[Federal Register Volume 85, Number 35 (Friday, February 21, 2020)]
[Rules and Regulations]
[Pages 10043-10047]
[FR Doc No: 2020-03276]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0156; Product Identifier 2019-CE-053-AD; Amendment
39-21029; AD 2020-03-16]
RIN 2120-AA64

Airworthiness Directives; Textron Aviation Inc. (Type Certificate
Previously Held by Cessna Aircraft Company)

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Textron Aviation Inc. (Textron) (type certificate previously held by
Cessna Aircraft Company) Models 210G, T210G, 210H, T210H, 210J, T210J,
210K, T210K, 210L, T210L, 210M, and T210M airplanes. This AD requires
visual and eddy current inspections of the carry-thru spar lower cap,
corrective action if necessary, application of a protective coating and
corrosion inhibiting compound (CIC), and reporting the inspection
results to the FAA. This AD was prompted by the in-flight break-up of a
Model T210M airplane in Australia, due to fatigue cracking that
initiated at a corrosion pit, and subsequent reports of other Model
210-series airplanes with widespread and severe corrosion. The FAA is
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective March 9, 2020.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 9,
2020.
    The FAA must receive comments on this AD by April 6, 2020.

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: 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 final rule, contact
Textron Aviation Inc. One Cessna Boulevard, Wichita, Kansas 67215;
phone:<PHONE_NUMBER>; email<EMAIL_ADDRESS>internet: https://support.cessna.com. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>. It is also available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2020-0156.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0156; 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 final rule, the regulatory evaluation, any comments received, and
other information. The street address for Docket Operations is listed
above. Comments will be available in the AD docket shortly after
receipt.

FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, Aerospace Engineer,
Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209;
telephone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>or acfbc5cfc4c5d8cd81efe3ffeccacdcd82cbc3da.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA received a report that, on May 26, 2019, a Textron Model
T210M airplane experienced an in-flight break-up while performing low-
altitude aerial survey operations in Australia. The carry-thru spar
failed and resulted in wing separation and loss of control of the
airplane. A visual examination of the fracture surface identified
fatigue cracking that initiated at a corrosion pit. The FAA issued an
airworthiness concern sheet (ACS) on June 27, 2019, advising owners and
operators of the accident and requesting relevant information about the
fleet.
    Following the ACS, the FAA received reports of widespread and
severe corrosion of the carry-thru spar on Models 210G, T210G, 210H,
T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, and T210M
airplanes. Further investigation identified that these early model
airplanes were manufactured without corrosion protection or primer,
increasing their susceptibility to corrosion. Additionally, the design
of these early model airplanes, where the upper surface of the spar is
exposed to the environment, allows a pathway for moisture intrusion.
Model 210-series airplanes were also delivered with foam installed
along the carry-thru spar lower cap. The foam traps moisture against
the lower surface of the carry-thru spar cap, which can increase the
development of corrosion.
    Corrosion of the carry-thru spar lower cap can lead to fatigue
cracking or reduced structural strength of the carry-thru spar, which
could result in separation of the wing and loss of airplane control.
The FAA is issuing this AD to address the unsafe condition on these
products.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Textron Aviation Mandatory Single Engine Service
Letter SEL-57-08, Revision 1, dated November 19, 2019 (SEL-57-08 R1).
This service information contains instructions for visually inspecting
the carry-thru spar for corrosion, damage, and cracks and for
completing an eddy current inspection. This service information also
specifies applying protective coating and CIC.
    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.

Other Related Service Information

    The FAA reviewed Textron Aviation Mandatory Single Engine Service
Letter SEL-57-08, dated November 1, 2019, which contains the same
instructions and repair criteria as SEL-57-08 R1.
    The FAA also reviewed Textron Aviation Mandatory Single Engine
Service Letter SEL-57-06, dated June 24, 2019, and Textron Aviation
Mandatory Single Engine Service Letter SEL-57-06, Revision 1, dated
November 19, 2019. This service information contains instructions for
visually inspecting the carry-thru spar for corrosion and doing an eddy
current inspection of the carry-thru spar regardless of whether
corrosion is found and removed. This service information also contains
instructions for applying CIC, but does not specify applying protective
coating.

FAA's Determination

    The FAA is issuing this AD because the FAA evaluated all the
relevant information and determined the unsafe condition described
previously is likely to exist or develop in other products of the same
type design.

AD Requirements

    This AD requires accomplishing the actions specified in SEL-57-08
R1 with the exception of the differences discussed in the Differences
Between the AD and the Service Information section located below. This
AD also requires reporting the inspection results to the FAA by email
at<EMAIL_ADDRESS>
Differences Between the AD and the Service Information

     Although Textron SEL-57-08 R1 also applies to Models 210N,
P210N, T210N, 210R, P210R, and T210R airplanes, this AD does not.
Models 210N, P210N, T210N, 210R, P210R, and T210R airplanes were
manufactured with corrosion protection. While the spars on these models
are subject to corrosion, the reports the FAA has received indicate the
corrosion is not as widespread or severe as on the earlier models
manufactured without corrosion protection. Therefore, the FAA has
determined to not include Models 210N, P210N, T210N, 210R, P210R, and
T210R airplanes in this immediate AD action; however, the FAA may take
AD action that applies to these models in the future.
     Textron SEL-57-08 R1 allows up to 12 months to comply with
the actions in the service letter. Due to the widespread and severe
corrosion affecting a substantial number of airplanes, this AD requires
compliance no later than 60 days after the effective date of this AD.
     Textron SEL-57-08 R1 specifies inspecting all interior
surfaces of the carry-thru spar, while this AD only requires inspecting
the carry-thru spar lower cap, including the lower surface, edge, and
upper surface of the lower cap. While the web and upper cap of the
carry-thru spar may be susceptible to corrosion, evidence does not
support including inspection of these areas as part of this AD. The FAA
will continue to monitor reports of corrosion on all areas of the
carry-thru spar for potential future action.
     Textron SEL-57-08 R1 does not require an eddy current
inspection on the carry-thru spar unless the amount of material removed
in the blended area exceeds 0.010 inch deep but is within limits. This
AD requires eddy current inspection of all locations on the carry-thru
spar where corrosion was removed. The fatigue crack on the Model T210M
airplane that suffered the in-flight break-up initiated from a
corrosion pit approximately 0.011 inch deep in the lower cap kick area.
The less restrictive eddy current inspection requirements specified in
SEL-57-08 R1 could potentially miss similar fatigue cracks on airplanes
currently operating in the field.
     Textron SEL-57-08 R1 only requires an eddy current
inspection of the lower cap kick of the carry-thru spar if corrosion is
identified on the carry-thru spar cap. This AD requires a one-time eddy
current inspection of the lower cap kick area of all affected
airplanes, regardless of the results of the visual inspection. The
fatigue crack on the Model T210M airplane that suffered the in-flight
break-up initiated in the lower cap kick area. Cracks and corrosion
damage may be difficult to identify through visual inspection alone.
The FAA will use the results of the one-time eddy current inspection of
the lower cap kick area, in part, to determine the necessity of future
rulemaking action.
     Textron SEL-57-08 R1 specifies contacting Textron for
evaluation and disposition of certain damage. Instead, this AD requires
removing the carry-thru spar from service or repairing it (if possible)
in accordance with the AMOC procedures identified in paragraph (o) of
this AD. Operators should work with Textron to develop a repair in
support of an AMOC request.
     Textron SEL-57-08 R1 provides instruction allowing
airplanes that have complied with SEL-57-06 to complete the application
of the protective coating and CIC within 200 flight hours or at the
next annual inspection, whichever occurs first. This AD permits those
airplanes that have complied with the visual and eddy current
inspections in SEL-57-06, as required in paragraphs (g) and (h) of this
AD, to complete the application of the protective coating and CIC
within 12 months from the date of the visual and eddy current
inspections.

Interim Action

    The FAA considers this AD interim action. This AD requires a one-
time visual inspection of specified areas on the carry-thru spar lower
cap and an eddy current inspection of the lower cap kick area and any
locations where corrosion was removed. This AD also requires reporting
the inspection results to the FAA. The FAA will analyze the inspection
results received to determine further rulemaking action.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies waiving notice and comment prior to adoption of this rule
because of a severe and widespread corrosion issue affecting the carry-
thru spar lower cap on some Textron Model 210-series airplanes. As of
January 29, 2020, Textron has received 194 inspection reports on Models
210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M,
and T210M airplanes. Of these 194 reports, 96 airplanes have reported
corrosion (49 percent) with 18 of those reports (9 percent) resulting
in removing the carry-thru spar from service. The corrosion observed
included several instances of exfoliation corrosion and stress
corrosion cracking. The FAA has determined that the large number of
corrosion reports and the severity of the corrosion identified on a
critical single load path part necessitate issuance of an immediately
adopted rule. If the corrosion initiates a fatigue crack or affects the
carry-thru spar's ability to support the required structural loads, the
airplane may suffer a catastrophic failure. Therefore, the FAA finds
good cause that notice and opportunity for prior public comment are
impracticable. In addition, for the reasons stated above, the FAA finds
that good cause exists for making this amendment effective in less than
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, the FAA invites you to send any written data, views,
or arguments about this final rule. Send your comments to an address
listed under the ADDRESSES section. Include the Docket Number FAA-2020-
0156 and Product Identifier 2019-CE-053-AD at the beginning of your
comments. The FAA specifically invites comments on the overall
regulatory, economic, environmental, and energy aspects of this final
rule. The FAA will consider all comments received by the closing date
and may amend this final rule because of those comments.
    The FAA will post all comments the FAA receives, without change, to
https://www.regulations.gov, including any personal information you
provide. The FAA will also post a report summarizing each substantive
verbal contact the FAA receives about this final rule.

Costs of Compliance

    The FAA estimates that this AD affects 1,520 airplanes of U.S.
registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per      Cost on U.S.
              Action                    Labor cost             Parts cost             product        operators
----------------------------------------------------------------------------------------------------------------
Inspections (includes part         15.5 work-hours x    $340....................       $1,657.50      $2,519,400
 removal for access, removal of     $85 per hour =
 foam, visual inspection, eddy      $1,317.50.
 current inspection of the cap
 kick area, application of primer
 and corrosion inhibitor and
 reassembly).
Report of inspection results.....  2 work-hours x $85   Not applicable..........             170         258,400
                                    per hour = $170.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repairs
based on the results of the inspection. The FAA has no way of
determining the number of airplanes that might need these repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                Action                          Labor cost                   Parts cost               product
----------------------------------------------------------------------------------------------------------------
Corrosion removal.....................  2 work-hours x $85 per     Not applicable...............            $170
                                         hour = $170.
On-condition eddy current inspection..  1 work-hour x $85 per      Not applicable...............              85
                                         hour = $85.
Spar replacement......................  160 work-hours x $85 per   $30,000......................          43,600
                                         hour = $13,600.
----------------------------------------------------------------------------------------------------------------

    The amount of work-hours necessary to complete the eddy current
inspection and remove the corrosion will depend on the extent of the
corrosion on the spar. The FAA has no way of estimating the work-hours
that may be required for those procedures. The FAA's cost estimate
assumes a minimum of one hour for the eddy current inspection and two
hours for the corrosion removal. Replacement spars are not currently
available from Textron. Textron no longer produces the current spar
design, and they are working to develop a new spar design. The FAA does
not have data to determine the availability of replacement spars from
other sources.

Paperwork Reduction Act

    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 currently 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 2 hours per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, completing and reviewing the collection of
information. All responses to this collection of information are
mandatory. Send comments regarding this burden estimate or any other
aspect of this collection of information, including suggestions for
reducing this burden to: Information Collection Clearance Officer,
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX
76177-1524.

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 Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because FAA has determined
that it has good cause to adopt this rule without notice and comment,
RFA analysis is not required.

Regulatory Findings

    This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866, and
    (2) Will not affect intrastate aviation in Alaska.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness
directive (AD):

2020-03-16 Textron Aviation Inc. (type certificate previously held
by Cessna Aircraft Company): Amendment 39-21029; Docket No. FAA-
2020-0156; Product Identifier 2019-CE-053-AD.

(a) Effective Date

    This AD is effective March 9, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Textron Aviation Inc. (type certificate
previously held by Cessna Aircraft Company) Models 210G, T210G,
210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, and T210M
airplanes, all serial numbers, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 5310, Fuselage Main, Structure.

(e) Unsafe Condition

    This AD was prompted by the in-flight break-up of a Model T210M
airplane due to fatigue cracking of the carry-thru spar that
initiated at a corrosion pit and subsequent reports of other Model
210-series airplanes with widespread and severe corrosion. The FAA
is issuing this AD to detect and correct cracks, corrosion, and
other damage of the carry-thru spar lower cap, which, if not
corrected, could lead to the carry-thru spar being unable to support
the required structural loads and could result in separation of the
wing and loss of airplane control.

(f) Compliance

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

(g) Visual Inspection

    Within 60 days after March 9, 2020 (the effective date of this
AD) or within the next 20 hours time-in-service (TIS) after March 9,
2020 (the effective date of this AD), whichever occurs first,
prepare the carry-thru spar lower cap for inspection by following
steps 4 and 5 of the Accomplishment Instructions in Textron Aviation
Mandatory Single Engine Service Letter SEL-57-08, Revision 1, dated
November 19, 2019 (SEL-57-08 R1). Visually inspect the carry-thru
spar lower cap (including the lower surface, upper surface, and
edge) with a 10X magnification lens looking for corrosion, cracks,
and damage. You are not required to inspect the lower cap to web
radius, spar web, or upper cap. Refer to the `Spar Dimensions'
figure on page 6 and the `Spar Detail' figure on page 7 of SEL-57-08
R1 for the location of the specific spar features.
    (1) If there is a crack, before further flight, remove the
carry-thru spar from service.
    (2) If there is damage or evidence of previous removal of
corrosion (blending), before further flight, either remove the
carry-thru spar from service or repair the area using a method
approved as specified in paragraph (o) of this AD. Comply with the
requirements in paragraph (h) of this AD before further flight.
    (3) If there is any corrosion, before further flight, remove the
corrosion in the affected area by following steps 6.B.(1) through
(7) of the Accomplishment Instructions in SEL-57-08 R1 and then
mechanically measure the depth of the blended area using a straight
edge and feeler gauge or a depth gauge micrometer.
    (i) If the material removed in the blended area exceeds the
allowable blend limits specified in table 1 (including the notes) of
SEL-57-08 R1, before further flight, either remove the carry-thru
spar from service or repair the area using a method approved as
specified in paragraph (o) of this AD. Comply with the requirements
in paragraph (h) of this AD before further flight.
    (ii) If the material removed in the blended area does not exceed
the allowable blend limits specified in table 1 (including the
notes) of SEL-57-08 R1, comply with the requirements in paragraph
(h) of this AD before further flight.
    (4) If the visual inspection did not detect corrosion, cracks,
or damage and there is no evidence of previous removal of corrosion,
comply with the requirements in paragraph (h) of this AD before
further flight.

(h) Eddy Current Inspection

    (1) Complete an eddy current inspection of the carry-thru spar
lower cap for cracks, corrosions, and damage in the following areas
in accordance with step 7 of the Accomplishment Instructions in SEL-
57-08 R1.
    (i) The kick area as depicted in the `Spar Dimensions' figure on
page 6 of SEL-57-08 R1. You must complete an eddy current inspection
of the lower cap kick area of your airplane regardless of whether
corrosion was found as a result of the visual inspection in
paragraph (g) of this AD.
    (ii) All areas where corrosion was found and removed as a result
of the inspection in paragraph (g) of this AD.
    (2) If there is a crack, before further flight, remove the
carry-thru spar from service.
    (3) If there is any damage, before further flight, either remove
the carry-thru spar from service or repair the area using a method
approved as specified in paragraph (o) of this AD. After completing
the repair, repeat the eddy current inspection of the repaired area
before further flight.
    (4) If there is any corrosion, before further flight, remove the
corrosion by following the requirements in paragraph (g)(3) of this
AD. You must repeat the eddy current inspection and comply with
paragraph (h) of this AD for the area where the additional material
was removed, but you do not have to repeat the eddy current
inspection of the kick area.

(i) Corrosion Protection

    Before further flight after completing the eddy current
inspection in paragraph (h) of this AD, apply protective coating and
corrosion inhibiting compound (CIC) by following steps 9 and 10 of
the Accomplishment Instructions in SEL-57-08 R1.

(j) Installation Prohibition

    As of March 9, 2020 (the effective date of this AD), do not
install on any airplane a carry-thru spar unless it has been
inspected as required by paragraphs (g) and (h) of this AD and
corrosion protection applied as required by paragraph (i).

(k) Reporting Requirement

    Within 10 days after completing the inspections required by this
AD or within 10 days after March 9, 2020 (the effective date of this
AD), whichever occurs later, report to the FAA by email<EMAIL_ADDRESS>all information requested in the Carry-Thru Spar
Inspection Report Attachment to SEL-57-08 R1.

(l) Credit for Previous Actions

    (1) You may take credit for the visual inspection required by
paragraph (g) of this AD if you performed the visual inspection
before March 9, 2020 (the effective date of this AD) using Textron
Aviation Mandatory Single Engine Service Letter SEL-57-08, dated
November 1, 2019 (SEL-57-08); Textron Aviation Mandatory Single
Engine Service Letter SEL-57-06, dated June 24, 2019 (SEL-57-06); or
Textron Aviation Mandatory Single Engine Service Letter SEL-57-06,
Revision 1, dated November 19, 2019 (SEL-57-06 R1).
    (2) You may take credit for the eddy current inspection of the
lower cap kick area and all locations where corrosion was removed on
the carry-thru spar lower cap as specified in paragraph (h) of this
AD if you performed the eddy current inspection before March 9, 2020
(the effective date of this AD) using SEL-57-08, SEL-57-06, or SEL-
57-06 R1.
    (3) You may take credit for the corrosion protection required by
paragraph (i) of this AD if you performed those actions before March
9, 2020 (the effective date of this AD) using SEL-57-08.
    (4) If you can take credit for the visual and eddy current
inspections as specified in paragraphs (l)(1) and (2) of this AD but
you did not apply protective coating and CIC to the spar, you must
apply protective coating and CIC by following steps 9 and 10 of the
Accomplishment Instructions in Textron SEL-57-08 R1 within 12 months
after the date you completed the visual and eddy current
inspections.
    (5) To take credit for any previous action, you must have
provided a completed Carry-Thru Spar Inspection Report, an
attachment to Textron SEL-57-06, Textron SEL-57-06 R1, or Textron
SEL-57-08 to Textron Aviation Inc. before March 9, 2020 (the
effective date of this AD), or you must comply with paragraph (k) of
this AD within 10 days after March 9, 2020 (the effective date of
this AD).

(m) Special Flight Permit

    Special flight permits are prohibited.

(n) Paperwork Reduction Act Burden Statement

    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 currently 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 2 hours per response, including the
time for reviewing instructions, searching existing data sources,
gathering and maintaining the data needed, completing and reviewing
the collection of information. All responses to this collection

of information are mandatory. Send comments regarding this burden
estimate or any other aspect of this collection of information,
including suggestions for reducing this burden to: Information
Collection Clearance Officer, Federal Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX 76177-1524.

(o) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita 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 local Flight Standards District
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 (p) of this AD.
    (2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district 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 a Textron Aviation, Inc. Unit Member (UM) of
the Textron Organization Designation Authorization (ODA), that has
been authorized by the Manager, Wichita ACO Branch, to make those
findings. To be approved, the repair, modification deviation, or
alteration deviation must meet the certification basis of the
airplane, and the approval must specifically refer to this AD.

(p) Related Information

    For more information about this AD, contact Bobbie Kroetch,
Aerospace Engineer, Wichita ACO Branch, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone:<PHONE_NUMBER>; fax: (316) 946-
4107; email<EMAIL_ADDRESS>or aef9c7cdc6c7dacf83ede1fdeec8cfcf80c9c1d8.

(q) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
    (i) Textron Aviation Mandatory Service Letter SEL-57-08,
Revision 1, dated November 19, 2019.
    (ii) [Reserved]
    (3) For the service information identified in this AD, contact
Textron Aviation Inc., One Cessna Boulevard, Wichita, Kansas 67215,
phone:<PHONE_NUMBER>; email<EMAIL_ADDRESS>internet:
https://support.cessna.com.
    (4) You may view this service information at FAA, Policy and
Innovation Division, 901 Locust, Kansas City, Missouri 64106. For
information on the availability of this material at the FAA, call
(816) 329-4148.
    (5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email<EMAIL_ADDRESS>or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on February 13, 2020.
Lance T. Gant,
Aircraft Certification Service, Director, Compliance and Airworthiness
Division, AIR-700.
[FR Doc. 2020-03276 Filed 2-20-20; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 87, Number 229 (Wednesday, November 30, 2022)]
[Rules and Regulations]
[Pages 73448-73452]
[FR Doc No: 2022-26080]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0156; Project Identifier AD-2021-01474-T;
Amendment 39-22237; AD 2022-23-10]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2021-06-
03, which applied to all The Boeing Company Model 777F series
airplanes. AD 2021-06-03 required deactivating the potable water
system. This AD was prompted by a report of a water supply line that
detached at a certain joint located above an electronic equipment (EE)
cooling filter, leading to water intrusion into the forward EE bay.
This AD retains the actions required by AD 2021-06-03 and requires
installing a shroud to the water supply line in the forward cargo
compartment, and performing a leak test of the potable water system.
For certain airplanes, this AD also requires replacing tubes and hoses
from the water supply line and installing a shroud to the water return
line. The FAA is issuing this AD to address the unsafe condition on
these products.

DATES: This AD is effective January 4, 2023.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of January 4,
2023.
    The Director of the Federal Register approved the incorporation by
reference

of a certain other publication listed in this AD as of March 5, 2021
(86 FR 12809, March 5, 2021).

ADDRESSES:
    AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2022-0156; 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 final rule, any comments received, and other
information. The address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
    Material Incorporated by Reference:
     For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110 SK57, Seal Beach, CA
90740-5600; telephone<PHONE_NUMBER>; website 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
regulations.gov under Docket No. FAA-2022-0156.

Examining the AD Docket

    You may examine the AD docket at regulations.gov by searching for
and locating Docket No. FAA-2022-0156; 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 final rule, any comments
received, and other information. The address for Docket Operations is
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE,
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Courtney Tuck, Aerospace Engineer,
Cabin Safety and Environmental Systems Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-
231-3986; email: [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2021-06-03, Amendment 39-21469 (86 FR
12809, March 5, 2021) (AD 2021-06-03). AD 2021-06-03 applied to all The
Boeing Company Model 777F series airplanes. The NPRM published in the
Federal Register on March 25, 2022 (87 FR 17035). The NPRM was prompted
by the development of new actions that result in a need to modify AD
2021-06-03. AD 2021-06-03 was issued because of a report of a water
supply line that detached at a certain joint located above an EE
cooling filter, leading to water intrusion into the forward EE bay. In
the NPRM, the FAA proposed to continue to require deactivating the
potable water system. The NPRM also proposed to require installing a
shroud to the water supply line in the forward cargo compartment, and
performing a leak test of the potable water system. For certain
airplanes, the NPRM also proposed to require replacing tubes and hoses
from the water supply line and installing a shroud to the water return
line. The FAA is issuing this AD to address water entering the EE
cooling system via the cooling filter, which can affect multiple EE bay
racks and line replaceable units (LRUs), resulting in loss of
functionality or inaccurate output of critical electrical systems and
possible loss of control of the airplane.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from the Air Line Pilots Association,
International (ALPA), and an individual, who supported the NPRM without
change.
    The FAA received additional comments from three commenters,
including Boeing, FedEx, and All Nippon Airways. The following presents
the comments received on the NPRM and the FAA's response to each
comment.

Request To Change the Affected Airplanes for Certain Requirements

    FedEx and Boeing requested that the FAA change the affected
airplanes in paragraph (g)(2) of the proposed AD from ``L/Ns [line
numbers] 960 and subsequent.'' to ``L/N 960 through L/N 1689.'' FedEx
noted that the airplanes affected by paragraph (g)(2) of the proposed
AD should reflect the effectivity of Boeing Alert Requirements Bulletin
777-38A0048 RB, dated October 18, 2021. FedEx stated that if the
affected airplanes are not revised, then the final rule will require
Boeing Alert Requirements Bulletin 777-38A0048 RB, dated October 18,
2021, to be accomplished on aircraft to which it is not effective.
Boeing pointed out that the FAA has previously accepted this
alternative method of compliance (AMOC) to AD 2021-06-03 for L/N(s)
1692 and on, which have incorporated Type Design Change PRR 62701 Part
B.
    The FAA agrees with the request for the reasons stated above. The
FAA has changed paragraph (g)(2) of this AD from ``L/Ns 960 and
subsequent'' to ``L/N 960 through L/N 1689 inclusive.''

Request To Change the Compliance Time of an Approved AMOC

    FedEx requested that the FAA allow the AMOC to AD 2021-06-03 that
included Boeing Alert Service Bulletin 777-38A0047, dated March 30,
2021, to remain valid for 24 months from the published date of Boeing
Alert Service Bulletin 777-38A0047, dated March 30, 2021, in this AD.
FedEx reasoned that the AMOC to AD 2021-06-03 will expire earlier than
actions specified in Boeing Alert Requirements Bulletin 777-38A0048 RB,
dated October 18, 2021, can reasonably be accomplished. All Nippon
Airways requested that the AMOC to AD 2021-06-03 for Boeing Alert
Service Bulletin 777-38A0047, dated March 30, 2021, remain valid for 24
months from the effective date of this AD. All Nippon Airways contended
that if this AD does not allow Boeing Alert Service Bulletin 777-
38A0047, dated March 30, 2021, to remain valid, certain airplanes will
be grounded. All Nippon Airways also noted that if this AD continues to
allow Boeing Alert Service Bulletin 777-38A0047, dated March 30, 2021,
as an AMOC to this AD, but without extending the compliance time,
certain airplanes may be grounded due to the time needed to submit and
validate the AMOC Notice to its local authority.
    Alternatively, All Nippon Airways requested that this AD be issued
after the expiration of the interim action of the AMOC to AD 2021-06-03
that includes Boeing Alert Service Bulletin 777-38A0047, dated March
30, 2021. All Nippon Airways contended that if this AD does not allow
the AMOC that specifies Boeing Alert Service Bulletin 777-38A0047,
dated March 30, 2021, to remain valid, certain airplanes will be
grounded for the reasons described above.
    The FAA agrees with the intent behind the requests but cannot
change the existing AMOC to provide this relief to operators. However,
the FAA is considering issuing an amended AMOC that would extend the
compliance time of Boeing Alert Service Bulletin 777-38A0047, dated
March 30, 2021. If this amended AMOC is issued, then it may extend the
24-month compliance time to align with the compliance time of Boeing
Alert Requirements Bulletin

777-38A0048 RB, dated October 18, 2021. The FAA has added paragraph
(n)(4) of this AD to state that ``AMOCs approved for AD 2021-06-03 are
approved as AMOCs for the corresponding provisions of this AD.''
    Additionally, the FAA does not agree to delay the issuance of this
AD until after the expiration of the interim action of the AMOC to AD
2021-06-03 that includes Boeing Alert Service Bulletin 777-38A0047,
dated March 30, 2021. An AD is issued to correct an unsafe condition.
The unsafe condition will be corrected using Boeing Alert Requirements
Bulletin 777-38A0048 RB, dated October 18, 2021. The FAA has not
changed the AD in this regard.

Request To Reference the Optional Interim Action of AD 2021-06-03

    FedEx and Boeing requested that the FAA include a paragraph in this
AD that allows for an optional interim action in accordance with Boeing
Alert Service Bulletin 777-38A0047, dated March 30, 2021. FedEx and
Boeing maintained that this AD should reference Boeing Alert Service
Bulletin 777-38A0047, dated March 30, 2021, which was included in an
AMOC to AD 2021-06-03. FedEx noted that by including the interim action
of Boeing Alert Service Bulletin 777-38A0047, dated March 30, 2021, in
this final rule, the information will provide a more complete picture
of the entire timeline for future reference.
    The FAA agrees for the reasons provided. The FAA has previously
approved the AMOC to AD 2021-06-03 regarding the installation of a
temporary water line shroud in accordance with Boeing Alert Service
Bulletin 777-38A0047, dated March 30, 2021. As a result, the FAA has
added paragraph (l) of this AD, which allows the activation of the
potable water system provided that installation of a shroud around the
water supply line and gray water line, installation of a shroud around
the water return line, and post-installation inspections and applicable
corrective actions are done in accordance with Boeing Alert Service
Bulletin 777-38A0047, dated March 30, 2021; and provided that the
potable water system is deactivated within a certain compliance time.
The FAA has also redesignated subsequent paragraphs accordingly. The
FAA has also revised the Costs of Compliance section to include the
cost estimates for this optional action.

Conclusion

    The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Except for minor editorial changes, and any other changes
described previously, this AD is adopted as proposed in the NPRM. None
of the changes will increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin 777-38A0048 RB,
dated October 18, 2021. This service information specifies procedures
for replacing tubes and hoses from the water supply line and installing
a shroud to the water supply and return lines in the forward cargo
compartment and performing a leak test of the potable water system.
    The FAA also reviewed Boeing Alert Service Bulletin 777-38A0047,
dated March 30, 2021. This service information describes procedures for
installing a shroud around the water supply line and gray water line at
station (STA) 529 to STA 634 in the forward cargo compartment,
installing a shroud around the water return line at STA 550 to STA 620
in the forward cargo compartment, post-installation inspection
requirements (which, depending on the shroud location, include a
detailed inspection for any evidence of a water leak and a general
visual inspection to determine if the shroud is in serviceable
condition), and corrective actions (which include doing applicable
corrective actions and a leak test until no leak is detected, and doing
applicable corrective actions to put the shroud back to serviceable
condition).
    This AD also requires Boeing Multi Operator Message MOM-MOM-21-
0089-01B, dated February 26, 2021, which the Director of the Federal
Register approved for incorporation by reference as of March 5, 2021
(86 FR 12809, March 5, 2021).
    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 ADDRESSES.

Costs of Compliance

    The FAA estimates that this AD affects 58 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
              Action                        Labor cost                   Parts cost                 Cost per  product          Cost on U.S.  operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Deactivation of potable water       2 work-hours x $85 per      $0..........................  $170........................  $9,860.
 system (retained actions from AD    hour = $170.
 2021-06-03).
Replace tubes and hoses, and        Up to 12 work-hours x $85   Up to $1,850................  Up to $2,870................  Up to $166,460.
 install shroud (new action).        per hour = Up to $1,020.
Potable water system leak test      2 work-hours x $85 per      $0..........................  $170........................  $9,860.
 (new action).                       hour = $170.
--------------------------------------------------------------------------------------------------------------------------------------------------------

                                                          Estimated Costs for Optional Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
                Action                                Labor cost                        Parts cost                        Cost per product
--------------------------------------------------------------------------------------------------------------------------------------------------------
Install shrouds......................  Up to 2 work-hours x $85 per hour =      Up to $1,380..............  Up to $1,550.
                                        $170.
Post installation inspections........  Up to 3 work-hours x $85 per hour =      $0........................  Up to $255 per inspection cycle.
                                        $255 per inspection cycle.
On-condition actions.................  Up to 11 work-hours x $85 per hour =     $0........................  Up to $935.
                                        $935.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all of the costs of
this AD may be covered under warranty, thereby reducing the cost impact
on affected operators.

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

    This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2021-06-03, Amendment 39-21469
(86 FR 12809, March 5, 2021); and
0
b. Adding the following new AD:

2022-23-10 The Boeing Company: Amendment 39-22237; Docket No. FAA-
2022-0156; Project Identifier AD-2021-01474-T.

(a) Effective Date

    This airworthiness directive (AD) is effective January 4, 2023.

(b) Affected ADs

    This AD replaces AD 2021-06-03, Amendment 39-21469 (86 FR 12809,
March 5, 2021) (AD 2021-06-03).

(c) Applicability

    This AD applies to all The Boeing Company Model 777F series
airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 38, Water/waste.

(e) Unsafe Condition

    This AD was prompted by a report of a water supply line that
detached at a certain joint located above an electronic equipment
(EE) cooling filter, leading to water intrusion into the forward EE
bay. This AD was also prompted by the development of new actions to
address the unsafe condition. The FAA is issuing this AD to address
water entering the EE cooling system via the cooling filter, which
can affect multiple EE bay racks and line replaceable units (LRUs),
resulting in loss of functionality or inaccurate output of critical
electrical systems and possible loss of control of the airplane.

(f) Compliance

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

(g) Retained Deactivation of Potable Water System, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD
2021-06-03, with no changes. For the airplanes identified in
paragraphs (g)(1) and (2) of this AD: Within 5 days after March 5,
2021 (the effective date of AD 2021-06-03), deactivate the potable
water system, in accordance with Boeing Multi Operator Message MOM-
MOM-21-0089-01B, dated February 26, 2021 (Boeing MOM-MOM-21-0089-
01B).
    (1) Line numbers (L/Ns) 959 and earlier on which the actions
specified in Boeing Service Bulletin 777-38-0042 have been
accomplished.
    (2) L/Ns 960 through L/N 1689 inclusive.
    Note 1 to paragraph (g): Guidance on deactivating the potable
water system can be found in Boeing 777 Aircraft Maintenance Manual
(AMM) Task 38-10-00-040-801.

(h) Retained Installation Prohibition, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD
2021-06-03, with no changes. For airplanes not identified in
paragraph (g) of this AD: As of March 5, 2021 (the effective date of
AD 2021-06-03), accomplishment of the actions specified in Boeing
Service Bulletin 777-38-0042 is prohibited.

(i) Retained Reporting Provisions, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD
2021-06-03, with no changes. Although Boeing MOM-MOM-21-0089-01B
specifies to report inspection findings, this AD does not require
any report.

(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 777-38A0048 RB, dated October 18, 2021,
do all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
777-38A0048 RB, dated October 18, 2021.

    Note 1 to paragraph (j): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
777-38A0048, dated October 18, 2021, which is referred to in Boeing
Alert Requirements Bulletin 777-38A0048 RB, dated October 18, 2021.

(k) Exceptions to Service Information Specifications

    Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 777-
38A0048 RB, dated October 18, 2021, use the phrase ``the Original
Issue date of Requirements Bulletin 777-38A0048 RB,'' this AD
requires using ``the effective date of this AD.''

(l) Optional Action for Deactivation of Potable Water System

    Accomplishment of the installation of a shroud around the water
supply line and gray water line at station (STA) 529 to STA 634 in
the forward cargo compartment, and a shroud around the water return
line at STA 550 to STA 620 in the forward cargo compartment, as
specified in the Accomplishment Instructions of Boeing Alert Service
Bulletin 777-38A0047, dated March 30, 2021, terminates the potable
water system deactivation required by paragraph (g) of this AD,
provided the conditions specified in paragraphs (l)(1) and (2) of
this AD are met.
    (1) Repetitive inspections and applicable corrective actions are
done at the applicable times specified in Table 1 and Table 2 of
paragraph 1.E, ``Compliance,'' of Boeing Alert Service Bulletin 777-
38A0047, dated March 30, 2021, and in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
38A0047, dated March 30, 2021.
    (2) The potable water system is deactivated in accordance with
Boeing MOM-MOM-21-0089-01B, within 42 months after March 30, 2021
(the issue date of Boeing Alert Service Bulletin 777-38A0047, dated
March 30, 2021).

(m) Terminating Action for Deactivation of Potable Water System

    Accomplishment of the required actions specified in the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
777-38A0048 RB, dated October 18, 2021, terminates the potable water
system deactivation required by paragraph (g) of this AD.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle 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 (o) 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, Seattle
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 for AD 2021-06-03 are approved as AMOCs for
the corresponding provisions of this AD.

(o) Related Information

    For more information about this AD, contact Courtney Tuck,
Aerospace Engineer, Cabin Safety and Environmental Systems Section,
FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198;
phone and fax:<PHONE_NUMBER>; email: [email protected].

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on
January 4, 2023.
    (i) Boeing Alert Service Bulletin 777-38A0047, dated March 30,
2021.
    (ii) Boeing Alert Requirements Bulletin 777-38A0048 RB, dated
October 18, 2021.
    (4) The following service information was approved for IBR on
March 5, 2021 (86 FR 12809, March 5, 2021).
    (i) Boeing Multi Operator Message MOM-MOM-21-0089-01B, dated
February 26, 2021.
    (ii) [Reserved]
    (5) 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>; website myboeingfleet.com.
    (6) 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>.
    (7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on November 1, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-26080 Filed 11-29-22; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 81, Number 79 (Monday, April 25, 2016)]
[Notices]
[Pages 24092-24093]
[FR Doc No: 2016-09521]

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ENVIRONMENTAL PROTECTION AGENCY

[EPA-HQ-OECA-2012-0680; FRL-9945-27-OEI]

Information Collection Request Submitted to OMB for Review and
Approval; Comment Request; Emission Guidelines and Compliance Times for
Existing Municipal Solid Waste Landfills (Renewal)

AGENCY: Environmental Protection Agency (EPA).

ACTION: Notice.

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

SUMMARY: The Environmental Protection Agency has submitted an
information collection request (ICR), ``Emission Guidelines and
Compliance Times for Existing Municipal Solid Waste Landfills (40 CFR
part 60, subpart Cc and 40 CFR part 62, subpart GGG) (Renewal)'' (EPA
ICR No. 1893.07, OMB Control No. 2060-0430), to the Office of
Management and Budget (OMB) for review and approval in accordance with
the Paperwork Reduction Act (44 U.S.C. 3501 et seq.). This is a
proposed extension of the ICR, which is currently approved through
April 30, 2016. Public comments were previously requested via the
Federal Register (80 FR 32116) on June 5, 2015 during a 60-day comment
period. This notice allows for an additional 30 days for public
comments. A fuller description of the ICR is given below, including its
estimated burden and cost to the public. An Agency may neither conduct
nor sponsor, and a person is not required to respond to, a collection
of information unless it displays a currently valid OMB control number.

DATES: Additional comments may be submitted on or before May 25, 2016.

ADDRESSES: Submit your comments, referencing Docket ID Number EPA-HQ-
OECA-2012-0680, to: (1) EPA online using www.regulations.gov (our
preferred method), or by email to<EMAIL_ADDRESS>or by mail to:
EPA Docket Center, Environmental Protection Agency, Mail Code 28221T,
1200 Pennsylvania Ave. NW., Washington, DC 20460; and (2) OMB via email
to<EMAIL_ADDRESS>Address comments to OMB Desk Officer
for EPA.
    EPA's policy is that all comments received will be included in the
public docket without change including any personal information
provided, unless the comment includes profanity, threats, information
claimed to be Confidential Business Information (CBI) or other
information whose disclosure is restricted by statute.

FOR FURTHER INFORMATION CONTACT: Patrick Yellin, Monitoring,
Assistance, and Media Programs Division, Office of Compliance, Mail
Code 2227A, Environmental Protection Agency, 1200 Pennsylvania Ave.
NW., Washington, DC 20460; telephone number:<PHONE_NUMBER>; email
address<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION: Supporting documents which explain in detail
the information that the EPA will be collecting are available in the
public docket for this ICR. The docket can be viewed online at
www.regulations.gov or in person at the EPA Docket Center, EPA West,
Room 3334, 1301 Constitution Ave. NW., Washington, DC. The telephone
number for the Docket Center is<PHONE_NUMBER>. For additional
information about EPA's public docket, visit: http://www.epa.gov/dockets.

    Abstract: Owners and operators of affected facilities are required
to comply with reporting and record keeping requirements for the
general provisions of 40 CFR part 60, subpart A and 40 CFR part 62,
subpart A, as well as for the specific requirements at 40 CFR part 60,
subpart Cc and 40 CFR part 62, subpart GGG. This includes submitting an
initial notification reports, performance tests and periodic reports
and results, and maintaining records of the occurrence and duration of
any startup, shutdown, or malfunction in the operation of an affected
facility, or any period during which the monitoring system is
inoperative. These reports are used by EPA to determine compliance with
these standards.
    Form Numbers: None.
    Respondents/affected entities: Existing municipal solid waste
landfills.
    Respondent's obligation to respond: Mandatory (40 CFR part 60,
subpart Cc and 40 CFR part 62, subpart GGG).
    Estimated number of respondents: 465 (total).
    Frequency of response: Initially, occasionally and annually.
    Total estimated burden: 38,900 hours (per year). Burden is defined
at 5 CFR 1320.3(b).
    Total estimated cost: $3,080,000 (per year), which includes
$603,000 in annualized capital/startup and/or operation & maintenance
costs.
    Changes in the Estimates: There is a net decrease in the total
burden associated with privately and publicly owned landfills and State
and local agencies. This decrease in burden from the most recently
approved ICR is due to an adjustment to the estimated average number of
respondents. To account for landfill closures that have occurred since
the previous ICR was approved, this ICR applies a three percent per
year landfill closure rate to the previous ICR's estimated number of
respondents. This results in a decrease in the respondent labor hours,
labor costs, O&M costs, and number of responses. There is also a
corresponding decrease in the Agency burden and cost.

Courtney Kerwin,
Acting-Director, Collection Strategies Division.
[FR Doc. 2016-09521 Filed 4-22-16; 8:45 am]
 BILLING CODE 6560-50-P


[Federal Register: October 29, 2008 (Volume 73, Number 210)]
[Notices]
[Page 64396-64397]
[DOCID:fr29oc08-109]

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DEPARTMENT OF TRANSPORTATION

Pipeline and Hazardous Materials Safety Administration

Office of Hazardous Materials Safety; Notice of Delays in
Processing of Special Permits Applications

AGENCY: Pipeline and Hazardous Materials Safety Administration (PHMSA),
DOT.

ACTION: List of Applications Delayed more than 180 days.

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SUMMARY: In accordance with the requirements of 49 U.S.C. 5117(c),
PHMSA is publishing the following list of special permit applications
that have been in process for 180 days or more. The reason(s) for delay
and the expected completion date for action on each application is
provided in association with each identified application.

FOR FURTHER INFORMATION CONTACT: Delmer F. Billings, Director, Office
of Hazardous Materials Special Permits and Approvals, Pipeline and
Hazardous Materials Safety Administration, U.S. Department of
Transportation, East Building, PHH-30, 1200 New Jersey Avenue, SE.,
Washington, DC 20590-0001,<PHONE_NUMBER>.

Key to ``Reason for Delay''

    1. Awaiting additional information from applicant.
    2. Extensive public comment under review.
    3. Application is technically complex and is of significant impact
or precedent-setting and requires extensive analysis.
    4. Staff review delayed by other priority issues or volume of
special permit applications.

Meaning of Application Number Suffixes

    N--New application.
    M--Modification request.
    PM--Party to application with modification request.

    Issued in Washington, DC, on October 22, 2008.
Delmer F. Billings,
Director, Office of Hazardous Materials, Special Permits and Approvals.

                                         Modification to Special Permits
----------------------------------------------------------------------------------------------------------------
                                                                                Reason for  Estimated date
                Application No.                               Applicant                 delay      of completion
----------------------------------------------------------------------------------------------------------------
14167-M........................................  Trinityrail, Dallas, TX...........            4      10-31-2008
8723-M.........................................  Alaska Pacific Powder Company,                1      10-31-2008
                                                  Anchorage, AK.
135 83-M.......................................  Structural Composites Industries,             1      10-31-2008
                                                  Pomona, CA.
10950-M........................................  The Fertilizer Institute,                     1      10-31-2008
                                                  Washington, DC.
----------------------------------------------------------------------------------------------------------------

                                         New Special Permit Applications
----------------------------------------------------------------------------------------------------------------
                                                                                Reason for  Estimated date
                Application No.                               Applicant                 delay      of completion
----------------------------------------------------------------------------------------------------------------
14643-N........................................  World Airways, Inc., Peachtree                3      11-30-2008
                                                  City, GA.
14664-N........................................  Century Arms, Inc., Fairfax, VT...            4      10-31-2008
14689-N........................................  Trinity Industries, Inc., Dallas,          2, 3      11-30-2008
                                                  TX.
14668-N........................................  Lincoln Composites, Lincoln, NE...            1      02-28-2009
----------------------------------------------------------------------------------------------------------------

 [FR Doc. E8-25742 Filed 10-28-08; 8:45 am]

BILLING CODE 4910-60-M