arcing or
sparking could provide a potential
ignition source inside the fuel tank,
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Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
which, in combination with flammable
fuel vapors, could result in fuel tank
explosions and consequent loss of the
airplane.
DATES: This AD becomes effective July
21, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of July 21, 2006.
ADDRESSES: You may examine the 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., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Margaret Langsted, Aerospace Engineer,
Propulsion Branch, ANM–140S, Seattle
Aircraft Certification Office, FAA, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 917–6500;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
jlentini on PROD1PC65 with RULES
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at 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 street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Boeing Model 777
airplanes. That NPRM was published in
the Federal Register on March 21, 2006
(71 FR 14126). That NPRM proposed to
require a one-time inspection of the first
bonding jumper aft of the bulkhead
fitting to detect damage or failure and to
determine the mechanical integrity of its
electrical bonding path, and repair if
necessary; measuring the bonding
resistance between the fitting for the
fuel feed tube and the front spar in the
left and right main fuel tanks, and
repairing the bonding if necessary; and
applying additional sealant to
completely cover the bulkhead fittings
inside the fuel tanks.
Comments
We provided the public the
opportunity to participate in the
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16:11 Jun 15, 2006
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development of this AD. We have
considered the comments received.
Support for the NPRM
Boeing concurs with the NPRM.
Request To Revise the Service Bulletin
Japan Airlines (JAL) suggests that
Boeing should revise Boeing Special
Attention Service Bulletin 777–28–
0044, Revision 1, dated December 20,
2005, to incorporate the repair
instructions for the bonding path rather
than having them separate from the
service bulletin. (This service bulletin
was referenced as the appropriate
source of service information for
accomplishing the actions in the
NPRM.) JAL states that it would be
simpler if the AD referred to the service
bulletin for the whole work instructions,
including all repair procedures.
We partially agree. We agree with JAL
that having all repair procedures in one
place can be simpler for operators. We
do not agree that Boeing should revise
its service bulletin for this reason, nor
can we request a manufacturer to revise
a service bulletin to make addressing an
unsafe condition more convenient.
Waiting to include a revised service
bulletin in this action would delay
addressing an unsafe condition. In
addition, manufacturers’ service
information often refers to procedures in
various maintenance manuals for a
number of reasons (e.g., to keep
procedures in the service bulletin from
becoming too cumbersome, or because
the procedure is an industry best
practice). In this case, the referenced
service bulletin refers to Chapter 28–00–
00 of the Boeing 777 Aircraft
Maintenance Manual (AMM) for doing
the general visual inspection of the first
bonding jumper aft of the bulkhead
fitting to detect damage or failure and to
determine the mechanical integrity of its
electrical bonding path. We assume
some of JAL’s issue stems from the
statement in paragraph (f)(1) of the
NPRM that these conditions must be
repaired according to a method we
approve, and that Chapter 28–00–00 of
the Boeing 777 AMM is one approved
method. We included that statement in
paragraph (f)(1) because although the
service bulletin implies repair for the
bonding path in accordance with the
AMM chapter, the statement in the
service bulletin is not explicit and could
be confusing. We have not changed the
final rule in this regard.
Request To Revise Cost Estimate
Air Transport Association (ATA), on
behalf of American Airlines, requests
that we revise the cost estimate.
American Airlines quotes an ‘‘AD
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34809
memo’’ that reads ‘‘FAA estimates that
46 airplanes of U.S. registry would be
affected by this rulemaking.’’ American
Airlines points out that it has 45
affected airplanes, and that there are
three other U.S. operators that also have
affected airplanes. American Airlines
also does not concur with the statement
in the NPRM that the cost of the
proposed actions would be $640 per
airplane for eight hours of work.
Although American Airlines
understands that the FAA does not
consider access time when calculating
the cost to comply with an AD,
American Airlines believes it is
important to note that this inspection
and sealant application requires
complete draining and venting of the
fuel tanks, which alone could take eight
hours. In total, American Airlines
estimates the inspection and sealant
application will require approximately
48 work hours per airplane at a cost of
$202,586.
We partially agree with the
commenters. We agree that there are
more than 45 airplanes of U.S. registry
affected by the actions in the NPRM. We
are not familiar with an ‘‘AD memo,’’
which could have been a summary of
the NPRM initiated by another source.
The number of affected airplanes listed
in the NPRM is 131 rather than 45. We
have revised the ‘‘Costs of Compliance’’
paragraph to reflect this information.
We do not agree with revising the
number of work hours in the cost
estimate. As American Airlines points
out, we do not consider access time
when calculating the cost of an AD. The
cost information below describes only
the direct costs of the specific actions
required by this AD. Based on the best
data available, the manufacturer
provided the number of work hours (8)
necessary to do the required actions.
This number represents the time
necessary to perform only the actions
actually required by this AD. We
recognize that, in doing the actions
required by an AD, operators may incur
incidental costs in addition to the direct
costs. The cost analysis in AD
rulemaking actions excludes the costs of
the time required to gain access and
close up, as American points out, but it
also excludes other incidental costs
such as the time necessary for planning,
or time for other administrative actions.
All of these costs may vary significantly
among operators and are almost
impossible to calculate. We have not
changed the final rule in this regard.
Explanation of Change in Applicability
We have revised the applicability of
this final rule to match the most current
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Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
type certificate data sheet for the
affected airplanes.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the change described
previously. We have determined that
this change will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
There are about 497 airplanes of the
affected design in the worldwide fleet.
This AD affects about 131 airplanes of
U.S. registry. The actions take about 8
work hours per airplane, at an average
labor rate of $80 per work hour. Based
on these figures, the estimated cost of
the AD for U.S. operators is $83,840, or
$640 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. 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.
We are issuing this rulemaking 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 rulemaking
action.
jlentini on PROD1PC65 with RULES
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 this AD:
(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,
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16:11 Jun 15, 2006
Jkt 208001
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 and placed it in the AD docket.
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
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
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2006–12–26 Boeing: Amendment 39–14652.
Docket No. FAA–2006–24173;
Directorate Identifier 2005–NM–262–AD.
Effective Date
(a) This AD becomes effective July 21,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777–
200, –300, and –300ER series airplanes,
certificated in any category; as identified in
Boeing Special Attention Service Bulletin
777–28–0044, Revision 1, dated December
20, 2005.
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent arcing or
sparking during a lightning strike at the
interface between the bulkhead fittings of the
engine fuel feed tube and the front spar
inside the fuel tank. This arcing or sparking
could provide a potential ignition source
inside the fuel tank, which, in combination
with flammable fuel vapors, could result in
fuel tank explosions 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.
Inspection and Corrective Actions
(f) Within 60 months after the effective
date of this AD, do the actions specified in
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Fmt 4700
Sfmt 4700
paragraphs (f)(1), (f)(2), and (f)(3) of this AD
for the bulkhead fittings of the engine fuel
feed tube for the left and right main fuel
tanks. Do all actions in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–28–
0044, Revision 1, dated December 20, 2005.
(1) Do a general visual inspection of the
first bonding jumper aft of the bulkhead
fitting to detect damage or failure and to
determine the mechanical integrity of its
electrical bonding path. If any damage or
failure is found during this inspection or if
the mechanical integrity of the bonding path
is compromised: Before further flight, repair
according to a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA. Chapter 28–00–00 of the Boeing
777 Aircraft Maintenance Manual is one
approved method.
(2) Measure the bonding resistance
between the fitting for the fuel feed tube and
the front spar in the left main fuel tank. If the
bonding resistance exceeds 0.001 ohm:
Before further flight, repair the bonding in
accordance with the service bulletin.
(3) Apply additional sealant to completely
cover the bulkhead fitting inside the fuel
tank.
Actions Accomplished in Accordance With
Previous Revision of Service Bulletin
(g) Actions done before the effective date
of this AD in accordance with Boeing Special
Attention Service bulletin 777–28–0044,
dated February 3, 2005, are acceptable for
compliance with the requirements of
paragraph (f) of this AD.
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Material Incorporated by Reference
(i) You must use Boeing Special Attention
Service Bulletin 777–28–0044, Revision 1,
dated December 20, 2005, 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. Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for a copy of this
service information. You may review copies
at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
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Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations
Issued in Renton, Washington, on June 8,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5428 Filed 6–15–06; 8:45 am]
Issued in Burlington, MA, on June 9, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 06–5427 Filed 6–15–06; 8:45 am]
BILLING CODE 4910–13–P
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Federal Aviation Administration
14 CFR Part 39
14 CFR Part 39
[Docket No. FAA–2005–21331; Directorate
Identifier 2005–NE–07–AD; Amendment 39–
14604; AD 2006–10–21]
[Docket No. FAA–2006–25030; Directorate
Identifier 2006–NM–109–AD; Amendment
39–14649; AD 2006–12–23]
RIN 2120–AA64
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–100, –200, –200C, –300,
–400, and –500 Series Airplanes
Airworthiness Directives; Engine
Components Incorporated (ECi)
Reciprocating Engine Connecting
Rods; Correction
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
Federal Aviation
Administration, DOT.
AGENCY:
ACTION:
Final rule; correction.
This document makes a
correction to Airworthiness Directive
(AD) 2006–10–21. That AD applies to
Engine Components Incorporated (ECi)
reciprocating engine connecting rods.
We published AD 2006–10–21 in the
Federal Register on May 18, 2006, (71
FR 28769). An incorrect amendment
number exists under the § 39.13
amended heading. This document
corrects the amendment number. In all
other respects, the original document
remains the same.
SUMMARY:
DATES:
Effective Date: Effective June 16,
2006.
FOR FURTHER INFORMATION CONTACT:
Peter Hakala, Aerospace Engineer,
Special Certification Office, FAA,
Rotorcraft Directorate, 2601 Meacham
Blvd., Fort Worth, TX 76193; telephone
(817) 222–5145; fax (817) 222–5785.
A final
rule AD, FR Doc. 06–4046, that applies
to Engine Components Incorporated
(ECi) reciprocating engine connecting
rods was published in the Federal
Register on May 18, 2006, (71 FR
28769). The following correction is
needed:
SUPPLEMENTARY INFORMATION:
jlentini on PROD1PC65 with RULES
§ 39.13
[Corrected]
On page 28771, in the third column,
under § 39.13 [Amended], in the fifth
and sixth lines, ‘‘Amendment 39–
14605’’ is corrected to read
‘‘Amendment 39–14604’’.
I
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SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain Boeing Model
737–100, –200, –200C, –300, –400, and
–500 series airplanes. The existing AD
currently requires initial and repetitive
inspections of the elevator tab assembly
to find any damage or discrepancy; and
corrective actions if necessary. This new
AD adds certain new inspections and
removes certain existing inspections.
This AD results from additional reports
of airframe vibrations of the elevator tab
during flight on airplanes inspected per
the existing AD; subsequently,
considerable damage was done to the
elevator tab, elevator, and horizontal
stabilizer. In several incidents, a portion
of the elevator tab separated from the
airplane. We are issuing this AD to
prevent excessive in-flight vibrations of
the elevator tab, which could lead to
loss of the elevator tab and consequent
loss of controllability of the airplane.
DATES: This AD becomes effective July
3, 2006.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of July 3, 2006.
On February 19, 2002 (67 FR 1603,
January 14, 2002), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Service Bulletin 737–55A1070, Revision
1, including appendices A, B, and C,
dated May 10, 2001.
We must receive any comments on
this AD by August 15, 2006.
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34811
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.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
You may examine the contents of the
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, Washington, DC.
This docket number is FAA–2006–
25030; the directorate identifier for this
docket is 2006–NM–109–AD.
FOR FURTHER INFORMATION CONTACT:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
Discussion
On December 28, 2001, we issued AD
2002–01–01, amendment 39–12592 (67
FR 1603, January 14, 2002). That AD
applies to certain Boeing Model 737–
100, –200, –200C, –300, –400, and –500
series airplanes. That AD requires initial
and repetitive inspections of the
elevator tab assembly to find any
damage or discrepancy; and corrective
actions if necessary. That AD resulted
from several reports indicating highfrequency airframe vibrations of the
elevator tab during flight. The actions
specified in that AD are intended to
prevent excessive in-flight vibrations of
the elevator tab, which could lead to
loss of the elevator tab and consequent
loss of controllability of the airplane.
Actions Since AD was Issued
Since we issued AD 2002–01–01, we
have received additional reports of
airframe vibrations of the elevator tab
during flight on airplanes inspected per
E:\FR\FM\16JNR1.SGM
16JNR1
]]>Agencies
[Federal Register Volume 71, Number 116 (Friday, June 16, 2006)]
[Rules and Regulations]
[Pages 34808-34811]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5428]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24173; Directorate Identifier 2005-NM-262-AD;
Amendment 39-14652; AD 2006-12-26]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 777-200, -300, and -300ER
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 777-200, -300, and -300ER series airplanes. This
AD requires a one-time inspection of the first bonding jumper aft of
the bulkhead fitting to detect damage or failure and to determine the
mechanical integrity of its electrical bonding path, and repair if
necessary; measuring the bonding resistance between the fitting for the
fuel feed tube and the front spar in the left and right main fuel
tanks, and repairing the bonding if necessary; and applying additional
sealant to completely cover the bulkhead fittings inside the fuel
tanks. This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent arcing or sparking
during a lightning strike at the interface between the bulkhead
fittings of the engine fuel feed tube and the front spar inside the
fuel tank. This arcing or sparking could provide a potential ignition
source inside the fuel tank,
[[Page 34809]]
which, in combination with flammable fuel vapors, could result in fuel
tank explosions and consequent loss of the airplane.
DATES: This AD becomes effective July 21, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of July 21,
2006.
ADDRESSES: You may examine the 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., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Margaret Langsted, Aerospace Engineer,
Propulsion Branch, ANM-140S, Seattle Aircraft Certification Office,
FAA, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6500; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at 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 street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Boeing Model
777 airplanes. That NPRM was published in the Federal Register on March
21, 2006 (71 FR 14126). That NPRM proposed to require a one-time
inspection of the first bonding jumper aft of the bulkhead fitting to
detect damage or failure and to determine the mechanical integrity of
its electrical bonding path, and repair if necessary; measuring the
bonding resistance between the fitting for the fuel feed tube and the
front spar in the left and right main fuel tanks, and repairing the
bonding if necessary; and applying additional sealant to completely
cover the bulkhead fittings inside the fuel tanks.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Support for the NPRM
Boeing concurs with the NPRM.
Request To Revise the Service Bulletin
Japan Airlines (JAL) suggests that Boeing should revise Boeing
Special Attention Service Bulletin 777-28-0044, Revision 1, dated
December 20, 2005, to incorporate the repair instructions for the
bonding path rather than having them separate from the service
bulletin. (This service bulletin was referenced as the appropriate
source of service information for accomplishing the actions in the
NPRM.) JAL states that it would be simpler if the AD referred to the
service bulletin for the whole work instructions, including all repair
procedures.
We partially agree. We agree with JAL that having all repair
procedures in one place can be simpler for operators. We do not agree
that Boeing should revise its service bulletin for this reason, nor can
we request a manufacturer to revise a service bulletin to make
addressing an unsafe condition more convenient. Waiting to include a
revised service bulletin in this action would delay addressing an
unsafe condition. In addition, manufacturers' service information often
refers to procedures in various maintenance manuals for a number of
reasons (e.g., to keep procedures in the service bulletin from becoming
too cumbersome, or because the procedure is an industry best practice).
In this case, the referenced service bulletin refers to Chapter 28-00-
00 of the Boeing 777 Aircraft Maintenance Manual (AMM) for doing the
general visual inspection of the first bonding jumper aft of the
bulkhead fitting to detect damage or failure and to determine the
mechanical integrity of its electrical bonding path. We assume some of
JAL's issue stems from the statement in paragraph (f)(1) of the NPRM
that these conditions must be repaired according to a method we
approve, and that Chapter 28-00-00 of the Boeing 777 AMM is one
approved method. We included that statement in paragraph (f)(1) because
although the service bulletin implies repair for the bonding path in
accordance with the AMM chapter, the statement in the service bulletin
is not explicit and could be confusing. We have not changed the final
rule in this regard.
Request To Revise Cost Estimate
Air Transport Association (ATA), on behalf of American Airlines,
requests that we revise the cost estimate. American Airlines quotes an
``AD memo'' that reads ``FAA estimates that 46 airplanes of U.S.
registry would be affected by this rulemaking.'' American Airlines
points out that it has 45 affected airplanes, and that there are three
other U.S. operators that also have affected airplanes. American
Airlines also does not concur with the statement in the NPRM that the
cost of the proposed actions would be $640 per airplane for eight hours
of work. Although American Airlines understands that the FAA does not
consider access time when calculating the cost to comply with an AD,
American Airlines believes it is important to note that this inspection
and sealant application requires complete draining and venting of the
fuel tanks, which alone could take eight hours. In total, American
Airlines estimates the inspection and sealant application will require
approximately 48 work hours per airplane at a cost of $202,586.
We partially agree with the commenters. We agree that there are
more than 45 airplanes of U.S. registry affected by the actions in the
NPRM. We are not familiar with an ``AD memo,'' which could have been a
summary of the NPRM initiated by another source. The number of affected
airplanes listed in the NPRM is 131 rather than 45. We have revised the
``Costs of Compliance'' paragraph to reflect this information.
We do not agree with revising the number of work hours in the cost
estimate. As American Airlines points out, we do not consider access
time when calculating the cost of an AD. The cost information below
describes only the direct costs of the specific actions required by
this AD. Based on the best data available, the manufacturer provided
the number of work hours (8) necessary to do the required actions. This
number represents the time necessary to perform only the actions
actually required by this AD. We recognize that, in doing the actions
required by an AD, operators may incur incidental costs in addition to
the direct costs. The cost analysis in AD rulemaking actions excludes
the costs of the time required to gain access and close up, as American
points out, but it also excludes other incidental costs such as the
time necessary for planning, or time for other administrative actions.
All of these costs may vary significantly among operators and are
almost impossible to calculate. We have not changed the final rule in
this regard.
Explanation of Change in Applicability
We have revised the applicability of this final rule to match the
most current
[[Page 34810]]
type certificate data sheet for the affected airplanes.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the change described previously.
We have determined that this change will neither increase the economic
burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 497 airplanes of the affected design in the
worldwide fleet. This AD affects about 131 airplanes of U.S. registry.
The actions take about 8 work hours per airplane, at an average labor
rate of $80 per work hour. Based on these figures, the estimated cost
of the AD for U.S. operators is $83,840, or $640 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. 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.
We are issuing this rulemaking 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
rulemaking action.
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 this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2006-12-26 Boeing: Amendment 39-14652. Docket No. FAA-2006-24173;
Directorate Identifier 2005-NM-262-AD.
Effective Date
(a) This AD becomes effective July 21, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777-200, -300, and -300ER
series airplanes, certificated in any category; as identified in
Boeing Special Attention Service Bulletin 777-28-0044, Revision 1,
dated December 20, 2005.
Unsafe Condition
(d) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent arcing or sparking
during a lightning strike at the interface between the bulkhead
fittings of the engine fuel feed tube and the front spar inside the
fuel tank. This arcing or sparking could provide a potential
ignition source inside the fuel tank, which, in combination with
flammable fuel vapors, could result in fuel tank explosions 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.
Inspection and Corrective Actions
(f) Within 60 months after the effective date of this AD, do the
actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of this
AD for the bulkhead fittings of the engine fuel feed tube for the
left and right main fuel tanks. Do all actions in accordance with
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 777-28-0044, Revision 1, dated December 20, 2005.
(1) Do a general visual inspection of the first bonding jumper
aft of the bulkhead fitting to detect damage or failure and to
determine the mechanical integrity of its electrical bonding path.
If any damage or failure is found during this inspection or if the
mechanical integrity of the bonding path is compromised: Before
further flight, repair according to a method approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA. Chapter
28-00-00 of the Boeing 777 Aircraft Maintenance Manual is one
approved method.
(2) Measure the bonding resistance between the fitting for the
fuel feed tube and the front spar in the left main fuel tank. If the
bonding resistance exceeds 0.001 ohm: Before further flight, repair
the bonding in accordance with the service bulletin.
(3) Apply additional sealant to completely cover the bulkhead
fitting inside the fuel tank.
Actions Accomplished in Accordance With Previous Revision of Service
Bulletin
(g) Actions done before the effective date of this AD in
accordance with Boeing Special Attention Service bulletin 777-28-
0044, dated February 3, 2005, are acceptable for compliance with the
requirements of paragraph (f) of this AD.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Material Incorporated by Reference
(i) You must use Boeing Special Attention Service Bulletin 777-
28-0044, Revision 1, dated December 20, 2005, 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. Contact Boeing Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124-2207, for a copy of this service
information. You may review copies at the Docket Management
Facility, U.S. Department of Transportation, 400 Seventh Street,
SW., Room PL-401, Nassif Building, Washington, DC; on the Internet
at https://dms.dot.gov; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at the NARA, call (202) 741-6030, or go to https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
[[Page 34811]]
Issued in Renton, Washington, on June 8, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-5428 Filed 6-15-06; 8:45 am]
BILLING CODE 4910-13-P
