[Federal Register Volume 81, Number 162 (Monday, August 22, 2016)]
[Proposed Rules]
[Pages 56540-56542]
[FR Doc No: 2016-19936]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8845; Directorate Identifier 2016-NM-094-AD]
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: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-
83), and DC-9-87 (MD-87) airplanes; and Model MD-88 airplanes. This
proposed AD was prompted by a report of fatigue cracking in a rear spar
lower cap of the horizontal stabilizer. This proposed AD would require
repetitive inspections for cracking of the rear spar lower caps of the
horizontal stabilizer, post-modification and post-repair inspections,
and corrective actions if necessary. This proposed AD also provides an
optional terminating fatigue life enhancement modification. We are
proposing this AD to detect and correct fatigue cracking in the rear
spar lower caps of the horizontal stabilizer, which, paired with
cracking in adjacent areas, could adversely affect the structural
integrity of the airplane.

DATES: We must receive comments on this proposed AD by October 6, 2016.

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 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: 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: Data & Services Management, 3855
Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone
206-544-5000, extension 2; fax<PHONE_NUMBER>; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call<PHONE_NUMBER>. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8845.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
8845; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone:<PHONE_NUMBER>) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Haytham Alaidy, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5224; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2016-8845;
Directorate Identifier 2016-NM-094-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 have received a report of a 0.513-inch crack in a rear spar
lower cap of the horizontal stabilizer. The Model MD-88 airplane had
accumulated 61,741 total flight hours and 45,985 total landing cycles.
Lab analysis on the area adjacent to the crack shows that the crack was
caused by fatigue. Such fatigue cracking, paired with cracking in
adjacent areas, could adversely affect the structural integrity of the
airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin MD80-55A072, dated April
8, 2016. The service information describes procedures for doing
inspections for cracking of the rear spar lower caps of the horizontal
stabilizer, post-modification and post-repair inspections, and repairs.
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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the Service
Information.'' For information on the procedures and compliance times,
see this service information at http://www.regulations.gov by searching
for and locating Docket No. FAA-2016-8845.
    The phrase ``corrective actions'' is used in this proposed AD.
Corrective actions correct or address any condition found. Corrective
actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin MD80-55A072, dated April 8, 2016,
specifies to contact the manufacturer for certain instructions, but
this proposed AD would require accomplishment of repair methods,
modification deviations, and alteration deviations in one of the
following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 395 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost on U.S.
             Action                     Labor cost           Parts cost      Cost per product      operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  3 work-hours x $85 per                $0   $255 per           $100,725 per
                                  hour = $255 per                            inspection cycle.  inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------

                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                Action                           Labor cost              Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Modification.........................  59 work-hours x $85 per hour            $1,267   $6,282 per stabilizer.
                                        = $ 5,015 per stabilizer.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacement
that would be required based on the results of the proposed inspection.
We have no way of determining the number of aircraft that might need
this replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                           Labor cost              Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement..........................  368 work-hours x $85 per hour          $31,408   $62,688 per stabilizer.
                                        = $31,280 per stabilizer.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions that require repair using a
method specified in paragraph (k) of 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.
    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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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 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 adding the following new airworthiness
directive (AD):

The Boeing Company: Docket No. FAA-2016-8845; Directorate Identifier
2016-NM-094-AD.

(a) Comments Due Date

    We must receive comments by October 6, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model DC-9-81 (MD-81),
DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes; and
Model MD-88 airplanes; certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by a report of fatigue cracking in a Model
MD-88 rear spar lower cap of the horizontal stabilizer. We are
issuing this AD to detect and correct fatigue cracking in the rear
spar lower caps of the horizontal stabilizer, which, paired with
cracking in adjacent areas, could adversely affect the structural
integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections and Corrective Actions

    Except as specified in paragraph (i)(1) of this AD, at the
applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin MD80-55A072, dated April 08, 2016: Do
an open hole high frequency eddy current inspection (HFEC) or
surface HFEC inspection for cracking of the rear spar lower caps of
the horizontal stabilizer, and do all applicable corrective actions;
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin MD80-55A072, dated April 8, 2016, except as
specified in paragraph (i)(2) of this AD. Do all applicable
corrective actions before further flight. Repeat the inspection
thereafter at the applicable interval specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin MD80-55A072, dated
April 8, 2016, until accomplishment of the actions provided by
paragraph (h) of this AD.

(h) Optional Terminating Action

    Accomplishment of the fatigue life enhancement modification in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin MD80-55A072, dated April 8, 2016, terminates the
repetitive inspections required by paragraph (g) of this AD.

(i) Service Information Exceptions

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin MD80-55A072, dated April 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 the effective date of this AD.
    (2) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin MD80-55A072, dated April
8, 2016, specifies to contact Boeing for appropriate action: Before
further flight, repair the cracking using a method approved in
accordance with the procedures specified in paragraph (k) of this
AD.

(j) Post-Modification and Post-Repair Actions

    For airplanes on which any modification or repair specified in
(g) or (h) of this AD has been done: At the applicable time and
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin MD80-55A072, dated April 8, 2016, do all
applicable post-modification and post-repair inspections and all
applicable corrective actions; in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin MD80-55A072, dated
April 8, 2016; except as specified in paragraph (i)(2) of this AD.
All applicable corrective actions must be done before further
flight.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. 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 ACO, send it to the
attention of the person identified in paragraph (l)(1) of this AD.
Information may be emailed to<EMAIL_ADDRESS>    (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 the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Los Angeles ACO, 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) Except as required by paragraph (i)(2) of this AD: For
service information that contains steps that are labeled as Required
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and
(k)(4)(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 sub-step is labeled ``RC Exempt,'' then
the RC requirement is removed from that step or sub-step. 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.

(l) Related Information

    (1) For more information about this AD, contact Haytham Alaidy,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office (ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712-4137; phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>;
email<EMAIL_ADDRESS>    (2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001;
telephone<PHONE_NUMBER>, extension 2; fax<PHONE_NUMBER>; Internet
https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call<PHONE_NUMBER>.

    Issued in Renton, Washington, on August 11, 2016.
Paul R. Bernado,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-19936 Filed 8-19-16; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 76, Number 44 (Monday, March 7, 2011)]
[Notices]
[Page 12408]
[FR Doc No: 2011-5093]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

Notice of Intent to Rule on Request To Release Airport Property
at Ellington Field Airport, Houston, Texas

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of request to release airport property.

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SUMMARY: The FAA proposes to rule and invite public comment on the
release of land at Ellington Field Airport under the provisions of
Section 125 of the Wendell H. Ford Aviation Investment Reform Act for
the 21st Century (AIR 21).

DATES: Comments must be received on or before April 4, 2011.

ADDRESSES: Comments on this application may be mailed or delivered to
the FAA at the following address:

Mr. Mike Nicely, Manager, Federal Aviation Administration, Southwest
Region, Airports Division, Texas Airports Development Office, ASW-650,
Fort Worth, Texas 76137.

    In addition, one copy of any comments submitted to the FAA must be
mailed or delivered to Mr. Mario C. Diaz, Aviation Director, at the
following address:

Mr. Mario C. Diaz, Aviation Director, Houston Airport System, 16930
John F. Kennedy Blvd., Houston, Texas 77032.

FOR FURTHER INFORMATION CONTACT: Mr. Ben Guttery, Senior Program
Manager, Federal Aviation Administration, Texas Airports Development
Office, ASW-652, 2601 Meacham Boulevard, Fort Worth, Texas 76137-0650,
Telephone:<PHONE_NUMBER>, E-mail<EMAIL_ADDRESS>Fax: (817) 222-
5989.
    The request to release property may be reviewed in person at this
same location.

SUPPLEMENTARY INFORMATION: The FAA invites public comment on the
request to release property at the Ellington Field Airport under the
provisions of the AIR 21.
    On February 7, 2011, the FAA determined that the request to release
property at Ellington Field Airport, submitted by the Airport, met the
procedural requirements of the Federal Aviation Regulations, Part 155.
The FAA may approve the request, in whole or in part, no later than
April 4, 2011.
    The following is a brief overview of the request:
    Ellington Field Airport requests the release of 16.019 acres of
non-aeronautical airport property. The land was acquired by the City of
Houston via an Indenture dated July 1, 1984, and Deed without Warranty
and Bill of Sale dated August 21, 1984. The funds generated by the
release will be used to improve the Ellington Field Airport.
    Any person may inspect the request in person at the FAA office
listed above under FOR FURTHER INFORMATION CONTACT.
    In addition, any person may, upon request, inspect the application,
notice and other documents relevant to the application in person at the
FAA Office listed above or the Houston Airport System Offices at
Ellington Field Airport.

    Issued in Fort Worth, Texas on February 25, 2011.
Kelvin Solco,
Manager, Airports Division.
[FR Doc. 2011-5093 Filed 3-4-11; 8:45 am]
BILLING CODE P


[Federal Register Volume 87, Number 39 (Monday, February 28, 2022)]
[Rules and Regulations]
[Pages 10958-10964]
[FR Doc No: 2022-04146]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0345; Product Identifier 2019-NM-154-AD; Amendment
39-21951; AD 2022-04-09]
RIN 2120-AA64

Airworthiness Directives; AVOX System Inc. (Formerly Scott
Aviation) Oxygen Cylinder and Valve Assemblies and Oxygen Valve
Assemblies

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain AVOX System Inc. (formerly Scott Aviation) oxygen cylinder and
valve assemblies, and oxygen valve assemblies, installed on but not
limited to various transport airplanes. This AD was prompted by reports
of cylinder and valve assemblies having oxygen leakage from the valve
assembly vent hole, caused by the absence of a guide that maintains
appropriate spacing between certain parts. This AD requires an
inspection of the oxygen valve assemblies, and oxygen cylinder and
valve assemblies, to determine the serial number of the valve,
cylinder, and entire assembly. For assemblies and parts with certain
serial numbers, this AD requires a detailed inspection for correct
spacing of the gap between the bottom of the packing retainer and top
of the valve body on the assemblies, and replacement of assemblies
having unacceptable gaps. The FAA is issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective April 4, 2022.
    The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 4,
2022.

ADDRESSES: For service information identified in this final rule,
contact AVOX Systems Inc., 225 Erie Street, Lancaster, NY 14086;
telephone<PHONE_NUMBER>; internet https://www.safranaerosystems.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-2020-0345.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0345; 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: Elizabeth Dowling, Aerospace Engineer,
Mechanical Systems and Administrative Services Section, FAA, New York
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone<PHONE_NUMBER>; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain AVOX System
Inc. (formerly Scott Aviation) oxygen cylinder and valve assemblies,
and oxygen valve assemblies, installed on but not limited to various
transport airplanes. The NPRM published in the Federal Register on May
1, 2020 (85 FR 25353). The NPRM was prompted by reports of cylinder and
valve assemblies having oxygen leakage from the valve assembly vent
hole, caused by the absence of a guide that maintains appropriate
spacing between certain parts. In the NPRM, the FAA proposed to require
an inspection of the oxygen valve assemblies, and oxygen cylinder and
valve assemblies, to determine the serial number of the valve,
cylinder, and entire assembly. For assemblies and parts with certain
serial numbers, the NPRM proposed to require a detailed inspection for
correct spacing of the gap between the bottom of the packing retainer
and top of the valve body on the assemblies, and replacement of
assemblies having unacceptable gaps (removing affected assemblies and
installing serviceable assemblies). The NPRM also proposed to require
reporting and returning of affected parts to the manufacturer. The FAA
is issuing this AD to address oxygen leakage from the cylinder, which
could result in decreased or insufficient oxygen supply during a
depressurization event; and heating or flow friction, which could cause
an ignition event in the valve assembly.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from one commenter, Air Line Pilots
Association, International (ALPA), who supported the NPRM without
change.
    The FAA received additional comments from five commenters,
including American Airlines (AAL), Delta Air Lines (DAL), FedEx Express
(FedEx), United Airlines (UAL), and an individual. The following
presents the comments received on the NPRM and the FAA's response to
each comment.

Request To Revise Applicability

    AAL and UAL suggested revising the applicability statement to
include more aircraft manufacturers and models. AAL suggested adding
all airplane models that affected assemblies could be installed on, in
particular, Boeing Model 737-NG (Next Generation models are 737-600, -
700, -700C, -800, -900, and -900ER series), 737-MAX, 777-200, and 777-
300 series airplanes. UAL also suggested adding Model 737-NG airplanes.
AAL stated that the applicability statement as proposed in the NPRM
could mislead operators into believing that the AD would apply only to
the airplanes identified in paragraphs (c)(1) through (12) of the AD.
UAL believed the suggested change will be beneficial and assist
operators in determining if their fleets are affected.

    The FAA disagrees with the commenters' request. The FAA does not
have a comprehensive list of all possible affected aircraft. To address
the incomplete list, paragraph (c) of this AD identifies specific
airplane models in paragraph (c) of this AD, but also notes that the
assemblies are ``not limited to.'' The FAA has not changed the AD in
this regard.

Request To Revise Compliance Time for Parts

    AAL stated that the 60-day compliance time should apply only to
valve assemblies that are installed on the aircraft and not ones in
stock. AAL believes the unsafe condition only exists when an assembly
is installed on an airplane, and for those assemblies that are not
installed on an airplane, the proposed requirements in paragraph (k) of
the proposed AD would ensure that the unsafe condition is addressed
before that assembly is installed on an aircraft.
    The FAA disagrees with the request to revise the compliance time.
The FAA agrees that an affected spare part that is uninstalled and
stored off an aircraft would not cause an unsafe condition on an
aircraft. The 60-day compliance time applies to parts already installed
on an aircraft, and paragraph (k) requires that action to be done on
affected spare parts before installation, which could result in a spare
part being inspected before the 60-day compliance time. In developing
the compliance time for this AD, the FAA considered the urgency
associated with the subject unsafe condition and the availability of
required parts. The FAA determined that the 60-day compliance time for
parts already installed on an aircraft is appropriate for accomplishing
the actions required by this AD while maintaining an adequate level of
safety. The FAA has not changed this AD in this regard.

Request To Remove Inspection for Serial Numbers or Include Only Valve
P/Ns

    AAL requested that the inspection to verify the serial number of
the oxygen cylinder and entire assembly not be required. DAL requested
that paragraphs (c), (h), (i), and (k) of the proposed AD be revised to
remove reference to cylinder part numbers (P/Ns) and apply only to
valve assembly P/Ns. AAL stated that it reviewed the service
information and it seems that the defective part is only the valve
assembly or ``hand valve.'' DAL also reasoned that the unsafe condition
applies only to the valve assembly and not the cylinder. AAL then
reasoned that the inspection to verify the serial number should apply
only to the valve assembly or ``hand valve.'' AAL also stated that
paragraph (i) of the proposed AD also seems to require the actions of
paragraph (h)(1) through (3) of the proposed AD if a serial number of a
cylinder was affected and a valve assembly not affected, even though it
seems that it should not require those actions.
    The FAA disagrees with the request. The parts of the oxygen
cylinder and valve assemblies are interrelated, and valves from matched
sets could have fit-up issues between parts or be mixed up or swapped
during maintenance operations. The serial number inspection as proposed
would address this interchangeability. The valve and cylinder that are
part of those assemblies must also be inspected to address the unsafe
condition, not just the assemblies themselves. Therefore, the FAA
specifies to inspect the oxygen valve assemblies, and oxygen cylinder
and valve assemblies, to determine the serial number of the valve,
cylinder, and entire assembly. The FAA has not changed this AD in this
regard.

Request To Clarify Which Components Need To Be Identified

    UAL requested a change to the wording of which components need the
serial number inspection. UAL stated that the statement in paragraph
(h) of the proposed AD can be misconstrued as requiring that each of
the three components (valve, cylinder, and entire assembly) be
inspected individually for suspect serial numbers. UAL inferred that
the intention is to inspect for the serial number of the entire
cylinder and valve assembly, and not the individual components. UAL
also stated that, for new oxygen cylinder assemblies from AVOX, there
are individual placards that itemize the P/N and serial number for each
component, and that for some cylinder assemblies, the serialization of
the entire cylinder and valve assembly is nearly identical in format to
the serialization of sub-component valve assemblies, which could lead
to inaccurate reporting of results. The FAA infers that UAL suggested
that the relevant numbers on the placards could be confused with other
numbers.
    The FAA disagrees. Each part and assembly stated in paragraph (h)
of this AD are interrelated and must be inspected. The valve and
cylinder components that are part of those assemblies must also be
inspected for serial numbers, not just the assemblies themselves. If
the serial number markings are unclear or missing, the service
information contains information on identifying the parts and part
assemblies. The FAA has not changed this AD in this regard.

Request To Revise Conditions for Gap Inspection and Related Actions

    AAL and DAL requested changes to address concerns about what
actions are required if a part is missing a blue dot. DAL stated that
it seems best to prohibit all affected serial numbers to avoid a case
where an inspected and marked part is installed, but the blue dot
fades. AAL pointed to paragraph (i) of the proposed AD that would
clarify that only the affected serial numbers of the valve assembly
would need additional work, and, for valve assemblies marked with a
blue dot, a detailed inspection for correct spacing of the gap between
the bottom of the packing retainer and top of the valve body would not
be required. AAL stated that, as written, the proposed AD seems to
suggest that an inspection of the gap would be required regardless of
the presence of a blue dot.
    The FAA disagrees with the request. The service information
specifies that if there is a doubt on the condition of a part, such as
missing serial numbers or a blue dot not definitively identified, then
the follow-on inspections are required to ensure that no discrepant or
affected part is missed. Paragraph (k) of this AD prohibits
installation of assemblies with affected serial numbers unless the
actions of paragraph (i) of this AD are accomplished. The FAA has not
changed this AD in this regard.

Request To Remove Inspection Report Requirement

    DAL requested that the compliance times for the inspection report
be removed from paragraph (j)(1) of the proposed NPRM, and if not, the
inspection report itself be removed. AAL requested removing the
proposed requirement to submit an inspection report after accomplishing
the requirements (i.e., gap inspection) of paragraph (i) of the
proposed AD. FedEx stated reporting should not be required for units
that pass the inspection, and that sending units that failed the
inspection to the vendor should be sufficient for reporting those
failures. FedEx noted that any reporting requirements should consider
the difficulties in reporting findings in a short period of time and
noted that the inspector might not have access to the internet, email,
and a device capable of printing and scanning. FedEx opined that its
proposal would maintain accurate reporting and accommodate the
realities of a global workplace. AAL and DAL stated that the reporting
seems unnecessary and does not contribute to any additional level of
safety. AAL

added that the NPRM would give operators the responsibility of ensuring
that any affected part is returned to the manufacturer, and asserted
that an equivalent level of safety would be maintained even if the
reporting is not accomplished. DAL reasoned that if a cylinder valve
assembly is unacceptable, it would be in the operator's best interest
to report that finding to AVOX anyways so that it can receive a
replacement assembly.
    The FAA disagrees. In this case, the inspection results need to be
reported to assist in tracking affected parts that are in circulation.
In addition, reporting all findings gives assurance that an inspection
was performed on an assembly with a given serial number. The FAA has
not changed this AD in this regard.

Request To Remove Compliance Time for Returning Parts

    AAL, DAL, and UAL requested revising paragraph (j)(2) of the
proposed AD to remove a compliance time for returning discrepant parts
to the manufacturer. AAL stated that a compliance time would not
contribute to the level of safety. AAL also stated that all discrepant
assemblies would be returned in a timely manner that is sufficient to
the operator. DAL stated that it would be an unnecessary burden on
operators to wait for AVOX's response before sending an unacceptable or
discrepant part back within the compliance time in exchange for a free-
of-charge replacement. DAL also stated that it would also be in the
operator's best interest to send in the assembly so that it can qualify
for a free-of-charge replacement if AVOX determines the part is
unacceptable or discrepant. UAL stated it also believes the instruction
to contact AVOX for shipping instructions could impede compliance with
the 30-day limit to ship discrepant parts back to AVOX. UAL also stated
that it wants to know how, for accurate AD-compliance reporting, it
would be determined that a part is being shipped back as a result of
this finding from AD-required inspections, or as a result of other,
normal repair order processes.
    The FAA agrees to clarify. Paragraph (j)(2) of this AD requires
returning the assembly to the manufacturer in accordance with paragraph
3.D.(2) or 3.D.(3), as applicable, of the applicable service
information. However, the service information does not include
instructions to wait for a response from AVOX before returning the
part. In addition, the FAA has revised paragraph (j)(2) of this AD to
clarify that contacting AVOX for shipping instructions in not required.
AVOX is tracking parts that are returned to it during accomplishment of
the AD for data collection or analysis of manufacturing issues, and
AVOX is also re-conditioning parts where possible. The FAA determined
that having a 30-day compliance time for returning the part after an
inspection finding is appropriate for this AD. However, under the
provisions of paragraph (m) of this AD, an operator may request an
approval of an alternative method of compliance (AMOC). The FAA has not
changed this AD in this regard.

Request To Allow Later Revisions of Service Information

    AAL requested that all the references to the AVOX service
information be revised to allow use of subsequent revisions. AAL
reasoned that this revision would reduce the number of AMOC requests
each time a referenced service bulletin is revised.
    The FAA disagrees. In an AD, the FAA may not refer to any document
that does not yet exist. In general terms, the FAA is required by the
Office of the Federal Register (OFR) regulations for approval of
materials incorporated by reference, as specified in 1 CFR 51.1(f), to
either publish the service document contents as part of the actual AD
language; or submit the service document to the OFR for approval as
referenced material, in which case the FAA may only refer to such
material in the text of an AD. The AD may refer to the service document
only if the OFR approved it for incorporation by reference. See 1 CFR
part 51. The FAA disagrees with revising the AD to include specific
airplane models based on the corresponding service information because
the agency does not have a comprehensive list of the applicable
aircraft to which specific AVOX service information could apply. The
FAA has not changed this AD in this regard.

Request To Clarify AD Applicability With Reference to Service
Information

    A commenter requested clarifying paragraph (c) of the proposed AD
by including reference to the service information that was identified
in paragraph (h) of the proposed AD. The commenter suggested revising
the paragraph so that the applicability would include information on
the service information definition of the affected units. AAL also
requested adding the airplane configuration information in the text of
the AD to add further clarification to operators and release the
technical data in a more organized fashion.
    The FAA disagrees. The definition of the affected units does not
need to be moved to paragraph (c) of the AD. The effectivity of the
service information is limited to specific airplane models, but the
applicability of this AD applies to all aircraft. Because the affected
parts could be installed on additional aircraft models, the FAA has
determined that the affected parts could later be installed on aircraft
that were initially delivered with acceptable parts, thereby subjecting
those aircraft to the unsafe condition. The FAA has not changed this AD
in this regard.

Request To Revise Compliance Time for Parts Identification

    DAL and UAL requested revising the compliance time proposed in
paragraph (h) of the proposed NPRM. DAL and UAL stated that since many
operators have parked their aircraft or severely reduced usage of
aircraft, an extension of the compliance time (either with additional
calendar days or adding an option for flight hours and flight cycles),
would allow operators additional time for compliance. UAL also stated
that the supply chain could be affected due to potential increased
shipping time and workforce reductions.
    The FAA disagrees with the request to extend the compliance time.
The FAA acknowledges the effects that the pandemic response might have
on operators' fleet use, supply chain, and maintenance personnel. In
developing an appropriate compliance time for this action, the FAA
considered the degree of urgency associated with addressing the subject
unsafe condition, the manufacturer's recommendation for an appropriate
compliance time, and the practical aspect of accomplishing the required
inspection within a period of time that corresponds to the normal
scheduled maintenance for most affected operators. In addition, the FAA
notes that some aircraft may have been in service during the pandemic
and must comply within the required compliance time. Operators do have
the option to inspect the airplane before the first flight following
storage if the airplane is in storage for more than 27 months. However,
under the provisions of paragraph (m) of this AD, the FAA will consider
requests for an extension of the compliance time if sufficient data are
submitted to substantiate that the new compliance time would provide an
acceptable level of safety. The FAA has not changed this AD in this
regard.

Request To Allow Use of Alternatives for Parts Marking

    FedEx requested that the specification to use oil-based blue ink
markers be

modified to allow alternative methods and colors such as black
indelible ink. FedEx stated that oil-based blue paint markers are not
readily available or kept in stock regularly. FedEx suggested that a
list of part numbers for approved, aircraft grade, oil-based paint be
provided.
    The FAA disagrees. While the FAA realizes this is a limitation,
there must be one standard to help avoid confusion. The procedures
required by this AD specify actions based on the presence or absence of
a blue dot in a specific location. The FAA has not seen any
difficulties in obtaining the paint markers. However, under the
provisions of paragraph (m) of this AD, any person may request an
approval of an AMOC. The FAA has not revised this AD in this regard.

Request To Allow Alternative Means of Measuring Gaps

    FedEx requested that the proposed AD be revised to allow use of
feeler gauges, calipers, and other means of measuring the gap in
imperial units of measure. FedEx stated that the service information
specifies use of pin gauges that are made for metric units of measure,
and that acquiring those metric pin gauges is an extra expense and
logistical complication. FedEx recommended adding a tolerance to the
gap measurement and specifying a fractional imperial measure (\3/32\-
inch) that is close to the metric unit specified. FedEx suggested that
if a tolerance or other measurement is not added, then a manufacturer
part number (MPN) for a specific tool or supplier should be provided.
    The FAA disagrees. Using other means of measuring could introduce
or increase variables that could affect the accuracy of the
measurement. The FAA understands that not everyone has the same
resources, tools, or supplies; however, the FAA also understands that
this means of measurement is easily accessible. Under the provisions of
paragraph (m) of this AD, operators may request approval of an AMOC if
sufficient data are submitted to substantiate that the tolerance would
provide an acceptable level of safety. The FAA has not changed this AD
in this regard.

Request To Revise Procedure for Shipping an Assembly

    FedEx requested that the proposed AD be revised to allow operators
to use their own procedures for shipping dangerous goods such as
unopened cylinder valve assemblies (CVAs) instead of the procedure
specified in the service information. FedEx explained that it has
established and accepted procedures for shipping dangerous goods, and
that the disposition of an unopened CVA would be done by a department
separate from the one doing the inspection. FedEx stated that following
the procedures in the service information would require additional
coordination time, and that the wording of the procedures would not
function properly with its AD compliance mechanisms.
    The FAA agrees to clarify. The design approval holder (DAH) of the
affected valve assemblies has specified a method for shipping, or
returning, an unopened CVA that has been found to be unacceptable or
discrepant, specifically a shipping method that is compliant with DOT
standard HM-224B. If FedEx has procedures that are compliant with DOT
standard HM-224B, then those procedures are acceptable for compliance
with this AD. For procedures that are not compliant with DOT standard
HM-224B, under the provisions of paragraph (m) of this AD, the FAA will
consider requests for an AMOC. The FAA has not changed this AD in this
regard.

Request for Clarification on Applicability of AD

    FedEx requested clarification on whether the proposed AD is written
``against'' the MPN or the serial numbers within that MPN. FedEx
explained the effects on the operator's workload and also on the
operational impact of a unit's overhaul cycle in conjunction with a 60-
day compliance time and the scope of the applicability. FedEx added
that a 180-day compliance time would be more reasonable.
    The FAA agrees to clarify. The applicability of this AD is written
against the MPN and specific serial numbers, in addition to manufacture
dates of the assemblies. The FAA disagrees to revise the compliance
time because the FAA has determined that requirement based on a risk
calculation. The FAA has not changed this AD in that regard.

Request To Clarify Requirement if Component Number(s) Cannot Be
Determined

    UAL requested clarification on what actions are required in the
event the P/N or serial number information cannot be determined. UAL
stated that as a result of in-service activity, that information might
be illegible, unintentionally obliterated, or missing from the placard.
UAL added that under its normal practices, whenever a part or serial
number cannot be determined, the part is considered suspect, made
unserviceable, and removed from service. UAL stated that, when the P/N
of the entire cylinder and valve assembly can be determined but not the
serial number, and the date of manufacture is between January and
November 2018, it wants to still be able to establish conformity by
inspecting for the presence of the blue dot and accomplish the
applicable service information instruction if the blue dot is missing.
UAL also stated that depending on the FAA's response to this request,
it may apply for an AMOC.
    The FAA agrees to clarify. The service information states to
inspect for the manufacturing date, serial number, and the presence of
a blue dot. The service information then states that if there is doubt
or a determination cannot be made (such as the numbers or dot is not
clearly identified), to proceed with the follow-on inspection for
proper gap spacing (this follow-on inspection is required by paragraph
(i) of this AD). The FAA has not changed this AD in this regard.

Request for Clarification on Compliance Time and Method for Inspection
Report

    UAL requested clarification on how a 30-day requirement for the
inspection report was determined, and if a ``comprehensive'' report is
acceptable. UAL stated that it understands the need for the information
gathered from the reports; however, it does not understand why or how a
30-day compliance time was established. UAL also stated that it assumed
that reporting of the results should be done as a single, comprehensive
report and not piece-wise (individually for each assembly or aircraft),
and that the report does not need to be an exact copy of the report
form in the service information.
    The FAA agrees to clarify. The FAA determined that the 30-day
compliance time is appropriate for this AD. Also, the manufacturer is
collecting information for analysis of manufacturing issues. The format
of the report may be done as UAL assumed, as long as all documents are
labeled correctly. However, under the provisions of paragraph (m) of
this AD, an operator may request an approval of an AMOC. The FAA has
not changed this AD in this regard.

Request To Provide Clarification on Reporting Form

    UAL requested clarification on the definition of ``manufacture
date'' in a recording column of a report form in the service
information. UAL stated that it is implied that ``manufacture date'' in
that column is the manufacture date of

the entire cylinder and valve assembly and not of the valve assembly.
    The FAA agrees to clarify. The ``manufacturer date'' is not limited
to the date of the entire cylinder and valve assembly, but is the
manufacture date of each part or assembly that might be recorded in the
inspection report, such as the assemblies listed in Appendix 1 of the
service information. The FAA has not changed this AD in this regard.

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, 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 AVOX Systems Inc. Alert Service Bulletins
10015804-35-01, Revision 02, dated October 16, 2019; 10015804-35-02,
Revision 2, dated October 31, 2019; and 10015804-35-03, Revision 02,
dated October 15, 2019. This service information describes procedures
for an inspection to determine the serial numbers of the oxygen
cylinder and valve assemblies, and the oxygen valve assemblies, a
detailed inspection for correct spacing of the gap between the bottom
of the packing retainer and top of the valve body on the assemblies,
parts marking, inspection report, and return of parts to the
manufacturer. These documents are distinct since they apply to
different assembly part numbers. 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 up to 3,034 oxygen cylinder
and valve assemblies, and oxygen valve assemblies, installed on various
transport category 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
----------------------------------------------------------------------------------------------------------------
Serial number inspection.........  1 work-hour x $85    None....................             $85        $257,890
                                    per hour = $85.
Reporting........................  1 work-hour x $85    0.......................              85         257,890
                                    per hour = $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary follow-on
actions that would be required based on the results of the inspection.
The FAA has no way of determining the number of aircraft that might
need these actions:

                                              On-Condition Costs *
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                Action                          Labor cost                   Parts cost               product
----------------------------------------------------------------------------------------------------------------
Detailed inspection...................  1 work-hour x $85 per      None.........................             $85
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------
* The FAA has received no definitive data on the cost of on-condition replacements.

    According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators. The FAA does not control warranty coverage for
affected operators. As a result, the FAA has included all known costs
in the cost estimate.

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 take
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, and 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 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 adding the following new airworthiness
directive:

2022-04-09 AVOX Systems Inc. (formerly Scott Aviation): Amendment
39-21951; Docket No. FAA-2020-0345; Product Identifier 2019-NM-154-
AD.

(a) Effective Date

    This airworthiness directive (AD) is effective April 4, 2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to AVOX Systems Inc. (formerly Scott Aviation)
oxygen cylinder and valve assemblies having part number (P/N)
89794077, 89794015, 891511-14, 806835-01, 807982-01, or 808433-01;
and oxygen valve assemblies (body and gage assemblies) having P/N
807206-01. These assemblies might be installed on, but not limited
to, the aircraft identified in paragraphs (c)(1) through (12) of
this AD, certificated in any category.
    (1) Airbus SAS Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C,
B4-103, and B4-203 airplanes.
    (2) Airbus SAS Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes.
    (3) Airbus SAS Model A310-203, -204, -221, -222, -304, -322, -
324, and -325 airplanes.
    (4) Airbus SAS Model A318-111, -112, -121, and -122 airplanes.
    (5) Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -
132, -133, and -151N airplanes.
    (6) Airbus SAS Model A320-211, -212, -214, -216, -231, -232, -
233, -251N, -252N, -253N, -271N, -272N, and -273N airplanes.
    (7) Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -
231, -232, -251N, -252N, -253N, -271N, -272N, -251NX, -252NX, -
253NX, -271NX, and -272NX airplanes.
    (8) Airbus SAS Model A330-201, -202, -203, -223, -243, -301, -
302, -303, -321, -322, -323, -341, -342, -343, and -941 airplanes.
    (9) Airbus Model A340-211, -212, -213, -311, -312, -313, -541,
and -642 airplanes.
    (10) ATR--GIE Avions de Transport R[eacute]gional Model ATR42-
200, -300, -320, and -500 airplanes.
    (11) ATR--GIE Avions de Transport R[eacute]gional Model ATR72-
101, -102, -201, -202, -211, -212, and -212A airplanes.
    (12) The Boeing Company Model 747-8 series airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 35, Oxygen
System.

(e) Unsafe Condition

    This AD was prompted by reports of cylinder and valve assemblies
having oxygen leakage from the valve assembly vent hole, caused by
the absence of a guide that maintains appropriate spacing between
certain parts. The FAA is issuing this AD to address oxygen leakage
from the cylinder, which could result in decreased or insufficient
oxygen supply during a depressurization event; and heating or flow
friction, which could cause an ignition event in the valve assembly.

(f) Compliance

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

(g) Definition of Detailed Inspection

    For the purposes of this AD, a detailed inspection is an
intensive examination of a specific item, installation, or assembly
to detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at an
intensity deemed appropriate. Inspection aids such as mirror,
magnifying lenses, etc., may be necessary. Surface cleaning and
elaborate procedures may be required.

(h) Identification of Affected Cylinder and Valve Assemblies

    Within 60 days after the effective date of this AD, inspect the
oxygen valve assemblies, and oxygen cylinder and valve assemblies,
to determine if the serial numbers of the valve, cylinder, and
entire assembly, are listed in Appendix 1, ``Affected Shipments,''
of the applicable service information identified in paragraphs
(h)(1) through (3) of this AD. A review of airplane maintenance
records is acceptable in lieu of this inspection if the serial
numbers can be conclusively determined from that review.
    (1) AVOX Systems Inc. Alert Service Bulletin 10015804-35-01,
Revision 02, dated October 16, 2019.
    (2) AVOX Systems Inc. Alert Service Bulletin 10015804-35-02,
Revision 2, dated October 31, 2019.
    (3) AVOX Systems Inc. Alert Service Bulletin 10015804-35-03,
Revision 02, dated October 15, 2019.

(i) Inspection of the Gap, Parts Marking Actions, and Replacement

    If, during any inspection or records review required by
paragraph (h) of this AD, any oxygen valve assembly, valve or
cylinder of an oxygen cylinder and valve assembly, or oxygen
cylinder and valve assembly having an affected serial number is
found: Before further flight, do a detailed inspection for correct
spacing of the gap between the bottom of the packing retainer and
top of the valve body, in accordance with paragraph 3.C. of the
Accomplishment Instructions of the applicable service information
identified in paragraphs (h)(1) through (3) of this AD.
    (1) If the gap is found to be acceptable, as defined in the
applicable service information identified in paragraphs (h)(1)
through (3) of this AD, before further flight, do the parts marking
actions in accordance with paragraph 3.D.(1) of the Accomplishment
Instructions of the applicable service information identified in
paragraphs (h)(1) through (3) of this AD.
    (2) If the gap is found to be unacceptable, as defined in the
applicable service information identified in paragraphs (h)(1)
through (3) of this AD, before further flight, remove the affected
assembly, in accordance with paragraphs 3.D.(2) or 3.D.(3), as
applicable, of the Accomplishment Instructions of the applicable
service information identified in paragraphs (h)(1) through (3) of
this AD; and replace with a serviceable assembly.

(j) Reporting and Return of Parts

    (1) Report the results of the inspection required by paragraph
(i) of this AD within the applicable time specified in paragraph
(j)(1)(i) or (ii) of this AD. Report the results in accordance with
paragraph 3.D.(1)(a) of the Accomplishment Instructions of the
applicable service information identified in paragraphs (h)(1)
through (3) of this AD.
    (i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
    (ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
    (2) If, during the inspection required by paragraph (i) of this
AD, any gap is found to be unacceptable, within the applicable time
specified in paragraph (j)(2)(i) or (ii) of this AD, return the
assembly to the manufacturer in accordance with paragraph 3.D.(2) or
3.D.(3), as applicable, of the Accomplishment Instructions of the
applicable service information identified in paragraphs (h)(1)
through (3) of this AD, except you are not required to contact AVOX
for shipping instructions.
    (i) If the inspection was done on or after the effective date of
this AD: Return the assembly within 30 days after the inspection.
    (ii) If the inspection was done before the effective date of
this AD: Return the assembly within 30 days after the effective date
of this AD.

(k) Parts Installation Limitation

    As of the effective date of this AD, no AVOX Systems Inc. oxygen
valve assembly, or valve or cylinder that is part of an oxygen
cylinder and valve assembly, or oxygen cylinder and valve assembly
having an affected serial number identified in Appendix 1,
``Affected Shipments,'' of any AVOX Systems Inc. service information

identified in paragraphs (h)(1) through (3) of this AD may be
installed on any airplane unless the requirements of paragraph (i)
of this AD have been accomplished on that affected assembly.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions specified in
paragraphs (h) or (i) of this AD, if those actions were performed
before the effective date of this AD using the service information
specified in paragraphs (l)(1) through (5) of this AD.
    (1) AVOX Systems Inc. Service Bulletin 10015804-35-01, dated
March 6, 2019.
    (2) AVOX Systems Inc. Alert Service Bulletin 10015804-35-01,
Revision 01, dated July 9, 2019.
    (3) AVOX Systems Inc. Alert Service Bulletin 10015804-35-02,
Revision 1, dated September 4, 2019.
    (4) AVOX Systems Inc. Service Bulletin 10015804-35-03, dated
April 11, 2019.
    (5) AVOX Systems Inc. Alert Service Bulletin 10015804-35-03,
Revision 01, dated May 21, 2019.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, New York 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 ATTN: Program
Manager, Continuing Operational Safety, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-
228-7300; fax<PHONE_NUMBER>.
    (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.

(n) Related Information

    (1) For more information about this AD, contact Elizabeth
Dowling, Aerospace Engineer, Mechanical Systems and Administrative
Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone<PHONE_NUMBER>; email [email protected].
    (2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (o)(3) and (4) of this AD.

(o) 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) AVOX Systems Inc. Alert Service Bulletin 10015804-35-01,
Revision 02, dated October 16, 2019.
    (ii) AVOX Systems Inc. Alert Service Bulletin 10015804-35-02,
Revision 2, dated October 31, 2019.
    (iii) AVOX Systems Inc. Alert Service Bulletin 10015804-35-03,
Revision 02, dated October 15, 2019.
    (3) For service information identified in this AD, contact AVOX
Systems Inc., 225 Erie Street, Lancaster, NY 14086; telephone 716-
683-5100; internet https://www.safranaerosystems.com.
    (4) 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>.
    (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 protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on February 11, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-04146 Filed 2-25-22; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register: January 14, 2010 (Volume 75, Number 9)]
[Notices]
[Page 2138]
[DOCID:fr14ja10-55]

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DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. ER10-507-000]

ERA MA, LLC; Supplemental Notice That Initial Market-Based Rate
Filing Includes Request for Blanket Section 204 Authorization

January 7, 2010.

    This is a supplemental notice in the above-referenced proceeding of
ERA MA, LLC's application for market-based rate authority, with an
accompanying rate tariff, noting that such application includes a
request for blanket authorization, under 18 CFR Part 34, of future
issuances of securities and assumptions of liability.
    Any person desiring to intervene or to protest should file with the
Federal Energy Regulatory Commission, 888 First Street, NE.,
Washington, DC 20426, in accordance with Rules 211 and 214 of the
Commission's Rules of Practice and Procedure (18 CFR 385.211 and
385.214). Anyone filing a motion to intervene or protest must serve a
copy of that document on the Applicant.
    Notice is hereby given that the deadline for filing protests with
regard to the applicant's request for blanket authorization, under 18
CFR Part 34, of future issuances of securities and assumptions of
liability, is January 27, 2010.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper, using the FERC Online links at http://
www.ferc.gov. To facilitate electronic service, persons with Internet
access who will eFile a document and/or be listed as a contact for an
intervenor must create and validate an eRegistration account using the
eRegistration link. Select the eFiling link to log on and submit the
intervention or protests.
    Persons unable to file electronically should submit an original and
14 copies of the intervention or protest to the Federal Energy
Regulatory Commission, 888 First Street, NE., Washington, DC 20426.
    The filings in the above-referenced proceeding are accessible in
the Commission's eLibrary system by clicking on the appropriate link in
the above list. They are also available for review in the Commission's
Public Reference Room in Washington, DC. There is an eSubscription link
on the Web site that enables subscribers to receive e-mail notification
when a document is added to a subscribed docket(s). For assistance with
any FERC Online service, please e-mail<EMAIL_ADDRESS>or
call<PHONE_NUMBER> (toll free). For TTY, call<PHONE_NUMBER>.

Kimberly D. Bose,
Secretary.
[FR Doc. 2010-533 Filed 1-13-10; 8:45 am]
BILLING CODE 6717-01-P


[Federal Register Volume 86, Number 104 (Wednesday, June 2, 2021)]
[Rules and Regulations]
[Pages 29486-29488]
[FR Doc No: 2021-11443]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0223; Project Identifier AD-2020-00539-A;
Amendment 39-21550; AD 2021-10-17]
RIN 2120-AA64

Airworthiness Directives; Mooney International Corporation
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Mooney International Corporation (Mooney) Model M20V airplanes.
This AD was prompted by reports of short circuit and arcing of the
alternator main power cable in the engine compartment. This condition,
if unaddressed, could result in a fire hazard, loss of engine thrust
control, and reduced control of the airplane. This AD requires
inspecting the alternator main power cable and the exhaust crossover
tube for damage, replacing damaged parts as necessary, and installing
an additional alternator cable clamp. The FAA is issuing this AD to
address the unsafe condition on these products.

DATES: This AD is effective July 7, 2021.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 7,
2021.

ADDRESSES: For service information identified in this final rule,
contact Mooney International Corporation, 165 Al Mooney Road, North
Kerrville, TX 78028; phone:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
You may view this service information at the FAA, Airworthiness
Products Section, Operational Safety Branch, 901 Locust, Kansas City,
MO 64106. 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-
0223.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0223; 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: Jacob Fitch, Aviation Safety Engineer,
Fort Worth ACO Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177;
phone:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain serial-numbered
Mooney Model M20V airplanes. The NPRM published in the Federal Register
on March 9, 2021 (86 FR 13502; corrected March 17, 2021, 86 FR 14554).
The NPRM was prompted by reports of short circuit and arcing of the
alternator main power cable in the engine compartment. Mooney
determined the alternator main power cable was incorrectly positioned
with slack in the cable and allowed contact between the alternator main
power cable and turbocharger right-hand (RH) exhaust crossover tube. In
one instance, this contact caused arcing of the alternator main power
cable and created a hole in the RH exhaust crossover tube, which may
result in a fire hazard. A damaged crossover tube may also decrease
effectiveness of the turbochargers and cause complete loss of engine
power at higher altitudes (above 9,000 ft. above sea level). In the
NPRM, the FAA proposed to require inspecting the alternator main power
cable and the exhaust crossover tube and modifying the alternator main
power cable routing by installing an additional alternator cable clamp,
part number (P/N) MS21919WCJ6. This condition, if not addressed, could
result in an inflight fire and loss of engine thrust control, which may
lead to reduced control of the airplane. The FAA is issuing this AD to
address the unsafe condition on these products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of
the costs.

Conclusion

    The FAA reviewed the relevant data and determined that air safety
requires adopting this AD as proposed. Accordingly, the FAA is issuing
this AD to address the unsafe condition on these products. This AD is
adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Mooney International Corporation Service Bulletin
M20-340C, dated February 14, 2020. The service information specifies
inspecting the alternator main power cable and the exhaust crossover
tube for damage and replacing damaged parts as necessary. The service
information also contains procedures for modifying the alternator main
power cable routing by installing an additional alternator cable clamp,
P/N MS21919WCJ6.

    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 18 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
----------------------------------------------------------------------------------------------------------------
Inspect the cable and exhaust           .5 work-hour x $85 per                $0          $42.50            $765
 crossover tube for damage.              hour = $42.50.
Install additional cable clamp........  .5 work-hour x $85 per                10           52.50             945
                                         hour = $42.50.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace alternator main power cable...........  8 work-hours x $85 per hour =             $1,000          $1,680
                                                 $680.
Replace exhaust crossover tube................  8 work-hours x $85 per hour =              2,500           3,180
                                                 $680.
----------------------------------------------------------------------------------------------------------------

    The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some 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 adding the following new airworthiness
directive:

2021-10-17 Mooney International Corporation: Amendment 39-21550;
Docket No. FAA-2021-0223; Project Identifier AD-2020-00539-A.

(a) Effective Date

    This airworthiness directive (AD) is effective July 7, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Mooney International Corporation Model M20V
airplanes, serial numbers 33-0001 through 33-0018, certificated in
any category.

(d) Subject

    Joint Aircraft System Component Code 2400, Electrical Power
System.

(e) Unsafe Condition

    This AD was prompted by reports of short circuit and arcing of
the alternator main power cable in the engine compartment. The FAA
is issuing this AD to prevent arcing of the alternator main power
cable in the engine compartment. This condition, if not addressed,
could result in an inflight fire and loss of engine thrust control,
which may lead to reduced control of the airplane.

(f) Compliance

    Comply with this AD before further flight after the effective
date of this AD, unless already done.

(g) Required Actions

    (1) Inspect the alternator main power cable and the exhaust
crossover tube for burn marks, chafing, holes, and cracks, and
replace any cable and crossover tube that has a burn mark, chafing,
a hole, or a crack.
    (2) Install an additional alternator cable clamp part number
MS21919WCJ6 and ensure correct routing of the alternator main power
cable by following steps 1.5. through 1.9. of the Instructions in
Mooney International Corporation Service Bulletin M20-340C, dated
February 14, 2020.

(h) Special Flight Permit

    A special flight permit may be issued with the following
limitations:
    (1) Flights must not carry passengers;
    (2) Operation in daytime visual meteorological conditions only;
    (3) Straight and level flight must be maintained;
    (4) Operation in areas of known turbulence prohibited; and
    (5) Altitude limited to 9,000 ft. above sea level.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Fort Worth 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 Related Information.
    (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.

(j) Related Information

    For more information about this AD, contact Jacob Fitch,
Aviation Safety Engineer, Fort Worth ACO Branch, FAA, 10101 Hillwood
Pkwy., Fort Worth, TX 76177; phone:<PHONE_NUMBER>; fax: (817) 222-
5245; email<EMAIL_ADDRESS>
(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the
incorporation by reference 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) Mooney International Corporation Service Bulletin M20-340C,
dated February 14, 2020.
    (ii) [Reserved]
    (3) For Mooney International Corporation service information
identified in this AD, contact Mooney International Corporation, 165
Al Mooney Road, North Kerrville, TX 78028; phone:<PHONE_NUMBER>;
email<EMAIL_ADDRESS>    (4) You may view this service information at FAA, Airworthiness
Products Section, Operational Safety Branch, 901 Locust, Kansas
City, MO 64106. For information on the availability of this material
at the FAA, call<PHONE_NUMBER>.
    (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 May 5, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-11443 Filed 6-1-21; 8:45 am]
BILLING CODE 4910-13-P