Airworthiness Directives; The Boeing Company Airplanes, 2624-2627 [2020-00580]
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Federal Register / Vol. 85, No. 11 / Thursday, January 16, 2020 / Rules and Regulations
of fluctuations in activity volumes, bad
debt, carrier insolvency, or other
unforeseen events.’’) This explanation
in that 2004 rulemaking makes clear
that, of the three items the cost of which
user fees should cover, APHIS was
justifying its inclusion ‘‘of a reservebuilding component’’ directly on the
third—‘‘[a]dministering the user fee
program.’’ As noted previously in the
Interpretive Rule and in this document,
this rationale effectively relies on
subsection 136a(a)(1)(B) of the FACT
Act as a basis for the reserve.
The 2004 rulemaking also aligned
administering the program with
ensuring continuity of AQI services by
indicating that one of the ways in which
APHIS administers the program is by
maintaining sufficient funds in reserve
to ensure continuity of AQI services
within the program. As noted
previously in the Interpretive Rule and
in this document, this rationale
effectively relies on subsection
136a(a)(1)(A) of the FACT Act as
another basis for the reserve.
In the 2006 final rule that responded
to comments on the 2004 rulemaking,
we again aligned administering the
program with maintaining sufficient
funds in reserve to ensure continuity of
AQI services. See 71 FR 49985.
APHIS’ 2014 proposed rule to revise
the AQI user fee schedule again aligned
administration of the user fee program
with maintaining sufficient funds to
provide AQI services. See 79 FR 22896.
Comment Requesting Assistance for
Domestic Programs
One commenter asked that APHIS
fund domestic control and eradication
programs undertaken by State
cooperators using AQI user fees.
The FACT Act prohibits such
subsidization.
Congressional Review Act
Pursuant to the Congressional Review
Act (5 U.S.C. 801 et seq.), the Office of
Information and Regulatory Affairs
designated this action as not a major
rule, as defined by 5 U.S.C. 804(2).
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Authority: 7 U.S.C. 7701–7772, 7781–
7786, and 8301–8317; 21 U.S.C. 136 and
136a; 49 U.S.C. 80503; 7 CFR 2.22, 2.80, and
371.3.
Done in Washington, DC, this 13th day of
January 2020.
Kevin Shea,
Administrator, Animal and Plant Health
Inspection Service.
[FR Doc. 2020–00659 Filed 1–15–20; 8:45 am]
BILLING CODE 3410–34–P
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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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
The FAA is correcting an
airworthiness directive (AD) that
published in the Federal Register. That
AD applies to all The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. As
published, the service information
reference specified in a certain
paragraph of the regulatory text is
incorrect. This document corrects that
error. In all other respects, the original
document remains the same.
DATES: This correction 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 (84 FR 68326,
December 16, 2019).
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: 562–797–1717; internet: https://
www.myboeingfleet.com. You may view
this referenced 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.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for
Docket Operations is Docket
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
PO 00000
Frm 00004
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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: 562–627–5254; fax: 562–627–
5210; email: serj.harutunian@faa.gov.
SUPPLEMENTARY INFORMATION: As
published, AD 2019–23–14,
Amendment 39–19808 (84 FR 68326,
December 16, 2019), requires revising
the existing maintenance or inspection
program, as applicable, to include new
or revised airworthiness limitations
(AWLs) for all The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes.
Need for the Correction
As published, the service information
reference specified in the paragraph
(g)(2)(ix) of the regulatory text is
incorrect. Paragraph (g)(2)(ix) of the
regulatory text incorrectly references the
actions specified in Boeing Service
Bulletin 737–28A1228 for the initial
compliance time to accomplish AWL
No. 28–AWL–31, ‘‘Cushion Clamps and
Teflon Sleeving Installed on Out-ofTank Wire Bundles Installed on
Brackets that are Mounted Directly on
the Fuel Tanks,’’ however, the correct
reference for that initial compliance
time is Boeing Service Bulletin 737–
57A1321. Boeing Service Bulletin 737–
28A1228 does not refer to AWL No. 28–
AWL–31. AWL No. 28–AWL–31 is only
referenced in Boeing Service Bulletin
737–57A1321.
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.
Correction of Publication
This document corrects an error and
correctly adds the AD as an amendment
to 14 CFR 39.13. Although no other part
of the preamble or regulatory
information has been corrected, the
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Federal Register / Vol. 85, No. 11 / Thursday, January 16, 2020 / Rules and Regulations
FAA is publishing the entire rule in the
Federal Register.
The effective date of this AD remains
January 21, 2020.
Since this action only corrects a
reference, it has no adverse economic
impact and imposes no additional
burden on any person. Therefore, the
FAA has determined that notice and
public comment procedures are
unnecessary.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Correction
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Corrected]
2. The FAA amends § 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.
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(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,
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(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.
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration amends part 39 of the
Federal Aviation Regulations (14 CFR
part 39) as follows:
§ 39.13
–300, –400, and –500 series airplanes,
certificated in any category.
(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, ‘‘OverCurrent and Arcing Protection Electrical
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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.
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(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, ‘‘OverCurrent 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 Outof-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 737–57A1321.
(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
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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.
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(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: 9-ANMLAACO-AMOC-Requests@faa.gov.
(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: 562–627–5210; email:
serj.harutunian@faa.gov.
(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 this AD specifies otherwise.
(3) The following service information was
approved for IBR on January 21, 2020 (84 FR
68326, December 16, 2019).
(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]
(4) 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: 562–797–1717; internet: https://
www.myboeingfleet.com.
(5) 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.
(6) You may view this service information
that is incorporated by reference at the
National Archives and Records
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Federal Register / Vol. 85, No. 11 / Thursday, January 16, 2020 / Rules and Regulations
Administration (NARA). For information on
the availability of this material at NARA,
email fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on January 9, 2020.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2020–00580 Filed 1–15–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0609; Product
Identifier 2019–NM–054–AD; Amendment
39–21018; AD 2019–25–19]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus SAS Model A350–941 airplanes.
This AD was prompted by a report of
dislodged passenger door girt bars. This
AD requires modification of the girt bar
retention mechanism of the affected
doors, as specified in a European Union
Aviation Safety Agency (EASA) AD,
which is incorporated by reference. The
FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective February 20,
2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of February 20, 2020.
ADDRESSES: For the material
incorporated by reference (IBR) in this
AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 89990
1000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this IBR material on the EASA
website at https://ad.easa.europa.eu.
You may view this IBR material 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 in the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0609.
khammond on DSKJM1Z7X2PROD with RULES
VerDate Sep<11>2014
16:46 Jan 15, 2020
Jkt 250001
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0609; 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:
Kathleen Arrigotti, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218.
SUPPLEMENTARY INFORMATION:
Discussion
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY:
Examining the AD Docket
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2019–0076, dated March 29, 2019
(‘‘EASA AD 2019–0076’’) (also referred
to as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus SAS Model A350–941
airplanes.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus SAS Model A350–
941 airplanes. The NPRM published in
the Federal Register on August 26, 2019
(84 FR 44563). The NPRM was
prompted by a report of dislodged
passenger door girt bars. The NPRM
proposed to require modification of the
girt bar retention mechanism of the
affected door.
The FAA is issuing this AD to address
dislodged girt bars, which could result
in functional loss of the affected door
slide and possibly prevent safe
evacuation during an emergency. See
the MCAI for additional background
information.
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.
Supportive Comments
One anonymous commenter stated
support for the NPRM. Delta Airlines
also agreed with the intent of the NPRM
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
2627
and submitted a request as described
below.
Request for Correction of Certain Serial
Numbers
Delta Airlines requested that the FAA
include a correction to certain serial
numbers listed in the appendixes of
Airbus service information referenced
by EASA AD 2019–0076. Delta Airlines
stated that certain door serial numbers
were duplicated for certain airplanes
across the different appendixes and after
sending a request for clarification,
Airbus confirmed to Delta Airlines that
those repeated numbers were
typographical errors.
The FAA agrees to revise this AD to
include the correct serial numbers. For
airplanes having manufacturer serial
numbers 0062 and 0119, the appendixes
of Airbus service information referenced
by EASA AD 2019–0076 identify the
correct part numbers for the doors, but
not the correct associated serial
numbers. Those two airplanes, with
manufacturer serial number (MSN) 0062
and 0119, are not on the U.S. registry.
The FAA has added paragraphs (h)(3)
and (h)(4) to this AD to specify the
correct serial numbers.
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 IBR Material Under 1 CFR Part
51
EASA AD 2019–0076 describes
procedures for modification of the girt
bar retention mechanism of the affected
doors. This material 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 12 airplanes of U.S. registry. The
FAA estimates the following costs to
comply with this AD:
E:\FR\FM\16JAR1.SGM
16JAR1
]]>Agencies
[Federal Register Volume 85, Number 11 (Thursday, January 16, 2020)]
[Rules and Regulations]
[Pages 2624-2627]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-00580]
=======================================================================
-----------------------------------------------------------------------
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; correction.
-----------------------------------------------------------------------
SUMMARY: The FAA is correcting an airworthiness directive (AD) that
published in the Federal Register. That AD applies to all The Boeing
Company Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. As published, the service information reference specified in
a certain paragraph of the regulatory text is incorrect. This document
corrects that error. In all other respects, the original document
remains the same.
DATES: This correction 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 (84 FR 68326, December 16, 2019).
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: 562-797-1717; internet: https://www.myboeingfleet.com. You may view this referenced 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; 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 AD, the regulatory evaluation,
any comments received, and other information. The address for Docket
Operations is Docket Management Facility, 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: 562-627-5254; fax: 562-627-
5210; email: [email protected].
SUPPLEMENTARY INFORMATION: As published, AD 2019-23-14, Amendment 39-
19808 (84 FR 68326, December 16, 2019), requires revising the existing
maintenance or inspection program, as applicable, to include new or
revised airworthiness limitations (AWLs) for all The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes.
Need for the Correction
As published, the service information reference specified in the
paragraph (g)(2)(ix) of the regulatory text is incorrect. Paragraph
(g)(2)(ix) of the regulatory text incorrectly references the actions
specified in Boeing Service Bulletin 737-28A1228 for the initial
compliance time to accomplish 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,'' however, the
correct reference for that initial compliance time is Boeing Service
Bulletin 737-57A1321. Boeing Service Bulletin 737-28A1228 does not
refer to AWL No. 28-AWL-31. AWL No. 28-AWL-31 is only referenced in
Boeing Service Bulletin 737-57A1321.
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.
Correction of Publication
This document corrects an error and correctly adds the AD as an
amendment to 14 CFR 39.13. Although no other part of the preamble or
regulatory information has been corrected, the
[[Page 2625]]
FAA is publishing the entire rule in the Federal Register.
The effective date of this AD remains January 21, 2020.
Since this action only corrects a reference, it has no adverse
economic impact and imposes no additional burden on any person.
Therefore, the FAA has determined that notice and public comment
procedures are unnecessary.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Correction
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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 [Corrected]
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.
[[Page 2626]]
(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
737-57A1321.
(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 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.
(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: 562-627-5210; email: [email protected].
(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 this AD specifies otherwise.
(3) The following service information was approved for IBR on
January 21, 2020 (84 FR 68326, December 16, 2019).
(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]
(4) 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: 562-797-1717; internet: https://www.myboeingfleet.com.
(5) 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.
(6) You may view this service information that is incorporated
by reference at the National Archives and Records
[[Page 2627]]
Administration (NARA). For information on the availability of this
material at NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on January 9, 2020.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2020-00580 Filed 1-15-20; 8:45 am]
BILLING CODE 4910-13-P
