Airworthiness Directives; Boeing Model 757-200, 757-200PF, and 757-300 Series Airplanes, 45895-45898 [E8-18222]
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Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance (AMOC)
according to paragraph (k) of this AD. The
request should include a description of
changes to the required inspections that will
ensure the continued operational safety of
the airplane.
Terminating Action for AWLs Revision
(j) Incorporating AWL No. 28–AWL–19 and
No. 28–AWL–20 into the AWLs section of the
ICA in accordance with paragraph (g)(2) of
AD 2008–11–13, amendment 39–15536,
terminates the action required by paragraph
(h) of this AD.
Inspection
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle ACO, FAA,
ATTN: Margaret Langsted, Aerospace
Engineer, Propulsion Branch, ANM–140S,
FAA, SACO, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6500; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(f) Within 60 months after the effective
date of this AD, do an inspection of the MOV
actuators of the main and center fuel tanks
for part number MA20A1001–1, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
777–28A0034, dated August 2, 2007.
Issued in Renton, Washington, on July 29,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–18211 Filed 8–6–08; 8:45 am]
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent electrical
current from flowing through a motor
operated valve (MOV) actuator into a fuel
tank, which could create a potential ignition
source inside the fuel tank. This condition,
in combination with flammable fuel vapors,
could result in a fuel tank explosion and
consequent loss of the airplane.
Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
BILLING CODE 4910–13–P
Replacement
(g) If any part number MA20A1001–1 is
found during the inspection required by
paragraph (f) of this AD, within 60 months
after the effective date of this AD, do the
actions specified in paragraphs (g)(1) and
(g)(2) of this AD by accomplishing all the
applicable actions specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–28A0034, dated August
2, 2007. Do all applicable corrective actions
before further flight.
(1) Replace the MOV actuator with a new
MOV actuator, part number MA030A1001.
(2) Measure the electrical resistance of the
bond from the adapter plate to the airplane
structure, and do all applicable corrective
actions.
Airworthiness Limitations (AWLs): Revision
for AWL No. 28–AWL–19 and 28–AWL–20
rmajette on PRODPC74 with PROPOSALS
(h) Concurrently with accomplishing the
actions required by paragraph (g) of this AD,
revise the AWLs section of the Instructions
for Continued Airworthiness (ICA) by
incorporating AWL No. 28–AWL–19 and No.
28–AWL–20 of Subsection E of Section 9,
Revision 28, dated February 2006, of the
Boeing 777 Maintenance Planning Data
(MPD) Document, D622W001–9.
No Alternative Critical Design Configuration
Control Limitations (CDCCLs)
(i) After accomplishing the action specified
in paragraph (h) of this AD, no alternative
CDCCLs may be used unless the CDCCLs are
approved as an AMOC in accordance with
the procedures specified in paragraph (k) of
this AD.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0846; Directorate
Identifier 2008–NM–045–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757–200, 757–200PF, and 757–
300 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for certain
Boeing Model 757–200, 757–200PF, and
757–300 series airplanes. This proposed
AD would require, for certain airplanes,
measuring the electrical bond resistance
at certain stations and doing any
applicable repair; installing support
brackets for the hot short protector and
new support clamps for the wire
bundles; installing the equipment of the
hot short protector; and modifying an
existing wire bundle and installing a
new wire bundle. This proposed AD
would also require, for certain other
airplanes, measuring the electrical bond
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45895
resistance at certain stations, measuring
the electrical bonding resistance
between the hot short protector and rear
spar web, and doing any applicable
repair. This proposed AD also would
require revising the Airworthiness
Limitations section of the Instructions
for Continued Airworthiness. This
proposed AD results from fuel system
reviews conducted by the manufacturer.
We are proposing this AD to prevent the
center fuel tank densitometer from
overheating and becoming a potential
ignition source inside the fuel tank,
which, in combination with flammable
fuel vapors, could result in a center fuel
tank explosion and consequent loss of
the airplane.
DATES: We must receive comments on
this proposed AD by September 22,
2008.
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Jen
Pei, Aerospace Engineer, Systems and
Equipment Branch, ANM–130S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6409; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
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Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0846; Directorate Identifier
2008–NM–045–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
rmajette on PRODPC74 with PROPOSALS
Discussion
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
we issued a regulation titled ‘‘Transport
Airplane Fuel Tank System Design
Review, Flammability Reduction and
Maintenance and Inspection
Requirements’’ (66 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements, this
rule included Special Federal Aviation
Regulation No. 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 21–83).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
ignition sources in the fuel tanks. This
requirement applies to type design
holders for large turbine-powered
transport airplanes and for subsequent
modifications to those airplanes. It
requires them to perform design reviews
and to develop design changes and
maintenance procedures if their designs
do not meet the new fuel tank safety
standards. As explained in the preamble
to the rule, we intended to adopt
airworthiness directives to mandate any
changes found necessary to address
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Jkt 214001
unsafe conditions identified as a result
of these reviews.
In evaluating these design reviews, we
have established four criteria intended
to define the unsafe conditions
associated with fuel tank systems that
require corrective actions. The
percentage of operating time during
which fuel tanks are exposed to
flammable conditions is one of these
criteria. The other three criteria address
the failure types under evaluation:
single failures, single failures in
combination with a latent condition(s),
and in-service failure experience. For all
four criteria, the evaluations included
consideration of previous actions taken
that may mitigate the need for further
action.
We have determined that the actions
identified in this AD are necessary to
reduce the potential of ignition sources
inside fuel tanks, which, in combination
with flammable fuel vapors, could result
in fuel tank explosions and consequent
loss of the airplane.
Boeing has found that no separation
was provided for the fuel quantity
indication system (FQIS) wires. A
potential hot short of the FQIS lead wire
could cause the densitometer in the
center fuel tank to overheat. In
situations where the fuel level in the
center fuel tank is low, the overheated
densitometer could ignite flammable
fuel vapors inside the center fuel tank.
This condition, if not corrected, could
result in a center fuel tank explosion
and consequent loss of the airplane.
Other Related Rulemaking
On April 29, 2008, we issued AD
2008–10–11, amendment 39–15517 (73
FR 25974, May 8, 2008), applicable to
all Boeing Model 757 airplanes. That
AD requires revising the Airworthiness
Limitations (AWLs) section of the
Instructions for Continued
Airworthiness (ICA) by incorporating
new limitations for fuel tank systems to
satisfy SFAR 88 requirements. That AD
also requires the initial inspection of
certain repetitive AWL inspections to
phase in those inspections, and repair if
necessary. That AD resulted from a
design review of the fuel tank systems.
We issued that AD to prevent the
potential for ignition sources inside fuel
tanks caused by latent failures,
alterations, repairs, or maintenance
actions, which, in combination with
flammable fuel vapors, could result in a
fuel tank explosion and consequent loss
of the airplane. Incorporating AWL No.
28–AWL–22 into the AWLs section of
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the ICA in accordance with paragraph
(g)(3) of AD 2008–10–11 would
terminate the action in paragraph (h) of
this proposed AD.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 757–28A0085, Revision
2, dated December 11, 2007. The service
bulletin describes the following
procedures:
• For certain airplanes: Measuring the
electrical bonding resistance between
the stiffeners located at inboard rear
spar station (IRSS) 164.9 and IRSS 179.2
and the rear spar web, and doing any
applicable repair; installing the support
brackets of the hot short protector (HSP)
and the new support clamps of the wire
bundles; installing the equipment of the
HSP; and modifying the existing wire
bundle and installing a new wire bundle
(includes re-routing).
• For certain other airplanes:
Measuring the electrical bonding
resistance between the stiffeners located
at IRSS 164.9 and IRSS 179.2 and the
rear spar web, measuring the electrical
bonding resistance between the HSP
and the rear spar web, and doing any
applicable repair.
We have also reviewed section 9,
Revision November 2007, of the Boeing
757 Maintenance Planning Data (MPD)
Document, D622N001–9 (hereafter
referred to as ‘‘the MPD’’). Subsection G
‘‘AIRWORTHINESS LIMITATIONS—
FUEL SYSTEM AWLs’’ of the MPD
describes AWLs for fuel tank systems
and includes AWL No. 28–AWL–22,
which is the critical design
configuration control limitation to
maintain the design features of the
center fuel tank’s HSP during its
replacement.
FAA’s Determination and Requirements
of This Proposed AD
We are proposing this AD because we
evaluated all relevant information and
determined the unsafe condition
described previously is likely to exist or
develop in other products of the(se)
same type design(s). This proposed AD
would require accomplishing the
actions specified in the service
information described previously.
Costs of Compliance
We estimate that this proposed AD
would affect 433 airplanes of U.S.
registry. The following table provides
the estimated costs for U.S. operators to
comply with this proposed AD.
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Federal Register / Vol. 73, No. 153 / Thursday, August 7, 2008 / Proposed Rules
ESTIMATED COSTS
Action
Groups 1–3; measurement, installations, and
modification.
Group 4; measurements
AWL Revision .................
1 Depending
Cost per product 1
Number
of U.S.registered
airplanes
Between $14,110 and
$14,215.
Between $14,750 and
$14,855.
433
Between $6,386,750 and
$6,432,215.
None ..............................
None ..............................
$160 ...............................
$80 .................................
433
433
$69,280.
$34,640.
Average
labor rate
per hour
Work
hours
8
$80
2
1
Parts 1
80
80
Fleet cost 1
on airplane configuration.
rmajette on PRODPC74 with PROPOSALS
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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
center fuel tank explosion and consequent
loss of the airplane.
PART 39—AIRWORTHINESS
DIRECTIVES
Measurement, Installation, Modifications,
Replacement, and Repair
(f) For Groups 1 through 3 airplanes, as
identified in Boeing Alert Service Bulletin
757–28A0085, Revision 2, dated December
11, 2007: Within 60 months after the effective
date of this AD, do the measurement,
installations, modifications, replacement,
and applicable repair by accomplishing all
the applicable actions specified in the
Accomplishment Instructions of the service
bulletin. Do the applicable repair before
further flight.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), and
3. 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.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
Applicability
(c) This AD applies to Boeing Model 757–
200, 757–200PF, and 757–300 series
airplanes, certificated in any category; as
identified in Boeing Alert Service Bulletin
757–28A0085, Revision 2, dated December
11, 2007.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new inspections. Compliance with
these inspections is required by 14 CFR
91.403(c). For airplanes that have been
previously modified, altered, or repaired in
the areas addressed by these inspections, the
operator may not be able to accomplish the
inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c),
the operator must request approval for an
alternative method of compliance (AMOC)
according to paragraph (l) of this AD. The
request should include a description of
changes to the required inspections that will
ensure the continued operational safety of
the airplane.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
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14:16 Aug 06, 2008
Jkt 214001
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Boeing: Docket No. FAA–2008–0846;
Directorate Identifier 2008–NM–045–AD.
Comments Due Date
(a) We must receive comments by
September 22, 2008.
Affected ADs
(b) None.
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent the center fuel
tank densitometer from overheating and
becoming a potential ignition source inside
the fuel tank, which, in combination with
flammable fuel vapors, could result in a
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Compliance
(e) Comply with this AD within the
compliance times specified, unless already
done.
Measure and Repair
(g) For Group 4 airplanes, as identified in
Boeing Alert Service Bulletin 757–28A0085,
Revision 2, dated December 11, 2007: Within
60 months after the effective date of this AD,
do the measurements and applicable repair
by accomplishing all the applicable actions
specified in the Accomplishment
Instructions of the service bulletin. Do the
applicable repair before further flight.
Airworthiness Limitations (AWLs) Revision
for AWL No. 28–AWL–22
(h) Concurrently with accomplishing the
actions required by paragraphs (f) and (g) of
this AD, revise the AWLs section of the
Instructions for Continued Airworthiness
(ICA) by incorporating AWL No. 28–AWL–22
of Subsection G of section 9, Revision
November 2007, Boeing 757 Maintenance
Planning Data (MPD) Document, D622N001–
9.
No Alternative Critical Design Configuration
Control Limitations (CDCCLs)
(i) After accomplishing the action specified
in paragraph (h) of this AD, no alternative
CDCCLs may be used unless the CDCCLs are
approved as an AMOC in accordance with
the procedures specified in paragraph (k) of
this AD.
Credit for Actions Done According to
Previous Issue of the Service Bulletin
(j) Actions done before the effective date of
this AD in accordance with Boeing Alert
Service Bulletin 757–28A0085, Revision 1,
dated April 16, 2007, are acceptable for
compliance with the requirements of
paragraphs (f) and (g) of this AD.
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Terminating Action for AWLs Revision
(k) Incorporating AWL No. 28–AWL–22
into the AWLs section of the ICA in
accordance with paragraph (g)(3) of AD
2008–10–11, amendment 39–15517,
terminates the action in paragraph (h) of this
AD.
control input connection to the horizontal
stabilizer and consequent] partial loss of
control of the aircraft.
Alternative Methods of Compliance
(AMOCs)
(l)(1) The Manager, Seattle ACO, FAA,
ATTN: Jen Pei, Aerospace Engineer, Systems
and Equipment Branch, ANM–130S, FAA,
Seattle ACO, 1601 Lind Avenue, SW.,
Renton, Washington 98057–3356; telephone
(425) 917–6409; fax (425) 917–6590; has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on July 29,
2008.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–18222 Filed 8–6–08; 8:45 am]
*
*
*
*
*
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by September 8, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0850; Directorate
Identifier 2007–NM–342–AD]
RIN 2120–AA64
Airworthiness Directives; Fokker
Model F.28 Mark 0100 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
rmajette on PRODPC74 with PROPOSALS
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above that would
supersede an existing AD. This
proposed AD results from mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country to identify
and correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as:
*
*
*
*
*
During recent inspections it was found that
some * * * bolts, that connect the horizontal
stabilizer control unit actuator with the doglinks, were broken. This condition, if not
corrected, could lead to [the loss of the flight
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You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, WA 98057–
3356; telephone (425) 227–1137; fax
(425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0850; Directorate Identifier
2007–NM–342–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
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We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On June 13, 1997, we issued AD 97–
13–05, Amendment 39–10051 (62 FR
34617, June 27, 1997). That AD required
actions intended to address an unsafe
condition on the products listed above.
Since we issued AD 97–13–05, we
received reports of inspection results
indicating that the bolt that connects the
horizontal stabilizer control unit
actuator with the dog-links was broken
(one on the nut side, and one on the
head side). When the bolts fails at the
nut end, the remaining part of the bolt
cannot drop out of the connection due
to the limited amount of space available
between the bolt head and plate, and the
affected connection is still able to carry
the system loads. However, if the head
side of the bolt fails, then the bolt may
drop out of the connection.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2007–0287,
dated November 15, 2007 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
In January 1996, Fokker issued Service
Bulletin (SB) SBF–100–27–069 (referencing
Menasco, now Goodrich, SB 23100–27–19) to
introduce an inspection of bolt Part Number
(P/N) 23233–1 for cracks after the
examination of a failed bolt. This Service
Bulletin was made mandatory by CAA–NL
(Civil Aviation Authority—the Netherlands)
with the issuance of AD BLA 1996–006 (A)
[reference corresponding FAA AD 97–13–05].
Additionally the same SB introduced a lower
torque value for these bolts.
During recent inspections it was found that
some of these bolts, that connect the
horizontal stabilizer control unit actuator
with the dog-links, were broken. This
condition, if not corrected, could lead to [the
loss of the flight control input connection to
the horizontal stabilizer and consequent]
partial loss of control of the aircraft.
Since an unsafe condition has been
identified that continues to exist or develop
on other aircraft of the same type design, this
Airworthiness Directive supersedes CAA–NL
AD 1996–006 and requires an integrity check
by a re-torque in accordance with SBF–100–
27–091 and the installation of a tie-wrap
through the bolt, which will act as a retainer
for the bolt and nut. The key function for this
tie-wrap is to keep the bolt in place in the
event the bolt head fails.
The corrective action includes
replacing any failed bolt (i.e., broken or
E:\FR\FM\07AUP1.SGM
07AUP1
]]>Agencies
[Federal Register Volume 73, Number 153 (Thursday, August 7, 2008)]
[Proposed Rules]
[Pages 45895-45898]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-18222]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0846; Directorate Identifier 2008-NM-045-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 757-200, 757-200PF, and
757-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 757-200, 757-200PF, and 757-300 series airplanes.
This proposed AD would require, for certain airplanes, measuring the
electrical bond resistance at certain stations and doing any applicable
repair; installing support brackets for the hot short protector and new
support clamps for the wire bundles; installing the equipment of the
hot short protector; and modifying an existing wire bundle and
installing a new wire bundle. This proposed AD would also require, for
certain other airplanes, measuring the electrical bond resistance at
certain stations, measuring the electrical bonding resistance between
the hot short protector and rear spar web, and doing any applicable
repair. This proposed AD also would require revising the Airworthiness
Limitations section of the Instructions for Continued Airworthiness.
This proposed AD results from fuel system reviews conducted by the
manufacturer. We are proposing this AD to prevent the center fuel tank
densitometer from overheating and becoming a potential ignition source
inside the fuel tank, which, in combination with flammable fuel vapors,
could result in a center fuel tank explosion and consequent loss of the
airplane.
DATES: We must receive comments on this proposed AD by September 22,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Jen Pei, Aerospace Engineer, Systems
and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6409; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
[[Page 45896]]
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0846;
Directorate Identifier 2008-NM-045-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The FAA has examined the underlying safety issues involved in fuel
tank explosions on several large transport airplanes, including the
adequacy of existing regulations, the service history of airplanes
subject to those regulations, and existing maintenance practices for
fuel tank systems. As a result of those findings, we issued a
regulation titled ``Transport Airplane Fuel Tank System Design Review,
Flammability Reduction and Maintenance and Inspection Requirements''
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards
for transport airplanes and new maintenance requirements, this rule
included Special Federal Aviation Regulation No. 88 (``SFAR 88,''
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
Among other actions, SFAR 88 requires certain type design (i.e.,
type certificate (TC) and supplemental type certificate (STC)) holders
to substantiate that their fuel tank systems can prevent ignition
sources in the fuel tanks. This requirement applies to type design
holders for large turbine-powered transport airplanes and for
subsequent modifications to those airplanes. It requires them to
perform design reviews and to develop design changes and maintenance
procedures if their designs do not meet the new fuel tank safety
standards. As explained in the preamble to the rule, we intended to
adopt airworthiness directives to mandate any changes found necessary
to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four
criteria intended to define the unsafe conditions associated with fuel
tank systems that require corrective actions. The percentage of
operating time during which fuel tanks are exposed to flammable
conditions is one of these criteria. The other three criteria address
the failure types under evaluation: single failures, single failures in
combination with a latent condition(s), and in-service failure
experience. For all four criteria, the evaluations included
consideration of previous actions taken that may mitigate the need for
further action.
We have determined that the actions identified in this AD are
necessary to reduce the potential of ignition sources inside fuel
tanks, which, in combination with flammable fuel vapors, could result
in fuel tank explosions and consequent loss of the airplane.
Boeing has found that no separation was provided for the fuel
quantity indication system (FQIS) wires. A potential hot short of the
FQIS lead wire could cause the densitometer in the center fuel tank to
overheat. In situations where the fuel level in the center fuel tank is
low, the overheated densitometer could ignite flammable fuel vapors
inside the center fuel tank. This condition, if not corrected, could
result in a center fuel tank explosion and consequent loss of the
airplane.
Other Related Rulemaking
On April 29, 2008, we issued AD 2008-10-11, amendment 39-15517 (73
FR 25974, May 8, 2008), applicable to all Boeing Model 757 airplanes.
That AD requires revising the Airworthiness Limitations (AWLs) section
of the Instructions for Continued Airworthiness (ICA) by incorporating
new limitations for fuel tank systems to satisfy SFAR 88 requirements.
That AD also requires the initial inspection of certain repetitive AWL
inspections to phase in those inspections, and repair if necessary.
That AD resulted from a design review of the fuel tank systems. We
issued that AD to prevent the potential for ignition sources inside
fuel tanks caused by latent failures, alterations, repairs, or
maintenance actions, which, in combination with flammable fuel vapors,
could result in a fuel tank explosion and consequent loss of the
airplane. Incorporating AWL No. 28-AWL-22 into the AWLs section of the
ICA in accordance with paragraph (g)(3) of AD 2008-10-11 would
terminate the action in paragraph (h) of this proposed AD.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 757-28A0085,
Revision 2, dated December 11, 2007. The service bulletin describes the
following procedures:
For certain airplanes: Measuring the electrical bonding
resistance between the stiffeners located at inboard rear spar station
(IRSS) 164.9 and IRSS 179.2 and the rear spar web, and doing any
applicable repair; installing the support brackets of the hot short
protector (HSP) and the new support clamps of the wire bundles;
installing the equipment of the HSP; and modifying the existing wire
bundle and installing a new wire bundle (includes re-routing).
For certain other airplanes: Measuring the electrical
bonding resistance between the stiffeners located at IRSS 164.9 and
IRSS 179.2 and the rear spar web, measuring the electrical bonding
resistance between the HSP and the rear spar web, and doing any
applicable repair.
We have also reviewed section 9, Revision November 2007, of the
Boeing 757 Maintenance Planning Data (MPD) Document, D622N001-9
(hereafter referred to as ``the MPD''). Subsection G ``AIRWORTHINESS
LIMITATIONS--FUEL SYSTEM AWLs'' of the MPD describes AWLs for fuel tank
systems and includes AWL No. 28-AWL-22, which is the critical design
configuration control limitation to maintain the design features of the
center fuel tank's HSP during its replacement.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the(se) same type
design(s). This proposed AD would require accomplishing the actions
specified in the service information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 433 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
[[Page 45897]]
Estimated Costs
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Average Number of
Work labor U.S.-
Action hours rate per Parts 1 Cost per product 1 registered Fleet cost 1
hour airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Groups 1-3; measurement, 8 $80 Between $14,110 and Between $14,750 and 433 Between $6,386,750 and
installations, and modification. $14,215. $14,855. $6,432,215.
Group 4; measurements................. 2 80 None..................... $160..................... 433 $69,280.
AWL Revision.......................... 1 80 None..................... $80...................... 433 $34,640.
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ Depending on airplane configuration.
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 determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979), and
3. 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Boeing: Docket No. FAA-2008-0846; Directorate Identifier 2008-NM-
045-AD.
Comments Due Date
(a) We must receive comments by September 22, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 757-200, 757-200PF, and 757-
300 series airplanes, certificated in any category; as identified in
Boeing Alert Service Bulletin 757-28A0085, Revision 2, dated
December 11, 2007.
Note 1:
This AD requires revisions to certain operator maintenance
documents to include new inspections. Compliance with these
inspections is required by 14 CFR 91.403(c). For airplanes that have
been previously modified, altered, or repaired in the areas
addressed by these inspections, the operator may not be able to
accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance (AMOC)
according to paragraph (l) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued operational safety of the airplane.
Unsafe Condition
(d) This AD results from fuel system reviews conducted by the
manufacturer. We are issuing this AD to prevent the center fuel tank
densitometer from overheating and becoming a potential ignition
source inside the fuel tank, which, in combination with flammable
fuel vapors, could result in a center fuel tank explosion and
consequent loss of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Measurement, Installation, Modifications, Replacement, and Repair
(f) For Groups 1 through 3 airplanes, as identified in Boeing
Alert Service Bulletin 757-28A0085, Revision 2, dated December 11,
2007: Within 60 months after the effective date of this AD, do the
measurement, installations, modifications, replacement, and
applicable repair by accomplishing all the applicable actions
specified in the Accomplishment Instructions of the service
bulletin. Do the applicable repair before further flight.
Measure and Repair
(g) For Group 4 airplanes, as identified in Boeing Alert Service
Bulletin 757-28A0085, Revision 2, dated December 11, 2007: Within 60
months after the effective date of this AD, do the measurements and
applicable repair by accomplishing all the applicable actions
specified in the Accomplishment Instructions of the service
bulletin. Do the applicable repair before further flight.
Airworthiness Limitations (AWLs) Revision for AWL No. 28-AWL-22
(h) Concurrently with accomplishing the actions required by
paragraphs (f) and (g) of this AD, revise the AWLs section of the
Instructions for Continued Airworthiness (ICA) by incorporating AWL
No. 28-AWL-22 of Subsection G of section 9, Revision November 2007,
Boeing 757 Maintenance Planning Data (MPD) Document, D622N001-9.
No Alternative Critical Design Configuration Control Limitations
(CDCCLs)
(i) After accomplishing the action specified in paragraph (h) of
this AD, no alternative CDCCLs may be used unless the CDCCLs are
approved as an AMOC in accordance with the procedures specified in
paragraph (k) of this AD.
Credit for Actions Done According to Previous Issue of the Service
Bulletin
(j) Actions done before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 757-28A0085, Revision
1, dated April 16, 2007, are acceptable for compliance with the
requirements of paragraphs (f) and (g) of this AD.
[[Page 45898]]
Terminating Action for AWLs Revision
(k) Incorporating AWL No. 28-AWL-22 into the AWLs section of the
ICA in accordance with paragraph (g)(3) of AD 2008-10-11, amendment
39-15517, terminates the action in paragraph (h) of this AD.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, Seattle ACO, FAA, ATTN: Jen Pei, Aerospace
Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle ACO,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6409; fax (425) 917-6590; has the authority to approve
AMOCs for this AD, if requested using the procedures found in 14 CFR
39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on July 29, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-18222 Filed 8-6-08; 8:45 am]
BILLING CODE 4910-13-P
