[Federal Register Volume 84, Number 241 (Monday, December 16, 2019)]
[Rules and Regulations]
[Pages 68326-68330]
[FR Doc No: 2019-26963]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0326; Product Identifier 2018-NM-166-AD; Amendment
39-19808; AD 2019-23-14]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. This AD was prompted by significant changes made to
the airworthiness limitations (AWLs) related to fuel tank ignition
prevention and the nitrogen generation system. This AD requires
revising the existing maintenance or inspection program, as applicable,
to include new or revised AWLs. The FAA is issuing this AD to address
the unsafe condition on these products.

DATES: This AD is effective January 21, 2020.
    The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 21,
2020.

ADDRESSES: 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; phone:<PHONE_NUMBER>; internet: https://www.myboeingfleet.com. You may view this service information at the
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA.
For information on the availability of this material at the FAA, call
206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0326.

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-2019-
0326; 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 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: Serj Harutunian, Aerospace Engineer,
Propulsion Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone:<PHONE_NUMBER>; fax: 562-627-
5210; email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on June 10, 2019 (84 FR 26778).
The NPRM was prompted by significant changes made to the AWLs related
to fuel tank ignition prevention and the nitrogen generation system.
The NPRM proposed to require revising the existing maintenance or
inspection program, as applicable, to include new or revised AWLs.
    The FAA is issuing this AD to address the potential of ignition
sources inside fuel tanks, which, in combination with flammable fuel
vapors, could result in fuel tank explosions and consequent loss of the
airplane.

Comments

    The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.

Support for the NPRM

    Air Line Pilots Association, International (ALPA) agreed with the
intent of the NPRM.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that the installation of winglets
per Supplemental Type Certificate (STC) ST01219SE does not affect the
accomplishment of the manufacturer's service instructions.
    The FAA agrees with the commenter that STC ST01219SE does not
affect the accomplishment of the manufacturer's service instructions.
Therefore, the installation of STC ST01219SE does not affect the
ability to accomplish the actions required by this AD. The FAA has not
changed this AD in this regard.

Request for Additional Affected AD

    Boeing requested that the FAA include AD 2018-04-12, Amendment 39-
19208 (83 FR 9178, March 5, 2018) (``AD 2018-04-12''), as an affected
AD in the proposed AD. Boeing pointed out that AD 2018-04-12 requires
operators to incorporate certain AWLs included in certain previous
revisions of Boeing 737-100/200/200C/300/400/500 Airworthiness
Limitations (AWLs) and Certification Maintenance Requirements (CMRs),
D6-38278-CMR. Boeing explained that the specific AWLs referenced by AD
2018-04-12 are still present in the latest revision mandated by this
AD, but are at a later revision, and as such, should be considered
terminating action for the requirements of paragraph (h) of AD 2018-04-
12. Boeing noted that AD 2013-13-15, Amendment 39-17503 (78 FR 42415,
July 16, 2013) (``AD 2013-13-15''), has similar requirements to those
in AD 2018-04-12, and that those similar requirements in AD 2013-13-15
are terminated as specified in paragraph (j)(3) of the proposed AD.
    The FAA agrees with the commenter's request for the reasons
provided. The FAA has added paragraph (b)(7) to this AD to specify that
AD 2018-04-12 is affected by this AD, and paragraph (j)(7) to this AD
to specify that the requirements of paragraph (h) of AD 2018-04-12 are
terminated by the revision required by paragraph (g) of this AD.

Clarification That Previous Alternative Methods of Compliance (AMOCs)
Are Not Approved For This AD

    The regulatory text of the NPRM did not include a paragraph
specifying that AMOCs previously approved for the ADs specified in
paragraph (j) of this AD are approved for the corresponding
requirements of this AD. For clarity, the FAA has added paragraph
(k)(4) to this AD to specify that AMOCs that were previously approved
for the ADs specified in paragraph (j) of this AD are not approved as
AMOCs for this AD.

Conclusion

    The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule with the changes described previously
and minor editorial changes. The FAA has determined that these minor
changes:
     Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was
already proposed in the NPRM.
    The FAA also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing 737-100/200/200C/300/400/500 Airworthiness
Limitations (AWLs) and Certification Maintenance Requirements (CMRs),
D6-38278-CMR, dated March 2019. This service information describes AWLs
that include airworthiness limitation instructions (ALI) and critical
design configuration control limitations (CDCCL) tasks related to fuel
tank ignition prevention and the nitrogen generation system. 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.

Costs of Compliance

    The FAA estimates that this AD affects 381 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
    The FAA has determined that revising the existing maintenance or
inspection program takes an average of 90 work-hours per operator,
although the FAA recognizes that this number may vary from operator to
operator. In the past, the FAA has estimated that this action takes 1
work-hour per airplane. Since operators incorporate maintenance or
inspection program changes for their affected fleet(s), the FAA has
determined that a per-operator estimate is more accurate than a per-
airplane estimate. Therefore, the FAA estimates the total cost per
operator to be $7,650 (90 work-hours x $85 per work-hour).

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.
    This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.

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.

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):

2019-23-14 The Boeing Company: Amendment 39-19808; Docket No. FAA-
2019-0326; Product Identifier 2018-NM-166-AD.

(a) Effective Date

    This AD is effective January 21, 2020.

(b) Affected ADs

    This AD affects the ADs specified in paragraphs (b)(1) through
(7) of this AD.
    (1) AD 2008-10-09 R1, Amendment 39-16148 (74 FR 69264, December
31, 2009) (``AD 2008-10-09 R1'').
    (2) AD 2011-12-09, Amendment 39-16716 (76 FR 33988, June 10,
2011) (``AD 2011-12-09'').
    (3) AD 2013-13-15, Amendment 39-17503 (78 FR 42415, July 16,
2013) (``AD 2013-13-15'').
    (4) AD 2013-25-05, Amendment 39-17701 (78 FR 78701, December 27,
2013) (``AD 2013-25-05'').
    (5) AD 2016-18-16, Amendment 39-18647 (81 FR 65864, September
26, 2016) (``AD 2016-18-16'').
    (6) AD 2017-17-09, Amendment 39-18999 (82 FR 40477, August 25,
2017) (``AD 2017-17-09'').
    (7) AD 2018-04-12, Amendment 39-19208 (83 FR 9178, March 5,
2018) (``AD 2018-04-12'').

(c) Applicability

    This AD applies to all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel; 47,
Nitrogen Generation System.

(e) Unsafe Condition

    This AD was prompted by a determination that new or revised
airworthiness limitations (AWLs) are necessary related to fuel tank
ignition prevention and the nitrogen generation system. The FAA is
issuing this AD to address the potential of ignition sources inside
fuel tanks, which, in combination with flammable fuel vapors, could
result in fuel tank explosions and consequent loss of the airplane.

(f) Compliance

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

(g) Maintenance or Inspection Program Revision

    (1) For The Boeing Company Model 737-100, -200, and -200C series
airplanes: Within 60 days after the effective date of this AD,
revise the existing maintenance or inspection program, as
applicable, to incorporate the information specified in Section C,
including Subsections C.1, C.2, and C.3 of Boeing 737-100/200/200C/
300/400/500 Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D6-38278-CMR, dated March 2019,
except as provided in paragraph (h) of this AD. The initial
compliance time for the ALI tasks are within the applicable
compliance times specified in paragraphs (g)(1)(i) through (x) of
this AD.
    (i) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel
Tank'': Within 120 months after the most recent inspection was
performed as specified in AWL No. 28-AWL-01, or within 12 months
after the effective date of this AD if no initial inspection has
been performed.
    (ii) For AWL No. 28-AWL-03, ``Fuel Quantity Indicating System
(FQIS)--Out Tank Wiring Lightning Shield to Ground Termination'':
Within 120 months after accomplishment of the actions specified in
Boeing Service Bulletin 737-28A1178, or within 120 months after the
most recent inspection was performed as specified in AWL No. 28-AWL-
03, whichever is later.
    (iii) For AWL No. 28-AWL-21, ``Center Tank Fuel Boost Pump
Automatic Shutoff System'': Within 12 months after accomplishment of
the actions specified in Boeing Service Bulletin 737-28A1228, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-21, whichever is later.
    (iv) For AWL No. 28-AWL-22, ``Auxiliary Tank Fuel Boost Pump
Automatic Shutoff System'': Within 12 months after accomplishment of
the actions specified in Boeing Service Bulletin 737-28A1228, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-22, whichever is later.
    (v) For AWL No. 28-AWL-23, ``Over-Current and Arcing Protection
Electrical Design Features Operation--Boost Pump Ground Fault
Interrupter (GFI)'': Within 12 months after accomplishment of the
actions specified in Boeing Service Bulletin 737-28A1212, or within
12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-23, whichever is later.
    (vi) For AWL No. 28-AWL-24, ``Center Tank Fuel Boost Pump Power
Failed On Protection System'': Within 12 months after accomplishment
of the actions specified in Boeing Service Bulletin 737-28A1227, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-24, whichever is later.
    (vii) For AWL No. 28-AWL-25, ``Auxiliary Fuel Tank Boost Pump
Power Failed On Protection System'': Within 12 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1227, or within 12 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-25, whichever is later.
    (viii) For AWL No. 28-AWL-29, ``AC Fuel Boost Pump
Installation'': Within 72 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-29, or within 12 months
after the effective date of this AD if no inspection has been
performed in the last 72 months.
    (ix) For AWL No. 47-AWL-04, ``Nitrogen Generation System (NGS)--
Thermal Switch'': Within 22,500 flight hours after accomplishment of
the actions specified in Boeing Service Bulletin 737-47-1005; within
22,500 flight hours after accomplishment of the actions specified in
Boeing Service Bulletin 737-47-1008; or within 22,500 flight hours
after the most recent inspection was performed as specified in AWL
No. 47-AWL-04; whichever is latest.
    (x) For AWL No. 47-AWL-05, ``Nitrogen Generation System (NGS)--
Nitrogen Enriched Air (NEA) Distribution Ducting Integrity'': Within
14,500 flight hours after accomplishment of the actions specified in
Boeing Service Bulletin 737-47-1005; within

14,500 flight hours after accomplishment of the actions specified in
Boeing Service Bulletin 737-47-1008; or within 14,500 flight hours
after the most recent inspection was performed as specified in AWL
No. 47-AWL-05; whichever is latest.
    (2) For The Boeing Company Model 737-300, -400, and -500 series
airplanes: Within 60 days after the effective date of this AD,
revise the existing maintenance or inspection program, as
applicable, to incorporate the information specified in Section C,
including Subsections C.1, C.2, and C.3 of Boeing 737-100/200/200C/
300/400/500 Airworthiness Limitations (AWLs) and Certification
Maintenance Requirements (CMRs), D6-38278-CMR, dated March 2019;
except as provided in paragraph (h) of this AD. The initial
compliance time for the ALI tasks are within the applicable
compliance times specified in paragraphs (g)(2)(i) through (xi) of
this AD.
    (i) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel
Tank'': Within 120 months after the most recent inspection was
performed as specified in AWL No. 28-AWL-01, or within 12 months
after the effective date of this AD if no initial inspection has
been performed.
    (ii) For AWL No. 28-AWL-03, ``Fuel Quantity Indicating System
(FQIS)--Out Tank Wiring Lightning Shield to Ground Termination'':
Within 120 months after accomplishment of the actions specified in
Boeing Service Bulletin 737-28A1175; within 120 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1183; within 120 months after accomplishment of the actions
specified in Boeing Service Bulletin 737-28A1186; or within 120
months after the most recent inspection was performed as specified
in AWL No. 28-AWL-03; whichever is latest.
    (iii) For AWL No. 28-AWL-20, ``Center Tank Fuel Boost Pump
Automatic Shutoff System'': Within 12 months after accomplishment of
the actions specified in Boeing Service Bulletin 737-28A1216, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-20, whichever is later.
    (iv) For AWL No. 28-AWL-21, ``Auxiliary Tank Fuel Boost Pump
Automatic Shutoff System'': Within 12 months after accomplishment of
the actions specified in Boeing Service Bulletin 737-28A1216, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-21, whichever is later.
    (v) For AWL No. 28-AWL-22, ``Over-Current and Arcing Protection
Electrical Design Features Operation--Boost Pump Ground Fault
Interrupter (GFI)'': Within 12 months after accomplishment of the
actions specified in Boeing Service Bulletin 737-28A1212, or within
12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-22, whichever is later.
    (vi) For AWL No. 28-AWL-23, ``Center Tank Fuel Boost Pump Power
Failed On Protection System'': Within 12 months after accomplishment
of the actions specified in Boeing Service Bulletin 737-28A1227, or
within 12 months after the most recent inspection was performed as
specified in AWL No. 28-AWL-23, whichever is later.
    (vii) For AWL No. 28-AWL-24, ``Auxiliary Fuel Tank Boost Pump
Power Failed On Protection System'': Within 12 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1227, or within 12 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-24, whichever is later.
    (viii) For AWL No. 28-AWL-27, ``AC Fuel Boost Pump
Installation'': Within 72 months after the most recent inspection
was performed as specified in AWL No. 28-AWL-27, or within 12 months
after the effective date of this AD if no inspection has been
performed in the last 72 months.
    (ix) For AWL No. 28-AWL-31, ``Cushion Clamps and Teflon Sleeving
Installed on Out-of-Tank Wire Bundles Installed on Brackets that are
Mounted Directly on the Fuel Tanks'': Within 144 months after
accomplishment of the actions specified in Boeing Service Bulletin
737-28A1228.
    (x) For AWL No. 47-AWL-04, ``Nitrogen Generation System (NGS)--
Thermal Switch'': Within 22,500 flight hours after accomplishment of
the actions specified in Boeing Service Bulletin 737-47-1005; within
22,500 flight hours after accomplishment of the actions specified in
Boeing Service Bulletin 737-47-1008; or within 22,500 flight hours
after the most recent inspection was performed as specified in AWL
No. 47-AWL-04; whichever is latest.
    (xi) For AWL No. 47-AWL-05, ``Nitrogen Generation System (NGS)--
Nitrogen Enriched Air (NEA) Distribution Ducting Integrity'': Within
14,500 flight hours after accomplishment of the actions specified in
Boeing Service Bulletin 737-47-1005; within 14,500 flight hours
after accomplishment of the actions specified in Boeing Service
Bulletin 737-47-1008; or within 14,500 flight hours after the most
recent inspection was performed as specified in AWL No. 47-AWL-05;
whichever is latest.

(h) Additional Acceptable Wire Types and Sleeving

    As an option to accomplishing the actions required by paragraph
(g) of this AD, the changes specified in paragraphs (h)(1) and (2)
of this AD are acceptable.
    (1) Where AWL No. 28-AWL-05 identifies wire types BMS 13-48, BMS
13-58, and BMS 13-60, the following wire types are acceptable: MIL-
W-22759/16, SAE AS22759/16 (M22759/16), MIL-W-22759/32, SAE AS22759/
32 (M22759/32), MIL-W-22759/34, SAE AS22759/34 (M22759/34), MIL-W-
22759/41, SAE AS22759/41 (M22759/41), MIL-W-22759/86, SAE AS22759/86
(M22759/86), MIL-W-22759/87, SAE AS22759/87 (M22759/87), MIL-W-
22759/92, and SAE AS22759/92 (M22759/92); and MIL-C-27500 and NEMA
WC 27500 cables constructed from these military or SAE specification
wire types, as applicable.
    (2) Where AWL No. 28-AWL-05 identifies TFE-2X Standard wall for
wire sleeving, the following sleeving materials are acceptable:
Roundit 2000NX and Varglas Type HO, HP, or HM.

(i) No Alternative Actions, Intervals, or Critical Design Configuration
Control Limitations (CDCCLs)

    After the existing maintenance or inspection program has been
revised as required by paragraph (g) of this AD, no alternative
actions (e.g., inspections), intervals, or CDCCLs may be used unless
the actions, intervals, and CDCCLs are approved as an alternative
method of compliance (AMOC) in accordance with the procedures
specified in paragraph (k) of this AD.

(j) Terminating Actions for Certain AD Requirements

    Accomplishment of the revision required by paragraph (g) of this
AD terminates the requirements specified in paragraphs (j)(1)
through (7) of this AD for that airplane:
    (1) All requirements of AD 2008-10-09 R1.
    (2) The revision required by paragraph (l) of AD 2011-12-09.
    (3) The revision required by paragraph (h) of AD 2013-13-15.
    (4) The revision required by paragraph (j) of AD 2013-25-05.
    (5) The revisions required by paragraphs (l) and (n) of AD 2016-
18-16.
    (6) The revision required by paragraph (h) of AD 2017-17-09.
    (7) The revision required by paragraph (h) of AD 2018-04-12.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, FAA, has the authority
to approve AMOCs for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
request to your principal inspector or 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 (l) 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 Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Los
Angeles ACO Branch, FAA, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
    (4) AMOCs that were previously approved for the ADs specified in
paragraph (j) of this AD are not approved as AMOCs for this AD.

(l) Related Information

    For more information about this AD, contact Serj Harutunian,
Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5254; fax:<PHONE_NUMBER>; email<EMAIL_ADDRESS>

(m) 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) Boeing 737-100/200/200C/300/400/500 Airworthiness
Limitations (AWLs) and Certification Maintenance Requirements
(CMRs), D6-38278-CMR, dated March 2019.
    (ii) [Reserved]
    (3) 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; phone:<PHONE_NUMBER>; internet: https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
    (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 in Des Moines, Washington, on November 20, 2019.
Dorr Anderson,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-26963 Filed 12-13-19; 8:45 am]
 BILLING CODE 4910-13-P


[Federal Register Volume 84, Number 212 (Friday, November 1, 2019)]
[Proposed Rules]
[Pages 58638-58641]
[FR Doc No: 2019-23832]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0827; Product Identifier 2019-SW-014-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters (Type Certificate
Previously Held by Eurocopter France) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2011-12-07 for Eurocopter France (now Airbus Helicopters) Model SA-
365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and
SA-366G1 helicopters. AD 2011-12-07 currently requires repetitively
inspecting the adhesive bead between the bushings and the Starflex star
(Starflex) arms and the Starflex arm ends. Since the FAA issued AD
2011-12-07, Airbus Helicopters has developed an improved Starflex. This
proposed AD would retain the requirements of AD 2011-12-07 and revise
the Applicability paragraph by omitting helicopters with the improved
Starflex installed. The FAA is proposing this AD to address the unsafe
condition on these products.

DATES: The FAA must receive comments on this proposed AD by December
31, 2019.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
     Fax:<PHONE_NUMBER>.
     Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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-2019-
0827; 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 proposed AD, the European Aviation Safety Agency (EASA) AD, the
economic 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 service information identified in this proposed rule, contact
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052;
telephone<PHONE_NUMBER> or<PHONE_NUMBER>; fax<PHONE_NUMBER>; or at
http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You

may view this service information at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort
Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone<PHONE_NUMBER>;
email<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to participate in this rulemaking by submitting
written comments, data, or views. The FAA also invites comments
relating to the economic, environmental, energy, or federalism impacts
that might result from adopting the proposals in this document. The
most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. To ensure the docket does not contain duplicate comments,
commenters should send only one copy of written comments, or if
comments are filed electronically, commenters should submit only one
time.
    The FAA will file in the docket all comments that the FAA receives,
as well as a report summarizing each substantive public contact with
FAA personnel concerning this proposed rulemaking. Before acting on
this proposal, the FAA will consider all comments received on or before
the closing date for comments. The FAA will consider comments filed
after the comment period has closed if it is possible to do so without
incurring expense or delay. The FAA may change this proposal in light
of the comments received.

Discussion

    The FAA issued AD 2011-12-07, Amendment 39-16714 (76 FR 35346, June
17, 2011) (``AD 2011-12-07'') for Eurocopter France (now Airbus
Helicopters) Model SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-
365N2, AS 365 N3, and SA-366G1 helicopters. AD 2011-12-07 requires
repetitively inspecting the adhesive bead between the bushings and the
Starflex arms for a crack, a gap, and loss of the adhesive bead,
inspecting the Starflex arm ends for delamination, and replacing the
Starflex if any of these conditions are found. AD 2011-12-07 was
prompted by three cases of deterioration of a Starflex arm end. In two
of these cases, the deterioration caused high amplitude vibrations in
flight, compelling the pilot to make a precautionary landing. The
requirements of AD 2011-12-07 are intended to prevent failure of the
Starflex, high-amplitude vibrations in flight, and subsequent loss of
control of the helicopter.

Actions Since AD 2011-12-07 Was Issued

    Since the FAA issued AD 2011-12-07, Airbus Helicopters has
developed new part-numbered Starflex, 365A31-1212-00 and 365A31-1213-
00, with different material. This change in material improves the
reliability and technical performance of the Starflex, improves
temperature-related behavior in the area of the Starflex arm ends, and
increases dimension margins. Subsequently, Airbus Helicopters has
extended the inspection interval of Starflex arm ends with these
Starflex installed. Airbus Helicopters identifies helicopters with
Starflex part number 365A31-1212-00 or 365A31-1213-00 installed as
Modification (MOD) 0762C37.
    Accordingly, EASA, which is the Technical Agent for the Member
States of the European Union, issued AD No. 2008-0165R1, dated June 30,
2017 (EASA AD 2008-0165R1), to address this unsafe condition for Airbus
Helicopters Model SA 365 N, SA 365 N1, AS 365 N2, AS 365 N3, SA 365 C,
SA 365 C1, SA 365 C2, SA 365 C3 and SA 366 G1 helicopters, except
helicopters with MOD 0762C37 installed in production. EASA advises that
the Airbus Helicopters Starflex manufactured with improved materials
make the 10-hour repetitive inspections specified in the original issue
of EASA AD 2008-0165R1 unnecessary. EASA AD 2008-0165R1 retains the
repetitive inspections from the original issue but does not apply to
helicopters with the new Starflex.
    Also since the FAA issued AD 2011-12-07, Eurocopter France changed
its name to Airbus Helicopters. This proposed AD reflects that change
and updates the contact information to obtain service documentation.

FAA's Determination

    These helicopters have been approved by EASA and are approved for
operation in the United States. Pursuant to the FAA's bilateral
agreement with the European Union, EASA has notified the FAA of the
unsafe condition described in its AD. The FAA is proposing this AD
after evaluating all known relevant information and determined that an
unsafe condition is likely to exist or develop on other helicopters of
the same type designs.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed one document that co-publishes four Airbus
Helicopters Emergency Alert Service Bulletin (EASB) identification
numbers: No. 05.00.51 for Model 365N-series helicopters, No. 05.35 for
Model 366G1 helicopters, No. 05.28 for Model 365C-series helicopters,
and No. 05.00.21 for non FAA-type certificated military helicopters,
all Revision 4 and dated November 20, 2014. EASB Nos. 05.00.51, 05.35,
and 05.28 are proposed for incorporation by reference in this proposed
AD. EASB No. 05.00.21 is not proposed for incorporation by reference in
this proposed AD.
    This service information specifies visually inspecting the adhesive
bead on the bushes of the Starflex arm ends for bonding failure of the
bushes and distortion of the Starflex arm ends. This service
information also specifies inspecting the leading edges and the
trailing edges of the Starflex arm ends for delamination.
    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 Airbus Helicopters Master Servicing Manual (MSM)
AS 365 N for Model SA-365N helicopters, MSM AS 365 N1 for Model SA-
365N1 helicopters, MSM AS 365 N2 for Model AS-365N2 helicopters, and
MSM AS 365 N3 for Model AS 365 N3 helicopters, all Revision 7 and dated
October 9, 2017. This service information provides a schedule of
maintenance tasks for the helicopters.
    The FAA also reviewed one document that co-publishes four
Eurocopter EASB identification numbers: No. 05.00.51 for Model 365N-
series helicopters, No. 05.35 for Model 366G1 helicopters, No. 05.28
for Model 365C-series helicopters, and No. 05.00.21 for non FAA-type
certificated military helicopters, all Revision 3 and dated August 18,
2008. This service information specifies the same Accomplishment
Instructions as Revision 4, which is issued under the name Airbus
Helicopters, although Revision 4 excludes helicopters that have MOD
0762C37 installed.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 2011-12-07 to
repetitively inspect the adhesive bead between the bushings and the
Starflex arms for a crack, a gap, and loss of the adhesive bead, and
repetitively inspect

the Starflex arm ends for delamination. However, this proposed AD would
not apply to helicopters with MOD 0762C37 installed.

Differences Between This Proposed AD and the EASA AD

    The EASA AD uses the word ``check,'' whereas this proposed AD uses
the word ``inspect'' instead. In some ADs, the FAA uses the word
``check'' to designate specific actions that may be performed by the
owner/operator (pilot). An ``inspection'' is a maintenance action that
must be performed by a certificated person as specified in 14 CFR 43.3.

Costs of Compliance

    The FAA estimates that this proposed AD affects 35 helicopters of
U.S. Registry. The FAA estimates that operators may incur the following
costs in order to comply with this AD. Labor costs are estimated at $85
per work-hour.
    Inspecting the Starflex would take about 0.25 work-hour for an
estimated cost of $21 per helicopter and $735 for the U.S. fleet per
inspection cycle. Replacing the Starflex would take about 10 work-hours
and parts would cost about $65,900 for an estimated cost of $66,750.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    The FAA 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, I certify this proposed regulation:
    (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.
    The FAA prepared an economic evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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 removing Airworthiness Directive (AD)
2011-12-07, Amendment 39-16714 (76 FR 35346, June 17, 2011), and adding
the following new AD:

Airbus Helicopters (Type Certificate Previously Held by Eurocopter
France): Docket No. FAA-2019-0827; Product Identifier 2019-SW-014-
AD.

(a) Applicability

    This AD applies to Airbus Helicopters (Type Certificate
previously held by Eurocopter France) Model SA-365C, SA-365C1, SA-
365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1
helicopters, certificated in any category, without Airbus
Helicopters Modification 0762C37 (starflex arm part number (P/N)
365A31-1212-00 or P/N 365A31-1213-00) installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of the Starflex
star (Starflex) arm. This condition could result in high amplitude
vibrations in flight and subsequent loss of control of the
helicopter.

(c) Affected ADs

    This AD replaces AD 2011-12-07, Amendment 39-16714 (76 FR 35346,
June 17, 2011).

(d) Comments Due Date

    The FAA must receive comments by December 31, 2019.

(e) Compliance

    You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.

 (f) Required Actions

    Within 10 hours time-in-service (TIS) and thereafter at
intervals not to exceed 10 hours TIS:
    (1) Visually inspect the adhesive bead between the bushing and
the Starflex arm for a crack, a gap, and loss of the adhesive bead,
and inspect the Starflex arm ends for delamination in accordance
with the Accomplishment Instructions, paragraphs 2.B.1. and 2.B.2.
of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No.
05.00.51, Revision 4, dated November 20, 2014 (EASB 05.00.51), EASB
No. 05.35, Revision 4, dated November 20, 2014 (EASB 05.35), or EASB
No. 05.28, Revision 4, dated November 20, 2014 (EASB 05.28), as
applicable to your model helicopter.
    (2) If there is a crack in the shockproof paint around the
entire adhesive bead where the Starflex arm joins the bushing (as
shown in Figure 2 of EASB 05.00.51, EASB 05.35, or EASB 05.28, as
applicable to your model helicopter), a gap between the adhesive
bead and the bushing (as shown in Figure 3 of EASB 05.00.51, EASB
05.35, or EASB 05.28, as applicable to your model helicopter),
delamination of a Starflex arm end (as shown in Figure 4 of EASB
05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model
helicopter), or loss of adhesive bead (as shown in Figure 5 of EASB
05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model
helicopter), replace the Starflex before further flight.

 (g) Credit for Previous Actions

    Actions accomplished before the effective date of this AD in
accordance with the procedures specified in Eurocopter Emergency
Alert Service Bulletin Nos. 05.00.51, 05.35, or 05.28, all Revision
3 and dated August 18, 2008, as applicable to your model helicopter,
are considered acceptable for compliance with the corresponding
actions specified in paragraph (f) of this AD as long as the last
inspection was accomplished within the prior 10 hours TIS.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards
Branch, FAA, may approve AMOCs for this AD. Send your proposal to:
Matt Fuller, Senior Aviation Safety Engineer, Safety Management
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy.,
Fort Worth, TX 76177; telephone<PHONE_NUMBER>; email<EMAIL_ADDRESS>    (2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office
or

certificate holding district office before operating any aircraft
complying with this AD through an AMOC.

(i) Additional Information

    (1) Airbus Helicopters Master Servicing Manual (MSM) AS 365 N,
MSM AS 365 N1, MSM AS 365 N2, and MSM AS 365 N3, all Revision 7 and
dated October 9, 2017; and Eurocopter Emergency Alert Service
Bulletin Nos. 05.00.51, 05.35, 05.28, and 05.00.21, all Revision 3
and dated August 18, 2008, which are not incorporated by reference,
contain additional information about the subject of this AD. For
service information identified in this AD, contact Airbus
Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone
(972) 641-0000 or<PHONE_NUMBER>; fax<PHONE_NUMBER>; or at http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html.
You may view a copy of the service information at the FAA, Office of
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room
6N-321, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2008-0165R1, dated June 30, 2017. You
may view the EASA AD on the internet at http://www.regulations.gov
in the AD Docket.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor
System.

    Issued in Fort Worth, Texas, on October 21, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2019-23832 Filed 10-31-19; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register Volume 77, Number 18 (Friday, January 27, 2012)]
[Notices]
[Page 4384]
[FR Doc No: 2012-1741]

=======================================================================
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SECURITIES AND EXCHANGE COMMISSION

Submission for OMB Review; Comment Request

Upon Written Request, Copies Available From: Securities and Exchange
Commission, Office of Investor Education and Advocacy, Washington, DC
20549-0213.

Extension:
Regulation G; OMB Control No. 3235-0576; SEC File No. 270-518.

    Notice is hereby given that pursuant to the Paperwork Reduction Act
of 1995 (44 U.S.C. 3501 et seq.) the Securities and Exchange Commission
(``Commission'') has submitted to the Office of Management and Budget a
request for extension of the previously approved collection of
information discussed below.
    Regulation G (17 CFR 244.100-244.102) under the Securities Exchange
Act of 1934 (the ``Exchange Act'') (15 U.S.C. 78a et seq.) requires
Exchange Act registrants that disclose or release financial information
in a manner that is calculated or presented other than in accordance
with generally accepted accounting principles (``GAAP'') to provide a
reconciliation of the non-GAAP financial information to the most
directly comparable GAAP financial measure. Regulation G implemented
the requirements of Section 401 of the Sarbanes-Oxley Act of 2002 (15
U.S.C. 7261). We estimate that approximately 14,000 public companies
must comply with Regulation G approximately six times a year for a
total of 84,000 responses annually. We estimated that it takes
approximately 0.5 hours per response (84,000 x 0.5 hours) for a total
reporting burden of 42,000 hours annually.
    An agency may not conduct or sponsor, and a person is not required
to respond to, a collection of information unless it displays a
currently valid control number.
    The public may view the background documentation for this
information collection at the following Web site, www.reginfo.gov.
Comments should be directed to: (i) Desk Officer for the Securities and
Exchange Commission, Office of Information and Regulatory Affairs,
Office of Management and Budget, Room 10102, New Executive Office
Building, Washington, DC 20503, or by sending an email to<EMAIL_ADDRESS>and (ii) Thomas Bayer, Director/Chief Information
Officer, Securities and Exchange Commission, c/o Remi Pavlik-Simon,
6432 General Green Way, Alexandria, VA 22312 or send an email to<EMAIL_ADDRESS>Comments must be submitted to OMB within 30 days of
this notice.

    Dated: January 23, 2012.
Kevin M. O'Neill,
Deputy Secretary.
[FR Doc. 2012-1741 Filed 1-26-12; 8:45 am]
BILLING CODE 8011-01-P


[Federal Register Volume 87, Number 195 (Tuesday, October 11, 2022)]
[Rules and Regulations]
[Pages 61236-61237]
[FR Doc No: 2022-21861]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0977; Project Identifier AD-2022-00419-E;
Amendment 39-22205; AD 2022-21-06]
RIN 2120-AA64

Airworthiness Directives; General Electric Company Turbofan
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain General Electric Company (GE) CF34-8C and CF34-8E model
turbofan engines. This AD was prompted by a report of a crack found on
the low-pressure turbine (LPT) stage 5 disk at the forward arm area.
This AD requires the removal of the affected LPT stage 5 disk and
replacement with a part eligible for installation. The FAA is issuing
this AD to address the unsafe condition on these products.

DATES: This AD is effective November 15, 2022.

ADDRESSES:
    AD Docket: You may examine the AD docket at regulations.gov by
searching for and locating Docket No. FAA-2022-0977; 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:  Scott Stevenson, Aviation Safety
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803;
phone:<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 GE CF34-8C1,
CF34-8C5, CF34-8C5A1, CF34-8C5A2, CF34-8C5A3, CF34-8C5B1, CF34-8E2,
CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1
model turbofan engines. The NPRM published in the Federal Register on
August 1, 2022 (87 FR 46906). The NPRM was prompted by a report of a
crack found on the LPT stage 5 disk at the forward arm area. In the
NPRM, the FAA proposed to require the removal of the affected LPT stage
5 disk and replacement with a part eligible for installation. The FAA
is issuing this AD to address the unsafe condition on these products.

Discussion of Final Airworthiness Directive

Comments

    The FAA received one comment from Air Line Pilots Association,
International (ALPA). ALPA supported the NPRM without change.

Conclusion

    The FAA reviewed the relevant data, considered the comment
received, and determined that air safety requires adopting the 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

    The FAA reviewed GE CF34-8C Service Bulletin (SB) 72-0352 R00,
dated September 20, 2021, and GE CF34-8E SB 72-0240 R00, dated
September 20, 2021. These SBs, differentiated by engine model, describe
procedures for removing and replacing the affected LPT stage 5 disk,
part number (P/N) 4117T14P02, with a new LPT stage 5 disk, P/N
4117T14P03.

Costs of Compliance

    The FAA estimates that this AD affects 112 engines installed on
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
----------------------------------------------------------------------------------------------------------------
Remove and replace the LPT stage 5  2 work-hours x $85     $30,500 (pro-rated)..         $30,670      $3,435,040
 disk.                               per hour = $170.
----------------------------------------------------------------------------------------------------------------

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:

2022-21-06 General Electric Company: Amendment 39-22205; Docket No.
FAA-2022-0977; Project Identifier AD-2022-00419-E.

(a) Effective Date

    This airworthiness directive (AD) is effective November 15,
2022.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company CF34-8C1, CF34-8C5,
CF34-8C5A1, CF34-8C5A2, CF34-8C5A3, CF34-8C5B1, CF34-8E2, CF34-
8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1
model turbofan engines with an installed low-pressure turbine (LPT)
stage 5 disk, part number (P/N) 4117T14P02.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine
Section.

(e) Unsafe Condition

    This AD was prompted by a report of a crack found on the LPT
stage 5 disk at the forward arm area. The FAA is issuing this AD to
prevent failure of the LPT stage 5 disk. The unsafe condition, if
not addressed, could result in loss of engine thrust control and
reduced control of the airplane.

(f) Compliance

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

(g) Required Actions

    During the next piece-part exposure after the affected LPT stage
5 disk accumulates 8,000 cycles since new (CSN), remove the affected
LPT stage 5 disk and replace with a part eligible for installation.

(h) Installation Prohibition

    Do not install an affected LPT stage 5 disk with 8,000 CSN or
more into the LPT module of the engine.

(i) Definitions

    (1) For the purpose of this AD, a ``part eligible for
installation'' is an LPT stage 5 disk, P/N 4117T14P03, or later
approved P/N.
    (2) For the purpose of this AD, ``piece-part exposure'' is when
the LPT module is separated from the engine and the LPT stage 5
blades are removed from the LPT stage 5 disk.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO 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 (k) of this AD and email to: [email protected].
    (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.

(k) Related Information

    For more information about this AD, contact Scott Stevenson,
Aviation Safety Engineer, ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone:<PHONE_NUMBER>; email:
[email protected].

(l) Material Incorporated by Reference

    None.

    Issued on October 3, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-21861 Filed 10-7-22; 8:45 am]
BILLING CODE 4910-13-P


[Federal Register: July 18, 2008 (Volume 73, Number 139)]
[Rules and Regulations]
[Page 41272-41274]
[DOCID:fr18jy08-16]

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ENVIRONMENTAL PROTECTION AGENCY

40 CFR Part 52

[EPA-R03-OAR-2008-0184; FRL-8693-4]

Approval and Promulgation of Air Quality Implementation Plans;
Pennsylvania; Section 110(a)(1) 8-Hour Ozone Maintenance Plan and 2002
Base-Year Inventory for the Juniata County Area

AGENCY: Environmental Protection Agency (EPA).

ACTION: Final rule.

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

SUMMARY: EPA is approving a State Implementation Plan (SIP) revision
submitted by the Commonwealth of Pennsylvania. The Pennsylvania
Department of Environmental Protection (PADEP) submitted a SIP revision
consisting of a maintenance plan that provides for continued attainment
of the 8-hour ozone national ambient air quality standard (NAAQS) for
at least 10 years after the April 30, 2004 designations, as well as a
2002 base-year inventory for the Juniata County Area. EPA is approving
the maintenance plan and the 2002 base-year inventory for the Juniata
County Area as revisions to the Pennsylvania SIP in accordance with the
requirements of the Clean Air Act (CAA).

EFFECTIVE DATE: This final rule is effective on August 18, 2008.

ADDRESSES: EPA has established a docket for this action under Docket ID
Number EPA-R03-OAR-2008-0184. All documents in the docket are listed in
the www.regulations.gov Web site. Although listed in the electronic
docket, some information is not publicly available, i.e., confidential
business information (CBI) or other information whose disclosure is
restricted by statute. Certain other material, such as copyrighted
material, is not placed on the Internet and will be publicly available
only in hard copy form. Publicly available docket materials are

available either electronically through www.regulations.gov or in hard
copy for public inspection during normal business hours at the Air
Protection Division, U.S. Environmental Protection Agency, Region III,
1650 Arch Street, Philadelphia, Pennsylvania 19103. Copies of the State
submittal are available at the Pennsylvania Department of Environment
Protection, Bureau of Air Quality Control, P.O. Box 8468, 400 Market
Street, Harrisburg, Pennsylvania 17105.

FOR FURTHER INFORMATION CONTACT: Melissa Linden,<PHONE_NUMBER>, or by
e-mail at<EMAIL_ADDRESS>
SUPPLEMENTARY INFORMATION:

I. Background

    On May 27, 2008 (73 FR 30352), EPA published a notice of proposed
rulemaking (NPR) for the Commonwealth of Pennsylvania. The NPR proposed
approval of Pennsylvania's SIP revision that establishes a maintenance
plan for the Juniata County Area that provides for continued attainment
of the 8-hour ozone NAAQS for at least 10 years after designation, and
a 2002 base-year emissions inventory. The formal SIP revisions were
submitted by PADEP on December 17, 2007. Other specific requirements of
Pennsylvania's SIP revision and the rationales for EPA's proposed
actions are explained in the NPR and will not be restated here. No
public comments were received on the NPR.

II. Final Action

    EPA is approving the maintenance plan and the 2002 base-year
inventory for the Juniata County Area, submitted on December 17, 2007,
as revisions to the Pennsylvania SIP. EPA is approving the maintenance
plan and 2002 base-year inventory for the Juniata County Area because
it meets the requirements of section 110(a)(1) of the CAA.

III. Statutory and Executive Order Reviews

A. General Requirements

    Under the Clean Air Act, the Administrator is required to approve a
SIP submission that complies with the provisions of the Act and
applicable Federal regulations. 42 U.S.C. 7410(k); 40 CFR 52.02(a).
Thus, in reviewing SIP submissions, EPA's role is to approve state
choices, provided that they meet the criteria of the Clean Air Act.
Accordingly, this action merely approves state law as meeting Federal
requirements and does not impose additional requirements beyond those
imposed by state law. For that reason, this action:
     Is not a ``significant regulatory action'' subject to
review by the Office of Management and Budget under Executive Order
12866 (58 FR 51735, October 4, 1993);
     Does not impose an information collection burden under the
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.);
     Is certified as not having a significant economic impact
on a substantial number of small entities under the Regulatory
Flexibility Act (5 U.S.C. 601 et seq.);
     Does not contain any unfunded mandate or significantly or
uniquely affect small governments, as described in the Unfunded
Mandates Reform Act of 1995 (Pub. L. 104-4);
     Does not have Federalism implications as specified in
Executive Order 13132 (64 FR 43255, August 10, 1999);
     Is not an economically significant regulatory action based
on health or safety risks subject to Executive Order 13045 (62 FR
19885, April 23, 1997);
     Is not a significant regulatory action subject to
Executive Order 13211 (66 FR 28355, May 22, 2001);
     Is not subject to requirements of Section 12(d) of the
National Technology Transfer and Advancement Act of 1995 (15 U.S.C. 272
note) because application of those requirements would be inconsistent
with the Clean Air Act; and
     Does not provide EPA with the discretionary authority to
address, as appropriate, disproportionate human health or environmental
effects, using practicable and legally permissible methods, under
Executive Order 12898 (59 FR 7629, February 16, 1994).
    In addition, this rule does not have tribal implications as
specified by Executive Order 13175 (65 FR 67249, November 9, 2000),
because the SIP is not approved to apply in Indian country located in
the state, and EPA notes that it will not impose substantial direct
costs on tribal governments or preempt tribal law.

B. Submission to Congress and the Comptroller General

    The Congressional Review Act, 5 U.S.C. 801 et seq., as added by the
Small Business Regulatory Enforcement Fairness Act of 1996, generally
provides that before a rule may take effect, the agency promulgating
the rule must submit a rule report, which includes a copy of the rule,
to each House of the Congress and to the Comptroller General of the
United States. EPA will submit a report containing this action and
other required information to the U.S. Senate, the U.S. House of
Representatives, and the Comptroller General of the United States prior
to publication of the rule in the Federal Register. A major rule cannot
take effect until 60 days after it is published in the Federal
Register. This action is not a ``major rule'' as defined by 5 U.S.C.
804(2).

C. Petitions for Judicial Review

    Under section 307(b)(1) of the Clean Air Act, petitions for
judicial review of this action must be filed in the United States Court
of Appeals for the appropriate circuit September 16, 2008. Filing a
petition for reconsideration by the Administrator of this final rule
does not affect the finality of this action for the purposes of
judicial review nor does it extend the time within which a petition for
judicial review may be filed, and shall not postpone the effectiveness
of such rule or action.
    This action approving the maintenance plan and the 2002 base-year
inventory for the Juniata County Area may not be challenged later in
proceedings to enforce its requirements. (See section 307(b)(2).)

List of Subjects in 40 CFR Part 52

    Environmental protection, Air pollution control, Incorporation by
reference, Nitrogen dioxide, Ozone, Reporting and recordkeeping
requirements, Volatile organic compounds.

    Dated: July 3, 2008.
Donald S. Welsh,
Regional Administrator, Region III.

0
40 CFR part 52 is amended as follows:

PART 52--[AMENDED]

0
1. The authority citation for part 52 continues to read as follows:

    Authority: 42 U.S.C. 7401 et seq.

Subpart NN--Pennsylvania

0
2. In Sec.  52.2020, the table in paragraph (e)(1) is amended by adding
an entry for the 8-Hour Ozone Maintenance Plan and 2002 Base-Year
Inventory for Juniata County at the end of the table to read as
follows:

Sec.  52.2020  Identification of plan.

* * * * *
    (e) * * *
    (1) * * *

--------------------------------------------------------------------------------------------------------------------------------------------------------
    Name of non-regulatory SIP      Applicable geographic       State
             revision                        area          submittal date             EPA approval date                    Additional explanation
--------------------------------------------------------------------------------------------------------------------------------------------------------

                                                                      * * * * * * *
8-Hour Ozone Maintenance Plan and   Juniata County.......        12/17/07  07/18/08 [Insert page number where the
 2002 Base-Year Inventory.                                                  document begins].
--------------------------------------------------------------------------------------------------------------------------------------------------------

* * * * *
[FR Doc. E8-16276 Filed 7-17-08; 8:45 am]

BILLING CODE 6560-50-P


[Federal Register Volume 84, Number 66 (Friday, April 5, 2019)]
[Notices]
[Page 13650]
[FR Doc No: 2019-06716]

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

DEPARTMENT OF ENERGY

Federal Energy Regulatory Commission

[Docket No. EL19-58-000]

PJM Interconnection, L.L.C.; Notice of Filing

    Take notice that on March 29, 2019, PJM Interconnection, L.L.C.
(PJM), pursuant to section 206 of the Federal Power Act (FPA), 16
U.S.C. 824e, filed proposed revisions to the Amended and Restated
Operating Agreement of PJM (Operating Agreement) to effectuate enhanced
price formation in PJM's reserve markets.
    Any person desiring to intervene or to protest this filing must
file in accordance with Rules 211 and 214 of the Commission's Rules of
Practice and Procedure (18 CFR 385.211, 385.214). Protests will be
considered by the Commission in determining the appropriate action to
be taken, but will not serve to make protestants parties to the
proceeding. Any person wishing to become a party must file a notice of
intervention or motion to intervene, as appropriate. Such notices,
motions, or protests must be filed on or before the comment date. On or
before the comment date, it is not necessary to serve motions to
intervene or protests on persons other than the Applicant.
    The Commission encourages electronic submission of protests and
interventions in lieu of paper using the ``eFiling'' link at http://www.ferc.gov. Persons unable to file electronically should submit an
original and 5 copies of the protest or intervention to the Federal
Energy Regulatory Commission, 888 First Street NE, Washington, DC
20426.
    This filing is accessible online at http://www.ferc.gov, using the
``eLibrary'' link and is available for review in the Commission's
Public Reference Room in Washington, DC. There is an ``eSubscription''
link on the website that enables subscribers to receive email
notification when a document is added to a subscribed docket(s). For
assistance with any FERC Online service, please email
[email protected], or call<PHONE_NUMBER> (toll free). For
TTY, call<PHONE_NUMBER>.
    Comment Date: 5:00 p.m. Eastern Time on May 15, 2019.

    Dated: April 1, 2019.
Kimberly D. Bose,
Secretary.
[FR Doc. 2019-06716 Filed 4-4-19; 8:45 am]
 BILLING CODE 6717-01-P


Paul_ R._ Noe@ omb. eop. gov 08/ 25/ 2003 04: 27 PM To: Bill Wehrum/ DC/ USEPA/ US@ EPA, Jeff Holmstead/ DC/ USEPA/ US@ EPA cc: Amy_ L._ Farrell@ omb. eop. gov, lee. otis@ hq. doe. gov Subject: Discussion of 20Percent Threshold Bill ( See attached file: NSRinsert20per. 1. doc)   As you requested, attached is language on the 20 percent threshold, for Section III( C) and in the Legal Basis. Please call to discuss. The easiest way to reach me is cell______________.

Attachment is in a separate docket entry.