Airworthiness Directives; The Boeing Company Model 747 Airplanes, 70863-70868 [2010-29231]
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Federal Register / Vol. 75, No. 223 / Friday, November 19, 2010 / Proposed Rules
063, dated April 15, 2010 (for Model F28
Mark 0100 airplanes).
(2) If a part number other than P/N
D48127–009 for Model F28 Mark 0100
airplanes and P/N A42509–089 for Model
F28 Mark 1000, 2000, 3000, and 4000
airplanes is installed, within 24 months after
the effective date of this AD, replace the cam
with a cam having a correct part number, and
do an inspection to verify that the cam
operates correctly, in accordance with Part 2
of the Accomplishment Instructions of
Fokker Service Bulletin SBF28–28–052,
dated April 20, 2010 (for Model F28 Mark
1000, 2000, 3000, and 4000 airplanes); or
SBF100–28–063, dated April 15, 2010 (for
Model F28 Mark 0100 airplanes).
(3) If, during any inspection required by
paragraphs (g)(1) and (g)(2) of this AD, the
cam does not operate correctly, before further
flight, adjust the cam until it operates
correctly, in accordance with Part 2 of the
Accomplishment Instructions of Fokker
Service Bulletin SBF28–28–052, dated April
20, 2010 (for Model F28 Mark 1000, 2000,
3000, and 4000 airplanes); or SBF100–28–
063, dated April 15, 2010 (for Model F28
Mark 0100 airplanes).
Repetitive Inspections
(h) Within 1,200 flight hours after verifying
that the cam operates correctly, as required
by paragraphs (g)(1) and (g)(2) of this AD, as
applicable: Do an inspection to verify that the
cam operates correctly and, before further
flight, do all applicable corrective actions, in
accordance with Part 2 of the
Accomplishment Instructions of Fokker
Service Bulletin SBF28–28–052, dated April
20, 2010 (for Model F28 Mark 1000, 2000,
3000, and 4000 airplanes); or SBF100–28–
063, dated April 15, 2010 (for Model F28
Mark 0100 airplanes). Thereafter, repeat the
inspection of the cam at intervals not to
exceed 1,200 flight hours.
Parts Installation
(i) As of the effective date of this AD, no
person may install an FCP access door, cam,
or fueling panel on any airplane, unless the
requirements of this AD have been
accomplished on the cam.
FAA AD Differences
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Note 1: This AD differs from the MCAI
and/or service information as follows:
Although paragraph (6) of the MCAI provides
an option to incorporate the repetitive
functional inspection into the maintenance
program and then use the maintenance
program as a method of complying with the
repetitive inspection requirement, this AD
does not include that provision.
Other FAA AD Provisions
(j) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Rodriguez,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
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FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1137; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
The AMOC approval letter must specifically
reference this AD.
(2) Airworthy Product: For any
requirement in this AD to obtain corrective
actions from a manufacturer or other source,
use these actions if they are FAA-approved.
Corrective actions are considered FAAapproved if they are approved by the State
of Design Authority (or their delegated
agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Related Information
(k) Refer to MCAI EASA Airworthiness
Directive 2010–0139, dated July 1, 2010;
Fokker Service Bulletin SBF28–28–052,
dated April 20, 2010; and Fokker Service
Bulletin SBF100–28–063, dated April 15,
2010; for related information.
Issued in Renton, Washington, on
November 10, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–29228 Filed 11–18–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0090; Directorate
Identifier 2007–NM–312–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747 Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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70863
Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
ACTION:
We are revising an earlier
proposed airworthiness directive (AD)
for certain Model 747 airplanes. The
original NPRM would have required
measuring the electrical bond resistance
between the motor operated valve
(MOV) actuators and airplane structure
for the main, center, auxiliary, and
horizontal stabilizer fuel tanks, as
applicable, and corrective action if
necessary. The original NPRM also
would have required a revision to the
maintenance program to incorporate
airworthiness limitation (AWL) No. 28–
AWL–21 or AWL No. 28–AWL–27, as
applicable. The original NPRM resulted
from fuel system reviews conducted by
the manufacturer. This supplemental
NPRM would revise the original NPRM
by adding airplanes to the applicability,
and would require replacing
production-installed laminate phenolic
spacers with metallic spacers between
the fuel jettison MOV and the airplane
structure, as applicable. We are
proposing this supplemental NPRM to
prevent electrical current from flowing
through an 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.
DATES: We must receive comments on
this supplemental NPRM by December
14, 2010.
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 proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
SUMMARY:
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Federal Register / Vol. 75, No. 223 / Friday, November 19, 2010 / Proposed Rules
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
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:
Douglas Bryant, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6505; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
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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–2008–0090; Directorate Identifier
2007–NM–312–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
We issued a notice of proposed
rulemaking (NPRM) (the ‘‘original
NPRM’’) to amend 14 CFR part 39 to
include an airworthiness directive (AD)
that would apply to certain Model 747
airplanes. That original NPRM was
published in the Federal Register on
January 31, 2008 (73 FR 5773). That
original NPRM proposed to require
measuring the electrical bond resistance
between the motor operated valve
(MOV) actuators and airplane structure
for the main, center, auxiliary, and
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horizontal stabilizer fuel tanks, as
applicable, and corrective action if
necessary. That original NPRM also
proposed to require a revision to the
maintenance program to incorporate
airworthiness limitation (AWL) No. 28–
AWL–21 or AWL No. 28–AWL–27, as
applicable.
Actions Since Original NPRM Was
Issued
Since we issued the original NPRM,
we reviewed Boeing Service Bulletin
747–28A2292, Revision 2, dated May
13, 2010 (for Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, 747SR, and 747SP
series airplanes). This service bulletin
clarifies the procedure for measuring the
electrical bond resistance, and adds
procedures for replacing productioninstalled laminate phenolic spacers with
metallic spacers for airplanes in Groups
12, 16, 17, 18, and 19. This service
bulletin also adds airplanes to the
Effectivity. Paragraphs (c) and (g) of this
supplemental NPRM have been revised
accordingly.
We also reviewed Boeing Service
Bulletin 747–28A2294, Revision 1,
dated March 5, 2009 (for Model 747–400
series airplanes equipped with an active
horizontal stabilizer fuel tank). This
service bulletin is the same as the
original issue, dated September 21,
2007, except that a reference to Subsection 28–17–03 of Boeing 747–400
Airplane Maintenance Manual (AMM)
is corrected in Revision 1.
We reviewed Boeing 747–100/200/
300/SP Airworthiness Limitations
(AWLs) and Certification Maintenance
Requirements (CMRs), Document D6–
13747–CMR, Revision March 2008
(hereafter referred to as ‘‘Document D6–
13747–CMR’’). (We referred to Revision
January 2007 of Document D6–13747–
CMR in the original NPRM.) Document
D6–13747–CMR revises certain AWLs
for fuel tank systems. However, AWL
No. 28–AWL–21, which is specified in
this supplemental NPRM, has not been
revised in Document D6–13747–CMR,
Revision March 2008.
We also reviewed the Boeing 747–400
Maintenance Planning Data (MPD)
Document, Section 9, D621U400–9,
Revision December 2009 (hereafter
referred to as ‘‘Boeing 747–400 MPD’’).
Among other things, Subsection D of
Boeing 747–400 MPD has been revised
to clarify the ‘‘Applicability’’ of AWL
No. 28–AWL–27, which is a critical
design configuration control limitation
(CDCCL) to maintain the design features
of the MOV actuator.
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We have revised this supplemental
NPRM to refer to the latest service
information described previously.
Other Relevant Rulemaking
On April 28, 2008, we issued AD
2008–10–07, Amendment 39–15513 (73
FR 25977, May 8, 2008); and on October
30, 2009, we issued AD 2008–10–07 R1,
Amendment 39–16070 (74 FR 56098,
November 16, 2009); applicable to all
Boeing Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–
200F, 747–300, 747SR, and 747SP series
airplanes. Those ADs require revising
the maintenance program by
incorporating new AWLs for fuel tank
systems to satisfy Special Federal
Aviation Regulation No. 88 (‘‘SFAR 88’’)
requirements. As an optional action,
those ADs also allow incorporating
AWL No. 28–AWL–21 into the
maintenance program. Therefore, we
have added a new paragraph (n) to this
supplemental NPRM to specify that
incorporating AWL No. 28–AWL–21
into the maintenance program in
accordance with paragraph (g) of AD
2008–10–07 or 2008–10–07 R1
terminates the action required by
paragraph (k) of this supplemental
NPRM for the applicable airplanes.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received from
the three commenters.
Request To Allow Use of Future
Revisions of the Service Bulletins
Boeing requested that we revise the
original NPRM to specify that the
proposed modifications may also be
done in accordance with any futureapproved revisions to Boeing Alert
Service Bulletin 747–28A2292, dated
September 14, 2007; and Boeing Alert
Service Bulletin 747–28A2294, dated
September 21, 2007. As justification,
Boeing stated that these service
bulletins could be revised by the time
we issue the AD.
We partially agree. As discussed
previously, we have revised this
supplemental NPRM to refer to the most
recently issued service information.
However, we do not agree to refer to
‘‘later revisions.’’ To allow operators to
use later revisions of the referenced
service documents, either we must
revise the AD to reference specific later
revisions, or operators must request
approval to use later revisions as an
alternative method of compliance with
the AD. Therefore, we have removed all
references to the use of a ‘‘later revision’’
of the applicable service information
from this supplemental NPRM to be
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consistent with FAA policy. We may
consider approving the use of later
revisions of the service information as
an AMOC with this AD, as provided by
paragraph (q) of this supplemental
NPRM.
Request To Revise Paragraphs (h) and
(i) of the Original NPRM
KLM Royal Dutch Airlines (KLM)
stated that the intent of the original
NPRM is to maintain the design features
introduced in accordance with Boeing
Alert Service Bulletin 747–28A2292,
dated September 14, 2007; and Boeing
Alert Service Bulletin 747–28A2294,
dated September 21, 2007; respectively;
when an MOV actuator is installed.
KLM thought that it was clearer if the
NPRM stated that the CDCCLs must be
incorporated into the applicable
paragraphs of the AMM to maintain
these design features.
We infer that KLM requests that we
revise paragraphs (h) and (i) of the
NPRM as proposed above. We disagree
with the commenter’s request. We
disagree that incorporating CDCCLs into
the AMM is the appropriate location for
a CDCCL. The AMM is not an FAAapproved document. The appropriate
location for a CDCCL is in the FAAapproved section (i.e., the
Airworthiness Limitations section) of an
operator’s maintenance program. We
have not changed this supplemental
NPRM in this regard.
Request To Exclude a Certain Airplane
From the Requirements of Paragraph
(g) of the Original NPRM
Lufthansa requested that we exclude
a certain Model 747–400 series airplane
from paragraph (g) of the original NPRM
because the horizontal stabilizer tank
(HST) on that airplane has never been
activated.
We disagree with the request.
Although the HST might not be
activated at this time, it could be
activated in the future. We cannot
exclude an airplane from the
requirements of this supplemental
NPRM without substantiation that the
unsafe condition has been adequately
addressed. We have not changed this
supplemental NPRM in this regard.
70865
Other Change Made to This
Supplemental NPRM
Request To Extend Compliance Time
Lufthansa requested that we extend
the compliance time of the original
NPRM from 60 months to 72 months.
Lufthansa stated that this extension will
allow operators to implement the
modification at the next maintenance
layover.
KLM requested that we extend the
compliance time of the original NPRM
from 60 months to 96 months. KLM
stated that tank entry might be
necessary for accomplishing the actions,
and KLM wanted to avoid tank entry
during C-checks.
We disagree with the commenters’
requests to extend the compliance time.
In developing an appropriate
compliance time for this supplemental
NPRM, we considered the urgency
associated with the subject unsafe
condition and the practical aspect of
accomplishing the required actions on
the Model 747 fleet in a timely manner.
We recognize that operators may have
different schedules for accomplishing
heavy maintenance, but at the same
time, we find that the 60-month
compliance time will include most
operators’ schedules for that type of
work. Further, according to the
provisions of paragraph (q) of this AD,
we may consider approving requests to
adjust the compliance time if those
requests include data that prove that the
new compliance time would provide an
acceptable level of safety. No change to
this supplemental NPRM is necessary in
this regard.
We have added a new paragraph (m)
to this supplemental NPRM to specify
that no alternative CDCCLs may be used
unless they are approved as an AMOC.
Inclusion of this paragraph in the
supplemental NPRM is intended to
ensure that the AD-mandated
airworthiness limitations changes are
treated the same as the airworthiness
limitations issued with the original type
certificate.
FAA’s Determination and Proposed
Requirements of the Supplemental
NPRM
We are proposing this supplemental
NPRM because we evaluated all
pertinent information and determined
an unsafe condition exists and is likely
to exist or develop on other products of
the same type design. Certain changes
described above expand the scope of the
original NPRM. As a result, we have
determined that it is necessary to reopen
the comment period to provide
additional opportunity for the public to
comment on this supplemental NPRM.
Explanation of Change to Costs of
Compliance
Since issuance of the original NPRM,
we have increased the labor rate used in
the Costs of Compliance form $80 per
work-hour to $85 per work-hour. The
Costs of Compliance information,
below, reflects this increase in the
specified hourly labor rate.
For convenience to the operator, the
Estimated Costs table, below, was
revised to break out the cost of replacing
the spacers and the on-condition costs.
Costs of Compliance
We estimate that this proposed AD
will affect 222 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Labor cost
Parts cost
Cost per product
Measurement ................
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Action
Up to 7 work-hours × $85 per hour =
Up to $595.
Up to 4 work-hours × $85 per hour =
Up to $340.
1 work-hour × $85 per hour = $85 ........
Up to $350 ...................
Up to $945 ...................
Up to $209,790.
$1,305 ..........................
Up to $1,645 ................
Up to $98,700.
$0 .................................
$85 ...............................
$18,870.
Replacement (Up to 60
airplanes).
Maintenance program
revision.
We estimate the following costs to do
any necessary modification that would
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be required based on the results of the
proposed inspection. We have no way of
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Cost on U.S. operators
determining the number of aircraft that
might need this modification:
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Federal Register / Vol. 75, No. 223 / Friday, November 19, 2010 / Proposed Rules
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Change electrical bond and rework part contact surface.
436 work-hours × $85 per hour = $37,060 ......
Up to $35,760 .............
Authority for This Rulemaking
the FAA proposes to amend 14 CFR part
39 as follows:
a fuel tank explosion and consequent loss of
the airplane.
PART 39—AIRWORTHINESS
DIRECTIVES
Compliance
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.
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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, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
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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:
The Boeing Company: Docket No. FAA–
2008–0090; Directorate Identifier 2007–
NM–312–AD.
Comments Due Date
(a) We must receive comments by
December 14, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing
Company Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–400F,
747SR, and 747SP series airplanes,
certificated in any category; as identified in
Boeing Service Bulletin 747–28A2292,
Revision 2, dated May 13, 2010.
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 (q) 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.
Subject
(d) Air Transport Association (ATA) of
America Code 28: Fuel.
Unsafe Condition
(e) This AD results from fuel system
reviews conducted by the manufacturer. The
Federal Aviation Administration is 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
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Cost per product
Up to $72,820.
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Measurement, Corrective Action, and
Replacement
(g) Within 60 months after the effective
date of this AD, do the actions required by
paragraphs (g)(1) and (g)(2) of this AD, as
applicable.
(1) Measure the electrical bond resistance
between the MOV actuators and the airplane
structure for the main, center, and auxiliary
fuel tanks, as applicable; and do all
applicable corrective actions; by
accomplishing all of the applicable actions in
the Accomplishment Instructions of Boeing
Service Bulletin 747–28A2292, Revision 2,
dated May 13, 2010. The corrective actions
must be accomplished before further flight.
(2) For airplanes in Groups 12, 16, 17, 18,
and 19, as identified in Boeing Service
Bulletin 747–28A2292, Revision 2, dated
May 13, 2010: Within 60 months after the
effective date of this AD, replace productioninstalled laminate phenolic spacers with
metallic spacers, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–28A2292, Revision 2,
dated May 13, 2010.
(h) For airplanes identified in Boeing
Service Bulletin 747–28A2294, Revision 1,
dated March 5, 2009: Within 60 months after
the effective date of this AD, measure the
electrical bond resistance between the MOV
actuators and airplane structure for the
horizontal stabilizer (HST) fuel tanks, and do
all the applicable corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
28A2294, Revision 1, dated March 5, 2009.
The corrective actions must be accomplished
before further flight.
Deactivation of the HST
(i) For airplanes identified in Boeing
Service Bulletin 747–28A2294, Revision 1,
dated March 5, 2009: Deactivation of the
HST, in accordance with the applicable
Boeing service information specified in Table
1 of this AD, terminates the requirements of
paragraph (h) of this AD, except as provided
by paragraph (j) of this AD. Deactivation of
the HST before the effective date of this AD
in accordance with the applicable service
information specified in Table 2 of this AD
also terminates the requirements of
paragraph (h) of this AD, except as provided
by paragraph (j) of this AD.
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Federal Register / Vol. 75, No. 223 / Friday, November 19, 2010 / Proposed Rules
TABLE 1—DEACTIVATION SERVICE INFORMATION
Boeing—
Service
Service
Service
Service
Service
Service
Service
Service
Service
Service
Service
Revision—
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
747–28–2265
747–28–2272
747–28–2274
747–28–2275
747–28–2279
747–28–2285
747–28–2293
747–28–2295
747–28–2296
747–28–2300
747–28–2314
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
Dated—
Original ...................................................
Original ...................................................
1 .............................................................
4 .............................................................
2 .............................................................
3 .............................................................
2 .............................................................
2 .............................................................
Original ...................................................
1 .............................................................
Original ...................................................
February 22, 2006.
February 21, 2006.
May 21, 2008.
February 2, 2009.
October 16, 2007.
August 30, 2007.
March 4, 2008.
January 19, 2009.
July 13, 2007.
June 2, 2008.
December 9, 2008.
TABLE 2—DEACTIVATION CREDIT SERVICE INFORMATION
Boeing—
Revision—
Dated—
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
.................................................................................
Original ...................................................
Original ...................................................
1 .............................................................
2 .............................................................
3 .............................................................
Original ...................................................
1 .............................................................
Original ...................................................
1 .............................................................
2 .............................................................
Original ...................................................
1 .............................................................
Original ...................................................
Service Bulletin 747–28–2295 .................................................................................
Service Bulletin 747–28–2300 .................................................................................
1 .............................................................
Original ...................................................
March 13, 2006.
June 12, 2006.
March 16, 2007.
July 2, 2007.
March 11, 2008.
June 12, 2006.
May 25, 2007.
January 23, 2007.
May 9, 2007.
August 3, 2007.
May 9, 2007.
August 29, 2007.
November 17,
2006.
March 20, 2008.
January 16, 2008
Service
Service
Service
Service
Service
Service
Service
Service
Service
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
Bulletin
747–28–2274
747–28–2275
747–28–2275
747–28–2275
747–28–2275
747–28–2279
747–28–2279
747–28–2285
747–28–2285
747–28–2285
747–28–2293
747–28–2293
747–28–2295
emcdonald on DSK2BSOYB1PROD with PROPOSALS
Reactivation of the HST
(j) For airplanes identified Boeing Service
Bulletin 747–28A2294, Revision 1, dated
March 5, 2009, on which the HST is
reactivated, the HST must be reactivated in
accordance with a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA. For any airplane on which the
HST is reactivated, the requirements of
paragraphs (h) and (l) of this AD must be
done before further flight following the
reactivation, or within 60 months after the
effective date of this AD, whichever occurs
later. For a reactivation method to be
approved, the reactivation method must meet
the certification basis of the airplane, and the
approval must specifically reference this AD.
Maintenance Program Revision
(k) For Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–200F,
747–300, 747SR, and 747SP series airplanes:
Concurrently with accomplishing the actions
required by paragraph (g) of this AD, revise
the maintenance program by incorporating
airworthiness limitation (AWL) No. 28–
AWL–21 of Section D of Boeing 747–100/
200/300/SP Airworthiness Limitations
(AWLs) and Certification Maintenance
Requirements (CMRs), Document D6–13747–
CMR, Revision March 2008.
(l) For Model 747–400, 747–400D, and
747–400F series airplanes: Concurrently with
accomplishing the actions required by
paragraph (g) of this AD, revise the
maintenance program by incorporating AWL
VerDate Mar<15>2010
17:04 Nov 18, 2010
Jkt 223001
No. 28–AWL–27 of Subsection D of Boeing
747–400 Maintenance Planning Data (MPD)
Document, Section 9, D621U400–9, Revision
December 2009.
No Alternative Critical Design Configuration
Control Limitations (CDCCLs)
(m) After accomplishing the applicable
action required in paragraph (k) or (l) 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 (q) of this AD.
Terminating Action for Maintenance
Program Revision
(n) For Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–200F,
747–300, 747SR, and 747SP series airplanes:
Incorporating AWL No. 28–AWL–21 into the
maintenance program in accordance with
paragraph (g) of AD 2008–10–07,
Amendment 39–15513; or AD 2008–10–07
R1, Amendment 39–16070; terminates the
action required by paragraph (k) of this AD.
Actions Accomplished According to
Previous Issue of Service Bulletin
(o) Actions done before the effective date
of this AD, in accordance with Boeing Alert
Service Bulletin 747–28A2294, dated
September 21, 2007, are acceptable for
compliance with the corresponding
requirements of this AD.
PO 00000
Frm 00023
Fmt 4702
Sfmt 4702
Incorporation of Previous Issues of
Airworthiness Limitation (AWL)
(p) Incorporation of AWL No. 28–AWL–21
of Section D of the Boeing 747–100/200/300/
SP Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements
(CMRs), Document D6–13747–CMR, Revision
January 2007, September 2007, or January
2008, is acceptable for compliance with the
corresponding requirements of this AD if
done before the effective date of this AD.
Alternative Methods of Compliance
(AMOCs)
(q)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
Douglas Bryant, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 917–6505; fax (425)
917–6590. Information may be e-mailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(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 principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
E:\FR\FM\19NOP1.SGM
19NOP1
70868
Federal Register / Vol. 75, No. 223 / Friday, November 19, 2010 / Proposed Rules
Office. The AMOC approval letter must
specifically reference this AD.
ssued in Renton, Washington on November
10, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–29231 Filed 11–18–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–1115; Directorate
Identifier 2010–NM–221–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, 747SR, and 747SP
Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD would require repetitive inspections
for damage of the electrical terminal at
the left and right flightdeck window 1,
and corrective actions if necessary. This
proposed AD would also allow for
replacing the flightdeck window 1 with
a new improved flightdeck window
equipped with different electrical
connections, which would terminate the
repetitive inspections for that flightdeck
window 1. This proposed AD was
prompted by several reports of electrical
arcs at the terminal blocks of the
electrically heated flightdeck window 1.
We are proposing this AD to prevent
smoke and fire in the cockpit, which
could lead to loss of visibility, and
injuries to or incapacitation of the
flightcrew.
SUMMARY:
We must receive comments on
this proposed AD by January 3, 2011.
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.
emcdonald on DSK2BSOYB1PROD with PROPOSALS
DATES:
VerDate Mar<15>2010
17:04 Nov 18, 2010
Jkt 223001
• Hand Delivery: Deliver to Mail
address above 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, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, Washington.
For information on the availability of
this material at the FAA, call 425–227–
1221.
Discussion
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
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Louis Natsiopoulos, Aerospace
Engineer, Systems and Equipment
Branch, ANM–130S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington
98057–3356; telephone (425) 917–6478;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Relevant Service Information
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2010–1115; Directorate Identifier 2010–
NM–221–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.
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
We have received multiple reports of
electrical arcs at the terminal blocks of
the flightdeck window 1. In several
incidents, the arcs resulted in open
flames. An investigation showed that
the electrical arcs are caused by loose
terminal connections, which are caused
by incorrect torque of the screw or an
incorrectly installed screw. A loose
terminal connection will overheat with
electrical current passing through it. An
overheated connector can degrade the
adjacent electrical circuit (including
solder, if present). This condition, if not
corrected, could result in smoke and fire
in the cockpit, and consequent loss of
visibility, and injuries to or
incapacitation of the flightcrew.
We have reviewed Boeing Special
Attention Service Bulletin 747–30–
2081, Revision 2, dated March 10, 2010.
Boeing Special Attention Service
Bulletin 747–30–2081, Revision 2, dated
March 10, 2010, describes procedures
for repetitive detailed inspections for
damage (including but not limited to a
cross-threaded screw, arcing, loose
terminal, and heat damage) of the
terminal block, connector, and wiring at
the left and right flightdeck window 1,
and corrective actions if necessary. The
corrective actions are applying the
correct torque to a loose electrical
connection, repairing damaged wiring,
or installing a replacement window 1.
Boeing Special Attention Service
Bulletin 747–30–2081, Revision 2, dated
March 10, 2010, specifies a compliance
time of within 500 hours after the date
on the service bulletin for doing the
initial detailed inspection.
Boeing Special Attention Service
Bulletin 747–30–2081, Revision 2, dated
March 10, 2010, specifies that the
replacement window can either be a
window that uses screws and lugs for
the electrical connection or a window
that uses pins and sockets for the
electrical connections. For airplanes on
which a replacement window that uses
pins and sockets is installed, Boeing
Special Attention Service Bulletin 747–
30–2081, Revision 2, dated March 10,
2010, also specifies changes to the
related wire bundle. Boeing Special
Attention Service Bulletin 747–30–
2081, Revision 2, dated March 10, 2010,
specifies that installing a window that
uses pins and sockets eliminates the
need for the repetitive inspections. If the
window is replaced with the same type
of window (i.e., windows with the
screw and lug type electrical
terminations), then the inspection must
be repeated within 500 flight hours from
E:\FR\FM\19NOP1.SGM
19NOP1
]]>Agencies
[Federal Register Volume 75, Number 223 (Friday, November 19, 2010)]
[Proposed Rules]
[Pages 70863-70868]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-29231]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0090; Directorate Identifier 2007-NM-312-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for certain Model 747 airplanes. The original NPRM would have
required measuring the electrical bond resistance between the motor
operated valve (MOV) actuators and airplane structure for the main,
center, auxiliary, and horizontal stabilizer fuel tanks, as applicable,
and corrective action if necessary. The original NPRM also would have
required a revision to the maintenance program to incorporate
airworthiness limitation (AWL) No. 28-AWL-21 or AWL No. 28-AWL-27, as
applicable. The original NPRM resulted from fuel system reviews
conducted by the manufacturer. This supplemental NPRM would revise the
original NPRM by adding airplanes to the applicability, and would
require replacing production-installed laminate phenolic spacers with
metallic spacers between the fuel jettison MOV and the airplane
structure, as applicable. We are proposing this supplemental NPRM to
prevent electrical current from flowing through an 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.
DATES: We must receive comments on this supplemental NPRM by December
14, 2010.
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 proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced
[[Page 70864]]
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
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: Douglas Bryant, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone
(425) 917-6505; fax (425) 917-6590.
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-2008-0090;
Directorate Identifier 2007-NM-312-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
We issued a notice of proposed rulemaking (NPRM) (the ``original
NPRM'') to amend 14 CFR part 39 to include an airworthiness directive
(AD) that would apply to certain Model 747 airplanes. That original
NPRM was published in the Federal Register on January 31, 2008 (73 FR
5773). That original NPRM proposed to require measuring the electrical
bond resistance between the motor operated valve (MOV) actuators and
airplane structure for the main, center, auxiliary, and horizontal
stabilizer fuel tanks, as applicable, and corrective action if
necessary. That original NPRM also proposed to require a revision to
the maintenance program to incorporate airworthiness limitation (AWL)
No. 28-AWL-21 or AWL No. 28-AWL-27, as applicable.
Actions Since Original NPRM Was Issued
Since we issued the original NPRM, we reviewed Boeing Service
Bulletin 747-28A2292, Revision 2, dated May 13, 2010 (for Model 747-
100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300,
747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes). This
service bulletin clarifies the procedure for measuring the electrical
bond resistance, and adds procedures for replacing production-installed
laminate phenolic spacers with metallic spacers for airplanes in Groups
12, 16, 17, 18, and 19. This service bulletin also adds airplanes to
the Effectivity. Paragraphs (c) and (g) of this supplemental NPRM have
been revised accordingly.
We also reviewed Boeing Service Bulletin 747-28A2294, Revision 1,
dated March 5, 2009 (for Model 747-400 series airplanes equipped with
an active horizontal stabilizer fuel tank). This service bulletin is
the same as the original issue, dated September 21, 2007, except that a
reference to Sub-section 28-17-03 of Boeing 747-400 Airplane
Maintenance Manual (AMM) is corrected in Revision 1.
We reviewed Boeing 747-100/200/300/SP Airworthiness Limitations
(AWLs) and Certification Maintenance Requirements (CMRs), Document D6-
13747-CMR, Revision March 2008 (hereafter referred to as ``Document D6-
13747-CMR''). (We referred to Revision January 2007 of Document D6-
13747-CMR in the original NPRM.) Document D6-13747-CMR revises certain
AWLs for fuel tank systems. However, AWL No. 28-AWL-21, which is
specified in this supplemental NPRM, has not been revised in Document
D6-13747-CMR, Revision March 2008.
We also reviewed the Boeing 747-400 Maintenance Planning Data (MPD)
Document, Section 9, D621U400-9, Revision December 2009 (hereafter
referred to as ``Boeing 747-400 MPD''). Among other things, Subsection
D of Boeing 747-400 MPD has been revised to clarify the
``Applicability'' of AWL No. 28-AWL-27, which is a critical design
configuration control limitation (CDCCL) to maintain the design
features of the MOV actuator.
We have revised this supplemental NPRM to refer to the latest
service information described previously.
Other Relevant Rulemaking
On April 28, 2008, we issued AD 2008-10-07, Amendment 39-15513 (73
FR 25977, May 8, 2008); and on October 30, 2009, we issued AD 2008-10-
07 R1, Amendment 39-16070 (74 FR 56098, November 16, 2009); applicable
to all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747SR, and 747SP series airplanes. Those ADs
require revising the maintenance program by incorporating new AWLs for
fuel tank systems to satisfy Special Federal Aviation Regulation No. 88
(``SFAR 88'') requirements. As an optional action, those ADs also allow
incorporating AWL No. 28-AWL-21 into the maintenance program.
Therefore, we have added a new paragraph (n) to this supplemental NPRM
to specify that incorporating AWL No. 28-AWL-21 into the maintenance
program in accordance with paragraph (g) of AD 2008-10-07 or 2008-10-07
R1 terminates the action required by paragraph (k) of this supplemental
NPRM for the applicable airplanes.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received from the three commenters.
Request To Allow Use of Future Revisions of the Service Bulletins
Boeing requested that we revise the original NPRM to specify that
the proposed modifications may also be done in accordance with any
future-approved revisions to Boeing Alert Service Bulletin 747-28A2292,
dated September 14, 2007; and Boeing Alert Service Bulletin 747-
28A2294, dated September 21, 2007. As justification, Boeing stated that
these service bulletins could be revised by the time we issue the AD.
We partially agree. As discussed previously, we have revised this
supplemental NPRM to refer to the most recently issued service
information. However, we do not agree to refer to ``later revisions.''
To allow operators to use later revisions of the referenced service
documents, either we must revise the AD to reference specific later
revisions, or operators must request approval to use later revisions as
an alternative method of compliance with the AD. Therefore, we have
removed all references to the use of a ``later revision'' of the
applicable service information from this supplemental NPRM to be
[[Page 70865]]
consistent with FAA policy. We may consider approving the use of later
revisions of the service information as an AMOC with this AD, as
provided by paragraph (q) of this supplemental NPRM.
Request To Revise Paragraphs (h) and (i) of the Original NPRM
KLM Royal Dutch Airlines (KLM) stated that the intent of the
original NPRM is to maintain the design features introduced in
accordance with Boeing Alert Service Bulletin 747-28A2292, dated
September 14, 2007; and Boeing Alert Service Bulletin 747-28A2294,
dated September 21, 2007; respectively; when an MOV actuator is
installed. KLM thought that it was clearer if the NPRM stated that the
CDCCLs must be incorporated into the applicable paragraphs of the AMM
to maintain these design features.
We infer that KLM requests that we revise paragraphs (h) and (i) of
the NPRM as proposed above. We disagree with the commenter's request.
We disagree that incorporating CDCCLs into the AMM is the appropriate
location for a CDCCL. The AMM is not an FAA-approved document. The
appropriate location for a CDCCL is in the FAA-approved section (i.e.,
the Airworthiness Limitations section) of an operator's maintenance
program. We have not changed this supplemental NPRM in this regard.
Request To Exclude a Certain Airplane From the Requirements of
Paragraph (g) of the Original NPRM
Lufthansa requested that we exclude a certain Model 747-400 series
airplane from paragraph (g) of the original NPRM because the horizontal
stabilizer tank (HST) on that airplane has never been activated.
We disagree with the request. Although the HST might not be
activated at this time, it could be activated in the future. We cannot
exclude an airplane from the requirements of this supplemental NPRM
without substantiation that the unsafe condition has been adequately
addressed. We have not changed this supplemental NPRM in this regard.
Request To Extend Compliance Time
Lufthansa requested that we extend the compliance time of the
original NPRM from 60 months to 72 months. Lufthansa stated that this
extension will allow operators to implement the modification at the
next maintenance layover.
KLM requested that we extend the compliance time of the original
NPRM from 60 months to 96 months. KLM stated that tank entry might be
necessary for accomplishing the actions, and KLM wanted to avoid tank
entry during C-checks.
We disagree with the commenters' requests to extend the compliance
time. In developing an appropriate compliance time for this
supplemental NPRM, we considered the urgency associated with the
subject unsafe condition and the practical aspect of accomplishing the
required actions on the Model 747 fleet in a timely manner. We
recognize that operators may have different schedules for accomplishing
heavy maintenance, but at the same time, we find that the 60-month
compliance time will include most operators' schedules for that type of
work. Further, according to the provisions of paragraph (q) of this AD,
we may consider approving requests to adjust the compliance time if
those requests include data that prove that the new compliance time
would provide an acceptable level of safety. No change to this
supplemental NPRM is necessary in this regard.
Other Change Made to This Supplemental NPRM
We have added a new paragraph (m) to this supplemental NPRM to
specify that no alternative CDCCLs may be used unless they are approved
as an AMOC. Inclusion of this paragraph in the supplemental NPRM is
intended to ensure that the AD-mandated airworthiness limitations
changes are treated the same as the airworthiness limitations issued
with the original type certificate.
FAA's Determination and Proposed Requirements of the Supplemental NPRM
We are proposing this supplemental NPRM because we evaluated all
pertinent information and determined an unsafe condition exists and is
likely to exist or develop on other products of the same type design.
Certain changes described above expand the scope of the original NPRM.
As a result, we have determined that it is necessary to reopen the
comment period to provide additional opportunity for the public to
comment on this supplemental NPRM.
Explanation of Change to Costs of Compliance
Since issuance of the original NPRM, we have increased the labor
rate used in the Costs of Compliance form $80 per work-hour to $85 per
work-hour. The Costs of Compliance information, below, reflects this
increase in the specified hourly labor rate.
For convenience to the operator, the Estimated Costs table, below,
was revised to break out the cost of replacing the spacers and the on-
condition costs.
Costs of Compliance
We estimate that this proposed AD will affect 222 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Measurement.................... Up to 7 work-hours x Up to $350....... Up to $945....... Up to $209,790.
$85 per hour = Up to
$595.
Replacement (Up to 60 Up to 4 work-hours x $1,305........... Up to $1,645..... Up to $98,700.
airplanes). $85 per hour = Up to
$340.
Maintenance program revision... 1 work-hour x $85 per $0............... $85.............. $18,870.
hour = $85.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary modification
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
this modification:
[[Page 70866]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Change electrical bond and rework 436 work-hours x $85 Up to $35,760........ Up to $72,820.
part contact surface. per hour = $37,060.
----------------------------------------------------------------------------------------------------------------
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, Incorporation by
reference, 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:
The Boeing Company: Docket No. FAA-2008-0090; Directorate Identifier
2007-NM-312-AD.
Comments Due Date
(a) We must receive comments by December 14, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated
in any category; as identified in Boeing Service Bulletin 747-
28A2292, Revision 2, dated May 13, 2010.
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 (q) 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.
Subject
(d) Air Transport Association (ATA) of America Code 28: Fuel.
Unsafe Condition
(e) This AD results from fuel system reviews conducted by the
manufacturer. The Federal Aviation Administration is 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
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Measurement, Corrective Action, and Replacement
(g) Within 60 months after the effective date of this AD, do the
actions required by paragraphs (g)(1) and (g)(2) of this AD, as
applicable.
(1) Measure the electrical bond resistance between the MOV
actuators and the airplane structure for the main, center, and
auxiliary fuel tanks, as applicable; and do all applicable
corrective actions; by accomplishing all of the applicable actions
in the Accomplishment Instructions of Boeing Service Bulletin 747-
28A2292, Revision 2, dated May 13, 2010. The corrective actions must
be accomplished before further flight.
(2) For airplanes in Groups 12, 16, 17, 18, and 19, as
identified in Boeing Service Bulletin 747-28A2292, Revision 2, dated
May 13, 2010: Within 60 months after the effective date of this AD,
replace production-installed laminate phenolic spacers with metallic
spacers, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-28A2292, Revision 2, dated May 13, 2010.
(h) For airplanes identified in Boeing Service Bulletin 747-
28A2294, Revision 1, dated March 5, 2009: Within 60 months after the
effective date of this AD, measure the electrical bond resistance
between the MOV actuators and airplane structure for the horizontal
stabilizer (HST) fuel tanks, and do all the applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-28A2294, Revision 1, dated March 5,
2009. The corrective actions must be accomplished before further
flight.
Deactivation of the HST
(i) For airplanes identified in Boeing Service Bulletin 747-
28A2294, Revision 1, dated March 5, 2009: Deactivation of the HST,
in accordance with the applicable Boeing service information
specified in Table 1 of this AD, terminates the requirements of
paragraph (h) of this AD, except as provided by paragraph (j) of
this AD. Deactivation of the HST before the effective date of this
AD in accordance with the applicable service information specified
in Table 2 of this AD also terminates the requirements of paragraph
(h) of this AD, except as provided by paragraph (j) of this AD.
[[Page 70867]]
Table 1--Deactivation Service Information
------------------------------------------------------------------------
Boeing-- Revision-- Dated--
------------------------------------------------------------------------
Service Bulletin 747-28-2265. Original........ February 22, 2006.
Service Bulletin 747-28-2272. Original........ February 21, 2006.
Service Bulletin 747-28-2274. 1............... May 21, 2008.
Service Bulletin 747-28-2275. 4............... February 2, 2009.
Service Bulletin 747-28-2279. 2............... October 16, 2007.
Service Bulletin 747-28-2285. 3............... August 30, 2007.
Service Bulletin 747-28-2293. 2............... March 4, 2008.
Service Bulletin 747-28-2295. 2............... January 19, 2009.
Service Bulletin 747-28-2296. Original........ July 13, 2007.
Service Bulletin 747-28-2300. 1............... June 2, 2008.
Service Bulletin 747-28-2314. Original........ December 9, 2008.
------------------------------------------------------------------------
Table 2--Deactivation Credit Service Information
------------------------------------------------------------------------
Boeing-- Revision-- Dated--
------------------------------------------------------------------------
Service Bulletin 747-28-2274. Original........ March 13, 2006.
Service Bulletin 747-28-2275. Original........ June 12, 2006.
Service Bulletin 747-28-2275. 1............... March 16, 2007.
Service Bulletin 747-28-2275. 2............... July 2, 2007.
Service Bulletin 747-28-2275. 3............... March 11, 2008.
Service Bulletin 747-28-2279. Original........ June 12, 2006.
Service Bulletin 747-28-2279. 1............... May 25, 2007.
Service Bulletin 747-28-2285. Original........ January 23, 2007.
Service Bulletin 747-28-2285. 1............... May 9, 2007.
Service Bulletin 747-28-2285. 2............... August 3, 2007.
Service Bulletin 747-28-2293. Original........ May 9, 2007.
Service Bulletin 747-28-2293. 1............... August 29, 2007.
Service Bulletin 747-28-2295. Original........ November 17, 2006.
Service Bulletin 747-28-2295. 1............... March 20, 2008.
Service Bulletin 747-28-2300. Original........ January 16, 2008
------------------------------------------------------------------------
Reactivation of the HST
(j) For airplanes identified Boeing Service Bulletin 747-
28A2294, Revision 1, dated March 5, 2009, on which the HST is
reactivated, the HST must be reactivated in accordance with a method
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA. For any airplane on which the HST is reactivated, the
requirements of paragraphs (h) and (l) of this AD must be done
before further flight following the reactivation, or within 60
months after the effective date of this AD, whichever occurs later.
For a reactivation method to be approved, the reactivation method
must meet the certification basis of the airplane, and the approval
must specifically reference this AD.
Maintenance Program Revision
(k) For Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747SR, and 747SP series airplanes:
Concurrently with accomplishing the actions required by paragraph
(g) of this AD, revise the maintenance program by incorporating
airworthiness limitation (AWL) No. 28-AWL-21 of Section D of Boeing
747-100/200/300/SP Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs), Document D6-13747-
CMR, Revision March 2008.
(l) For Model 747-400, 747-400D, and 747-400F series airplanes:
Concurrently with accomplishing the actions required by paragraph
(g) of this AD, revise the maintenance program by incorporating AWL
No. 28-AWL-27 of Subsection D of Boeing 747-400 Maintenance Planning
Data (MPD) Document, Section 9, D621U400-9, Revision December 2009.
No Alternative Critical Design Configuration Control Limitations
(CDCCLs)
(m) After accomplishing the applicable action required in
paragraph (k) or (l) 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 (q) of this AD.
Terminating Action for Maintenance Program Revision
(n) For Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747SR, and 747SP series airplanes:
Incorporating AWL No. 28-AWL-21 into the maintenance program in
accordance with paragraph (g) of AD 2008-10-07, Amendment 39-15513;
or AD 2008-10-07 R1, Amendment 39-16070; terminates the action
required by paragraph (k) of this AD.
Actions Accomplished According to Previous Issue of Service Bulletin
(o) Actions done before the effective date of this AD, in
accordance with Boeing Alert Service Bulletin 747-28A2294, dated
September 21, 2007, are acceptable for compliance with the
corresponding requirements of this AD.
Incorporation of Previous Issues of Airworthiness Limitation (AWL)
(p) Incorporation of AWL No. 28-AWL-21 of Section D of the
Boeing 747-100/200/300/SP Airworthiness Limitations (AWLs) and
Certification Maintenance Requirements (CMRs), Document D6-13747-
CMR, Revision January 2007, September 2007, or January 2008, is
acceptable for compliance with the corresponding requirements of
this AD if done before the effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(q)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Send information to
ATTN: Douglas Bryant, Aerospace Engineer, Propulsion Branch, ANM-
140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW., Renton, Washington 98057-3356; telephone (425) 917-6505; fax
(425) 917-6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(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 principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District
[[Page 70868]]
Office. The AMOC approval letter must specifically reference this
AD.
ssued in Renton, Washington on November 10, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-29231 Filed 11-18-10; 8:45 am]
BILLING CODE 4910-13-P
