[Federal Register Volume 87, Number 14 (Friday, January 21, 2022)]
[Proposed Rules]
[Pages 3246-3250]
[FR Doc No: 2022-01014]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1073; Project Identifier AD-2021-01252-T]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2017-24-10, which applies to certain The Boeing Company Model 757-200,
-200PF, and -300 series airplanes. AD 2017-24-10 requires repetitive
inspections for any cracking of a certain fuselage frame inner chord;
identification of the material of a certain fuselage frame inner chord
for certain

airplanes; and applicable corrective actions. Since the FAA issued AD
2017-24-10, the FAA has received reports of new crack findings outside
of the AD 2017-24-10 inspection area, which the existing inspections
will not detect. This proposed AD would continue to require the actions
in AD 2017-24-10, would add new airplanes and would require new
inspection types in certain areas, an expanded inspection area,
additional inspections, and applicable corrective actions. The FAA is
proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by March 7,
2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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: 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 NPRM, contact Boeing
Commercial Airplanes, Attention: Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com. You may
view this service information at the FAA, Airworthiness Products
Section, Operational Safety Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of this material at the FAA,
call<PHONE_NUMBER>. It is also available at https://www.regulations.gov
by searching for and locating Docket No. FAA-2021-1073.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1073; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this NPRM, any comments
received, and other information. The street address for Docket
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Peter Jarzomb, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone:<PHONE_NUMBER>; email:
[email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2021-1073; Project Identifier
AD-2021-01252-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this proposed AD.

Confidential Business Information

    CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Peter
Jarzomb, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5234; email: [email protected]. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.

Background

    The FAA issued AD 2017-24-10, Amendment 39-19114 (82 FR 57343,
December 5, 2017) (AD 2017-24-10), for certain The Boeing Company Model
757-200, -200PF, and -300 series airplanes. AD 2017-24-10 was prompted
by reports of cracking found at a certain fuselage frame inner chord.
AD 2017-24-10 requires repetitive inspections for any cracking of a
certain fuselage frame inner chord; identification of the material of a
certain fuselage frame inner chord for certain airplanes; and
applicable corrective actions. The agency issued AD 2017-24-10 to
detect and correct such cracks, which could result in the cargo door
opening during flight, and result in rapid decompression of the
airplane and the inability to sustain loads required for continued safe
flight and landing.

Actions Since AD 2017-24-10 Was Issued

    Since the FAA issued AD 2017-24-10, the FAA has received reports of
new crack findings outside of the AD 2017-24-10 inspection area, which
the existing inspections will not detect. An operator was accomplishing
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016,
which is the service information required by AD 2017-24-10) on a
certain The Boeing Company Model 757-200 airplane and found four cracks
ranging from 0.10 to 2.00 inches in length in the station (STA) 1380
frame web and two cracks ranging from 1.00 to 2.12 inches in length in
the frame inner chord. The airplane had 23,005 total flight cycles at
the time of the crack findings. The frame web was made from 0.09 inch
thick 2024-T3 aluminum, and the inner chord was made from 7075-T73
aluminum. Based on the length of the crack in the web at the time of
discovery, the cracks in the frame may have initiated in the 2024-T3
web, and would have been hidden behind the guide track fitting. If the
cracks start in the frame web, existing Maintenance Planning Data (MPD)
and Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016,
inspections do not provide sufficient opportunities to find cracks in
the STA 1380 frame before the critical crack length is reached,
resulting in an airplane-level safety issue.
    In addition, the FAA has received five reports of crack findings in
airplanes with production line numbers 1-57, which are made with 7075
material for the inner and outer chord and the frame web. Those
airplanes may also have a thinner web gauge than that in airplanes with
line numbers 58 and subsequent. Existing inspections for these
airplanes do not remove the guide track fitting at STA 1380, and
therefore do not provide sufficient opportunity to detect cracks

before the critical crack length is reached.
    The root cause for the cracking in the STA 1380 frame inner chord
and web under the roller guide track fitting is attributed to the out-
of-plane bending stress induced from a mis-rigging condition of the No.
2 cargo door, which allows the roller pin on the lower cargo door to
contact the roller guide track fitting. The new proposed repetitive
inspections include removing the guide track fitting to inspect for any
crack. The FAA is issuing this AD to detect and correct such cracks,
which could result in rapid decompression of the airplane and the
inability to sustain loads required for continued safe flight and
landing.

FAA's Determination

    The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin 757-53A0118 RB,
dated October 22, 2021. This service information specifies procedures
for a general visual inspection or a maintenance records check of the
STA 1380 frame for any repair, and repetitive surface high frequency
eddy current (HFEC) inspections of the STA 1380 frame inner chord and
frame web for any cracking, repetitive sub-surface low frequency eddy
current (LFEC) inspections of the STA 1380 frame inner chord for any
cracking, and applicable corrective actions. Corrective actions include
repair.
    This AD would also require Boeing Alert Service Bulletin 757-
53A0101, dated November 8, 2016, which the Director of the Federal
Register approved for incorporation by reference as of January 9, 2018
(82 FR 57343, December 5, 2017).
    This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.

Proposed AD Requirements in This NPRM

    This proposed AD would retain all requirements of AD 2017-24-10.
This proposed AD would add new airplanes and would require new
inspection types in certain areas, an expanded inspection area,
additional inspections, and applicable corrective actions. This
proposed AD would require accomplishment of the actions identified in
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22,
2021, described previously, except for any differences identified as
exceptions in the regulatory text of this proposed AD.
    Accomplishment of the applicable initial inspections and corrective
actions specified in the Accomplishment Instructions of Boeing Alert
Requirements Bulletin 757-53A0118 RB, dated October 22, 2021,
terminates the inspections required by paragraphs (g) and (h) of this
proposed AD.
    For information on the procedures and compliance times, see this
service information at https://www.regulations.gov by searching for and
locating Docket No. FAA-2021-1073.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would
affect 477 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Surface HFEC inspection (retained  5 work-hours x $85               $0  $425 per inspection  $202,725 per
 actions from AD 2017-24-10).       per hour = $425                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
Identify the material (retained    Up to 2 work-hours                0  Up to $170.........  Up to $81,090.
 actions from AD 2017-24-10).       x $85 per hour =
                                    $170.
General visual inspection (new     6 work-hours x $85                0  $510...............  $243,270.
 proposed action).                  per hour = $510.
Surface frame inner chord HFEC     Up to 10 work-hours               0  Up to $850 per       Up to $405,450 per
 inspection (new proposed action).  x $85 per hour =                     inspection cycle.    inspection cycle.
                                    $850 per
                                    inspection cycle.
Sub-surface frame inner chord      Up to 6 work-hours                0  Up to $510 per       Up to $243,270 per
 LFEC inspection (new proposed      x $85 per hour =                     inspection cycle.    inspection cycle.
 action).                           $510 per
                                    inspection cycle.
Surface HFEC frame web inspection  Up to 6 work-hours                0  Up to $510 per       Up to $243,270 per
 (new proposed action).             x $85 per hour =                     inspection cycle.    inspection cycle.
                                    $510 per
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this proposed AD.

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.
    The FAA is 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

    The FAA has 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 that the proposed
regulation:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,

    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2017-24-10, Amendment 39-19114
(82 FR 57343, December 5, 2017), and
0
b. Adding the following new AD:

The Boeing Company: Docket No. FAA-2021-1073; Project Identifier AD-
2021-01252-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive
(AD) action by March 7, 2022.

(b) Affected ADs

    This AD replaces AD 2017-24-10, Amendment 39-19114 (82 FR 57343,
December 5, 2017) (AD 2017-24-10).

(c) Applicability

    This AD applies to all The Boeing Company Model 757-200, -200PF,
-200CB, and -300 series airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of cracking found at the
fuselage station (STA) 1380 frame inner chord and by reports of new
crack findings outside of the AD 2017-24-10 inspection area, which
the existing inspections will not detect. The FAA is issuing this AD
to detect and correct such cracks, which could result in rapid
decompression of the airplane and the inability to sustain loads
required for continued safe flight and landing.

(f) Compliance

    Comply with this AD within the compliance times specified,
unless already done.

(g) Retained Inspection for Group 1 Airplanes, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD
2017-24-10, with no changes. For Group 1 airplanes as identified in
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016:
At the applicable time specified in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 757-53A0101, dated November 8,
2016; except as specified in paragraph (i)(1) of this AD, do a
surface high frequency eddy current (HFEC) inspection for any
cracking of the fuselage STA 1380 frame inner chord, and do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016; except as specified in paragraph (i)(2) of this
AD. Do all applicable corrective actions before further flight.
Repeat the surface HFEC inspection, thereafter, at the times
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 757-53A0101, dated November 8, 2016.

(h) Retained Inspection for Group 2 Airplanes, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD
2017-24-10, with no changes. For Group 2 airplanes as identified in
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016:
At the applicable time specified in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 757-53A0101, dated November 8,
2016, except as specified in paragraph (i)(1) of this AD, identify
the material of the fuselage STA 1380 frame inner chord, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 757-53A0101, dated November 8, 2016.
    (1) If the fuselage STA 1380 frame inner chord material 2024-T42
aluminum alloy is found during any identification required by
paragraph (h) of this AD: No further action is required by this
paragraph for that airplane.
    (2) If the fuselage STA 1380 frame inner chord material 7075-T73
aluminum alloy is found during any identification required by the
introductory text of paragraph (h) of this AD: Before further
flight, do a surface HFEC inspection for any cracking of the
fuselage STA 1380 frame inner chord, and do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016; except as specified in paragraph (i)(2) of this
AD. Do all applicable corrective actions before further flight.
Repeat the surface HFEC inspection thereafter at the times specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
757-53A0101, dated November 8, 2016.

(i) Retained Exceptions to the Service Information, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD
2017-24-10, with no changes.
    (1) Where Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016, specifies a compliance time ``after the original
issue date of this service bulletin,'' this AD requires compliance
within the specified compliance time after January 9, 2018 (the
effective date of AD 2017-24-10).
    (2) Where Boeing Alert Service Bulletin 757-53A0101, dated
November 8, 2016, specifies to contact Boeing for appropriate action
and identifies that action as ``RC'' (Required for Compliance):
Before further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (m) of this
AD.

(j) New Required Actions

    Except as specified by paragraph (k) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021,
do all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
757-53A0118 RB, dated October 22, 2021.
    Note 1 to paragraph (j): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
757-53A0118, dated October 22, 2021, which is referred to in Boeing
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021.

(k) New Exceptions to Service Information Specifications

    (1) Where the Compliance Time column of the tables in the
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 757-
53A0118 RB, dated October 22, 2021, uses the phrase ``the original
issue date of the Requirements Bulletin 757-53A0118 RB,'' this AD
requires using ``the effective date of this AD.''
    (2) Where Boeing Alert Requirements Bulletin 757-53A0118 RB,
dated October 22, 2021, specifies contacting Boeing for repair
instructions or for alternative inspections: This AD requires doing
the repair, or doing the alternative inspections and applicable on-
condition actions using a method approved in accordance with the
procedures specified in paragraph (m) of this AD.

(l) Terminating Action for Certain Inspections

    Accomplishment of the applicable initial inspections and
corrective actions specified in the Accomplishment Instructions of
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22,
2021, terminates the inspections required by paragraphs (g) and (h)
of this AD.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, FAA, has the authority
to approve AMOCs for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
request to your principal inspector or responsible Flight Standards
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (n)(1) of this AD. Information may be
emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate
principal inspector,

or lacking a principal inspector, the manager of the responsible
Flight Standards Office.
    (3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Los
Angeles ACO Branch, FAA, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
    (4) AMOCs approved previously for AD 2017-24-10 are not approved
as AMOCs with this AD.
    (5) Except as specified by paragraph (i) of this AD: For service
information that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (m)(5)(i) and (ii) of
this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.

(n) Related Information

    (1) For more information about this AD, contact Peter Jarzomb,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5234; email: [email protected].
    (2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone<PHONE_NUMBER>; internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des Moines, WA. For information
on the availability of this material at the FAA, call<PHONE_NUMBER>.

    Issued on December 10, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-01014 Filed 1-20-22; 8:45 am]
BILLING CODE 4910-13-P


revision                 geographic area    submittal date   EPA approval date       explanation
----------------------------------------------------------------------------------------------------------------

                                                  * * * * * * *
Section 110(a)(2) Infrastructure  Statewide...........         6/18/14  3/4/15 [Insert       This action
 Requirements for the 2010                                               Federal Register     addresses the
 Sulfur Dioxide NAAQS.                                                   citation].           following CAA
                                                                                elements, or
                                                                                portions thereof:
                                                                                110(a)(2)(A), (B),
                                                                                (C), (D)(i)(II)
                                                                                (PSD), (D)(ii),
                                                                                (E)(i), (E)(iii),
                                                                                (F), (G), (H), (J)
                                                                                (consultation,
                                                                                notification, and
                                                                                PSD), (K), (L),
                                                                                and (M).
----------------------------------------------------------------------------------------------------------------

[FR Doc. 2015-04377 Filed 3-3-15; 8:45 am]
BILLING CODE 6560-50-P


[Federal Register: March 7, 2008 (Volume 73, Number 46)]
[Proposed Rules]
[Page 12301-12303]
[DOCID:fr07mr08-18]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27339; Directorate Identifier 2006-NM-280-AD]
RIN 2120-AA64

Airworthiness Directives; McDonnell Douglas Model DC-10-10 and
DC-10-10F Airplanes, Model DC-10-15 Airplanes, Model DC-10-30 and DC-
10-30F (KC-10A and KDC-10) Airplanes, Model DC-10-40 and DC-10-40F
Airplanes, Model MD-10-10F and MD-10-30F Airplanes, and Model MD-11 and
MD-11F Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.

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SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for certain transport category airplanes identified above. The
original NPRM would have required modifying the fuel boost pumps. The
original NPRM resulted from a fuel boost pump found with blown thermal
fuses and a fractured thrust washer. This action revises the original
NPRM by referring to new service information, which would require more
work. We are proposing this supplemental NPRM to prevent failure of the
fuel boost pumps, which could lead to the potential of ignition sources
inside fuel tanks. This condition, in combination with flammable fuel
vapors, could result in fuel tank explosions and consequent loss of the
airplane.

DATES: We must receive comments on this supplemental NPRM by April 1,
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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, Long Beach Division, 3855 Lakewood Boulevard,
Long Beach, California, 90846, Attention: Data and Service Management,
Dept. C1-L5A (D800-0024).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
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<PHONE_NUMBER>) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.

FOR FURTHER INFORMATION CONTACT: Samuel Lee, Aerospace Engineer,
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>.

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-2007-
27339; Directorate Identifier 2006-NM-280-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 http://
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 McDonnell Douglas Model DC-10-10 and
DC-10-10F airplanes, Model DC-10-15 airplanes, Model DC-10-30 and DC-
10-30F (KC-10A and KDC-10) airplanes, Model DC-10-40 and DC-10-40F
airplanes, Model MD-10-10F and MD-10-30F airplanes, and Model MD-11 and
MD-11F airplanes. That original NPRM was published in the Federal
Register on February 26, 2007 (72 FR 8307). That original NPRM proposed
to require modifying the fuel boost pumps.

Actions Since Original NPRM Was Issued

    Since we issued the original NPRM, Boeing and Crane Hydro-Aire have
revised their service information for modifying certain fuel boost
pumps. The original NPRM referred to Boeing Alert Service Bulletin
DC10-28A254 and Boeing Alert Service Bulletin MD11-28A134, both dated
September 8, 2006, which in turn refer to Crane Hydro-Aire Service
Bulletin 60-847-28-3, dated May 1, 2006, as an additional source of
service information for accomplishing the modification. This
supplemental NPRM refers to the revised service information, which
would require more work. The additional work involves rerouting the
stator-to-connector wire leads for fuel boost pumps modified according
to the original issue of Crane Hydro-Aire Service Bulletin 60-847-28-3.

Relevant Service Information

    We have reviewed the following service bulletins:
     Boeing Alert Service Bulletin DC10-28A254, Revision 1,
dated September 12, 2007, for Model DC-10-10 and DC-10-10F airplanes,
Model DC-10-15 airplanes, Model DC-10-30 and DC-10-30F (KC-10A and KDC-
10) airplanes, Model DC-10-40 and DC-10-40F airplanes, and Model MD-10-
10F and MD-10-30F airplanes.
     Boeing Alert Service Bulletin MD11-28A134, Revision 1,
dated September 6, 2007, for Model MD-11 and MD-11F airplanes.
    Revision 1 of the service bulletins describe procedures for
modifying fuel boost pumps, part numbers (P/Ns) 60-847-1A, -2, and -3,
as applicable. The service bulletins also refer to Crane Hydro-Aire
Service Bulletin 60-847-28-3, Revision 1, dated July 2, 2007, as an
additional source of service information for modifying the fuel boost
pumps. The modification involves upgrading the rotor assembly by
replacing the Stellite thrust washer with a stainless steel thrust
washer manufactured after a certain date, inspecting the stator
assembly wire leads, replacing the stator assembly with a new assembly
if necessary, rerouting the stator-to-connector wire leads if
necessary, and replacing the washers, screws, and other hardware with
new parts. Fuel boost pumps modified according to the original issue of
Crane Hydro-Aire Service Bulletin 60-847-28-3 need to be reworked by
rerouting

the stator-to-connector wire leads to prevent damage to the wire leads
during pump assembly.
    Revision 1 of Crane Hydro-Aire Service Bulletin 60-847-28-3
specifies prior accomplishment of Crane Hydro-Aire Service Bulletin 60-
847-1A-28-6, dated February 15, 1973, for fuel boost pump P/N 60-847-
1A. Crane Hydro-Aire Service Bulletin 60-847-28-3 also specifies prior
accomplishment of Crane Hydro-Aire Service Bulletin 60-847-3-28-13,
dated March 17, 1975, for fuel boost pump P/N 60-847-2.

Comments

    We gave the public the opportunity to participate in developing
this AD. We considered the comments received from the one commenter.

Request To Limit the Scope of the Modification

    Boeing requests that we limit the scope of the proposed
modification to replacing the Stellite thrust washer with a steel
washer. Boeing suggests that we revise paragraph (g) of the
supplemental NPRM to specify that operators must modify the fuel boost
pump by replacing the Stellite thrust washer with a steel thrust
washer. Boeing also suggests that we delete the sentence regarding the
modification details from the ``Relevant Service Information'' section
of the original NPRM and replace it with the following sentences: ``The
primary required modification involves upgrading the rotor assembly to
include a new thrust washer. The service information also includes
instructions for inspecting the stator assembly wire leads, and
rerouting the stator-to-connector wire leads with sleeving, if
necessary. Washers, screws, and other miscellaneous hardware are also
replaced.'' As justification, Boeing states that modification of the
fuel boost pumps is solely driven by the need to replace the Stellite
thrust washer, and that this action alone will address the unsafe
condition. Boeing also states that the other actions mentioned in the
``Relevant Service Information'' section of the original NPRM are not
related to the unsafe condition. Boeing states that those other actions
depend on the serviceability of certain components within the pump
assembly, which is determined during pump disassembly and the
inspection. Boeing asserts that the related information was included in
Crane Hydro-Aire Service Bulletin 60-847-28-3 to highlight certain
component serviceability checks that are done as part of any pump
disassembly and should be emphasized as part of the required action.
According to Boeing, this is particularly true for rerouting the
stator-to-connector wire leads, since the connector must be removed and
replaced with a new connector in order to reroute the wire leads.
Boeing states that if the connector is serviceable, the wire leads do
not need to be rerouted. Additionally, replacement of the existing
attachment hardware, screws, and washers is a consequence of
disassembly/assembly of the pump, as part of thrust washer replacement.
    We agree that the primary action of the modification is to replace
the Stellite thrust washer with a stainless steel thrust washer. We
also agree that replacement of the electrical connector of the pump
assembly depends upon the inspection results. We have revised the
``Relevant Service Information'' section of this supplemental NPRM to
specify that the modification involves replacing the stator assembly
with a new assembly if necessary, and rerouting the stator-to-connector
wire leads if necessary.
    However, we have determined that both the physical integrity of the
thrust washer and the critical configuration control of the routing of
the stator lead wires must be addressed in order to minimize potential
ignition sources associated with failure of a fuel boost pump. This is
accomplished by replacing the Stellite thrust washer, inspecting the
stator wire leads, and replacing the stator assembly if necessary.
Operators must also verify that the stator-to-connector wire leads are
properly routed, and reroute the wire leads if necessary. Therefore, we
have not revised paragraph (g) of this supplemental NPRM.

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.

Costs of Compliance

    We estimate that this proposed AD would affect 360 airplanes of
U.S. registry. We also estimate that it would take about 3 work-hours
per fuel boost pump to comply with this proposed AD. The average labor
rate is $80 per work-hour. Required parts would cost about $640 per
fuel boost pump. Depending on the airplane configuration, there are
between 10 and 19 fuel boost pumps per product. Based on these figures,
we estimate the cost of this proposed AD to the U.S. operators to be
between $3,168,000 and $6,019,200, or between $8,800 and $16,720 per
product.

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:

McDonnell Douglas: Docket No. FAA-2007-27339; Directorate Identifier
2006-NM-280-AD.

Comments Due Date

    (a) We must receive comments by April 1, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the airplanes identified in paragraphs
(c)(1) and (c)(2) of this AD, certificated in any category.
    (1) McDonnell Douglas Model DC-10-10 and DC-10-10F airplanes,
Model DC-10-15 airplanes, Model DC-10-30 and DC-10-30F (KC-10A and
KDC-10) airplanes, Model DC-10-40 and DC-10-40F airplanes, and Model
MD-10-10F and MD-10-30F airplanes; as identified in Boeing Alert
Service Bulletin DC10-28A254, Revision 1, dated September 12, 2007.
    (2) McDonnell Douglas Model MD-11 and MD-11F airplanes, as
identified in Boeing Alert Service Bulletin MD11-28A134, Revision 1,
dated September 6, 2007.

Unsafe Condition

    (d) This AD results from a fuel boost pump found with blown
thermal fuses and a fractured thrust washer. We are issuing this AD
to prevent failure of the fuel boost pumps, which could lead to the
potential of ignition sources inside fuel tanks. This condition, in
combination with flammable fuel vapors, could result in fuel tank
explosions and consequent loss of the airplane.

Compliance

    (e) Comply with this AD within the compliance times specified,
unless already done.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the
following service bulletins, as applicable:
    (1) For the airplanes identified in paragraph (c)(1) of this AD,
Boeing Alert Service Bulletin DC10-28A254, Revision 1, dated
September 12, 2007.
    (2) For the airplanes identified in paragraph (c)(2) of this AD,
Boeing Alert Service Bulletin MD11-28A134, Revision 1, dated
September 6, 2007.

    Note 1: Boeing Alert Service Bulletin DC10-28A254, Revision 1,
dated September 12, 2007; and Boeing Alert Service Bulletin MD11-
28A134, Revision 1, dated September 6, 2007; refer to Crane Hydro-
Aire Service Bulletin 60-847-28-3, Revision 1, dated July 2, 2007,
as an additional source of service information for accomplishing the
modification in paragraph (g) of this AD.

Modification

    (g) At the applicable compliance time specified in paragraph
(g)(1) or (g)(2) of this AD, modify the fuel boost pumps having part
numbers 60-847-1A, -2, and -3, in accordance with the Accomplishment
Instructions of the applicable service bulletin.
    (1) For fuel boost pumps identified as Configuration 1 or 2 in
Table 1 of paragraph 1.E. of the applicable service bulletin, do the
modification within 120 months after the effective date of this AD.
    (2) For fuel boost pumps identified as Configuration 3 in Table
1 of paragraph 1.E. of the applicable service bulletin, do the
modification within 72 months after the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, Los Angeles Aircraft Certification Office,
FAA, ATTN: Samuel Lee, Aerospace Engineer, Propulsion Branch, ANM-
140L, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone<PHONE_NUMBER>; fax<PHONE_NUMBER>; 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 March 3, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
 [FR Doc. E8-4475 Filed 3-6-08; 8:45 am]

BILLING CODE 4910-13-P


[Federal Register Volume 79, Number 25 (Thursday, February 6, 2014)]
[Notices]
[Pages 7257-7258]
[FR Doc No: 2014-02561]

-----------------------------------------------------------------------

SECURITIES AND EXCHANGE COMMISSION

[Release No. 34-71181A; File No. SR-Topaz-2013-19]

Self-Regulatory Organizations; Topaz Exchange, LLC; Notice of
Filing and Immediate Effectiveness of Proposed Rule Change To More
Specifically Address the Number and Size of Contra-Parties to a
Qualified Contingent Cross Order; Correction

December 24, 2013.
AGENCY: Securities and Exchange Commission.

ACTION: Notice; correction.

-----------------------------------------------------------------------

SUMMARY: The Securities and Exchange Commission published a document in
the Federal Register of December 31, 2013 concerning a Notice of Filing
and Immediate Effectiveness of Proposed Rule Change to More
Specifically Address the Number and Size of Contra-parties to a
Qualified Contingent Cross Order. The document was dated incorrectly.

FOR FURTHER INFORMATION CONTACT: Jennifer Colihan, Division of Trading
and Markets, Securities and Exchange

Commission, 100 F Street NE., Washington, DC 20549,<PHONE_NUMBER>.

Correction

    In the Federal Register of December 31, 2013, in FR Doc. 2013-
31227, on page 79718, in the 49th line of the third column, the date is
corrected to read as noted above.

Kevin M. O'Neill,
Deputy Secretary.
[FR Doc. 2014-02561 Filed 2-5-14; 8:45 am]
BILLING CODE 8011-01-P


1.  Radiological issue – Does the currently generated sludge have a
radiological component (i.e., is this sludge a mixed waste)?  In the FR
notice for the proposed delisting of the currently generated sludge (64
FR 42320) we wrote, based on information that you submitted, that “In
June 1990, the filter cake was found to contain trace levels of special
nuclear material (i.e., uranium at typically less than 30 picocuries per
gram).  As of October 1991, this special nuclear material contamination
was eliminated from the filter cake.”

In the description of waste streams in the delisting petition, the low
level radioactive treatment system receives small quantities of
radioactive materials including uranium and radioactive materials
contained in storm water from building roofs.  Does precipitation and
microfiltration sufficiently remove the radioactive component in this
waste so that subsequent sludge formation is not a mixed waste?

2.  How is the current delisted filter cake disposed of?  The delisting
for this waste includes a condition requiring it be disposed in a
Subtitle D landfill.

3.  All Federal delistings granted are conditional exclusions which
include several conditions including a condition prescribing permissible
disposal.  For a typical delisted waste, this condition has been
disposal in a Subtitle D landfill.  What disposal options are available
for management of this material under NRC regulations?  Does NRC
regulation of the sludge continue indefinitely, or does it end if the
radiation levels drop below some limit?  We’ve been assuming that
disposal in a Subtitle D landfill is not an option.

4.  Fluoride in groundwater – Based on recent analysis of Final
Effluent Pond (FEP) groundwater monitoring samples, has the
concentration of fluoride in the groundwater changed since the sampling
events of the 2001/2002 timeframe?

5.  Fluoride in sludge – Fluoride concentration (both total and
leachate) were determined on filter cake for the January 14, 2000
delisting of the (then) currently produced sludge. Fluoride
concentrations were determined on sludge samples (not dewatered filter
cake) collected from the FEPs for the pending delisting petition.

Do you have analytical results that show total and leachable fluoride
concentrations for dewatered FEP sludge?  Perhaps you collected some
fluoride data on filtered samples when you did the recent FEP sludge
removal project.

6.  Active life of the FEPs – Do you have a revised estimate of how
many years you expect to utilize the FEPs until they are decommissioned
and closed?