Airworthiness Directives; The Boeing Company Airplanes, 61533-61537 [2019-24716]
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Federal Register / Vol. 84, No. 219 / Wednesday, November 13, 2019 / Rules and Regulations
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, New York ACO Branch,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(i) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
AD CF–2018–36, dated December 27, 2018,
for related information. This MCAI may be
found in the AD docket on the internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2019–0582.
(2) For more information about this AD,
contact Thomas Niczky, Aerospace Engineer,
Avionics and Electrical Systems Services
Section, FAA, New York ACO Branch, 1600
Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7347; fax 516–
794–5531; email 9-avs-nyaco-cos@faa.gov.
(j) 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.
(i) ‘‘Unreliable Airspeed Procedure,’’ from
Unreliable Airspeed, in the Emergency
Procedures section, of the Canadair
Challenger CL–600–1A11 Airplane Flight
Manual (AFM), RAG–600–101, Issue 2,
Product Publication 600, Revision A111,
dated August 31, 2018.
(ii) ‘‘Unreliable Airspeed Procedure,’’ from
Unreliable Airspeed, in the Emergency
Procedures section, of the Canadair
Challenger CL–600–1A11 (Winglets) AFM,
RAG–600–101, Issue 2, Product Support
Publication (PSP) 600–1, Revision 103, dated
August 31, 2018.
(iii) ‘‘Unreliable Airspeed Procedure,’’ from
Unreliable Airspeed, in the Emergency
Procedures section, of the Canadair
Challenger CL–600–2A12 AFM, PSP 601–1A,
Revision 120, dated August 31, 2018.
(iv) ‘‘Unreliable Airspeed Procedure,’’ from
Unreliable Airspeed, in the Emergency
Procedures section, of the Canadair
Challenger CL–600–2A12 AFM, PSP 601–
1A–1, Revision 79, dated August 31, 2018.
(v) ‘‘Unreliable Airspeed Procedure,’’ from
Unreliable Airspeed, in the Emergency
Procedures section, of the Canadair
Challenger CL–600–2A12 AFM, PSP 601–1B,
Revision 83, dated August 31, 2018.
(vi) ‘‘Unreliable Airspeed Procedure,’’ from
Unreliable Airspeed, in the Emergency
Procedures section, of the Canadair
Challenger CL–600–2A12 AFM, PSP 601–1B–
1, Revision 81, dated August 31, 2018.
(vii) ‘‘Unreliable Airspeed Procedure,’’
from Unreliable Airspeed, in the Emergency
Procedures section, of the Canadair
Challenger CL–600–2B16 AFM, PSP 601A–1,
Revision 103, dated August 31, 2018.
(viii) ‘‘Unreliable Airspeed Procedure,’’
from Unreliable Airspeed, in the Emergency
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Procedures section, of the Canadair
Challenger CL–600–2B16 AFM, PSP 601A–
1–1, Revision 92, dated August 31, 2018.
(3) For service information identified in
this AD, contact Bombardier, Inc., 200 CoˆteVertu Road West, Dorval, Que´bec H4S 2A3,
Canada; North America toll-free telephone
1–866–538–1247 or direct-dial telephone
1–514–855–2999; email ac.yul@
aero.bombardier.com; internet https://
www.bombardier.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 fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
October 18, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–24506 Filed 11–12–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0866; Product
Identifier 2019–NM–174–AD; Amendment
39–19789; AD 2019–22–10]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2019–20–
02, which applied to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series
airplanes. AD 2019–20–02 required
repetitive inspections for cracking of the
left- and right-hand side outboard
chords of frame fittings and failsafe
straps at a certain station around two
fasteners, and repair if any cracking is
found. This AD also requires repetitive
inspections for cracking of the left- and
right-hand side outboard chords of
frame fittings and failsafe straps at a
certain station, but expands the
inspection to the area around eight
fasteners, and also requires repair if any
cracking is found. This AD was
prompted by a determination that the
SUMMARY:
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61533
inspection area needs to be expanded.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective November
13, 2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 13, 2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of October 3, 2019 (84 FR
52754, October 3, 2019).
The FAA must receive any comments
on this AD by December 30, 2019.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this final rule, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110–SK57,
Seal Beach, CA 90740–5600; telephone
562–797–1717; 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–2019–0866.
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–
0866; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Greg
Rutar, Aerospace Engineer, Airframe
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Federal Register / Vol. 84, No. 219 / Wednesday, November 13, 2019 / Rules and Regulations
Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: 206–231–3529; email:
Greg.Rutar@faa.gov.
SUPPLEMENTARY INFORMATION:
repaired before the residual strength
capability falls below the minimum
residual strength required under Title
14 Code of Federal Regulations (14 CFR)
25.571.
Discussion
The FAA issued AD 2019–20–02,
Amendment 39–19755 (84 FR 52754,
October 3, 2019) (‘‘AD 2019–20–02’’),
for all The Boeing Company Model 737–
600, –700, –700C, –800, –900, and
–900ER series airplanes. AD 2019–20–
02 required repetitive inspections for
cracking of the left- and right-hand side
outboard chords of frame fittings and
failsafe straps at a certain station around
two fasteners, and repair if any cracking
is found. AD 2019–20–02 was prompted
by reports of cracking in this area found
on multiple Boeing Model 737–800
airplanes during a passenger-to-freighter
conversion. The FAA issued AD 2019–
20–02 to address this cracking, which
could result in failure of a Principal
Structural Element (PSE) to sustain limit
load. This condition could adversely
affect the structural integrity of the
airplane, and result in loss of control of
the airplane.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing MultiOperator Message MOM–MOM–19–
0623–01B, dated November 5, 2019.
This service information describes
procedures for repetitive detailed
inspections for cracking of the left- and
right-hand side outboard chords of the
station (STA) 663.75 frame fittings and
failsafe straps around eight fasteners
adjacent to the stringer S–18A straps.
This AD also requires Boeing MultiOperator Message MOM–MOM–19–
0536–01B, dated September 30, 2019,
which the Director of the Federal
Register approved for incorporation by
reference as of October 3, 2019 (84 FR
52754, October 3, 2019).
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.
Actions Since AD 2019–20–02 Was
Issued
Since AD 2019–20–02 was issued, the
FAA has reviewed inspection findings
submitted as required by paragraph (h)
of AD 2019–20–02. From these findings,
four airplanes have been identified to
have cracking outside the initial
inspection area. Based on these
findings, the FAA has determined that
the inspection area must be expanded
from the area around two fasteners to
the area around eight fasteners on both
the left- and right-hand sides (which
includes the area around the two
fasteners inspected as required by AD
2019–20–02) to adequately address the
unsafe condition.
The FAA has taken all inspection
findings into consideration in assessing
the merits of the existing regulatory
action. The findings support that the
initial inspection thresholds are
adequate to ensure fleet safety. All
airplane structure has an initial period
when fatigue cracking is not anticipated.
Beyond this period, structural safety can
be maintained with a damage-tolerant
design and inspection program. The
compliance times for the initial and
repetitive inspections as specified in
paragraph (g) of AD 2019–20–02 were
determined using standard damage
tolerance principles. Residual strength
is the load that damaged (cracked)
structure can still carry without failing.
Structure is damage-tolerant if damage
that may occur can be detected and
FAA’s Determination
The FAA is issuing this AD because
the agency evaluated all the relevant
information and determined the unsafe
condition described previously is likely
to exist or develop in other products of
the same type design.
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AD Requirements
This AD requires repetitive
inspections for cracking of the left- and
right-hand side outboard chords of the
STA 663.75 frame fittings and failsafe
straps around eight fasteners adjacent to
the stringer S–18A straps. This AD also
requires repair of all cracking using a
method approved by the FAA or The
Boeing Company Organization
Designation Authorization (ODA).
Accomplishing the initial inspection
required by paragraph (i) of this AD
terminates the inspections originally
required by AD 2019–20–02 and
retained in this AD. This AD also
requires sending a report of all results
of the initial inspections to Boeing.
Interim Action
The FAA considers this AD interim
action. The inspection reports that are
required by this AD will enable the
manufacturer to obtain better insight
into the nature, cause, and extent of the
cracking, and eventually to develop
final action to address the unsafe
condition. Once final action has been
identified, the FAA might consider
further rulemaking.
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Justification for Immediate Adoption
and Determination of the Effective Date
Section 553(b)(3)(B) of the
Administrative Procedure Act (APA) (5
U.S.C.) authorizes agencies to dispense
with notice and comment procedures
for rules when the agency, for ‘‘good
cause,’’ finds that those procedures are
‘‘impracticable, unnecessary, or contrary
to the public interest.’’ Under this
section, an agency, upon finding good
cause, may issue a final rule without
seeking comment prior to the
rulemaking. Similarly, Section 553(d) of
the APA authorizes agencies to make
rules effective in less than thirty days,
upon a finding of good cause.
An unsafe condition exists that
requires the immediate adoption of this
AD without providing an opportunity
for public comments prior to adoption.
The FAA has found that the risk to the
flying public justifies forgoing notice
and comment prior to adoption of this
rule because cracking in the STA 663.75
frame fitting outboard chords and
failsafe straps around eight fasteners
adjacent to the stringer S–18A straps
could result in failure of a PSE to
sustain limit load. This condition could
adversely affect the structural integrity
of the airplane and result in loss of
control of the airplane. The compliance
time for the required action is shorter
than the time necessary for the public to
comment and for publication of the final
rule.
Accordingly, notice and opportunity
for prior public comment are
impracticable and contrary to the public
interest pursuant to 5 U.S.C.
553(b)(3)(B). In addition, for the reasons
stated above, the FAA finds that good
cause exists pursuant to 5 U.S.C. 553(d)
for making this amendment effective in
less than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment.
However, the FAA invites you to send
any written data, views, or arguments
about this final rule. Send your
comments to an address listed under the
ADDRESSES section. Include the docket
number FAA–2019–0866 and Product
Identifier 2019–NM–174–AD at the
beginning of your comments. The FAA
specifically invites comments on the
overall regulatory, economic,
environmental, and energy aspects of
this final rule. The FAA will consider
all comments received by the closing
date and may amend this final rule
because of those comments.
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The FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact received about this final rule.
Regulatory Flexibility Act
The requirements of the Regulatory
Flexibility Act (RFA) do not apply when
an agency finds good cause pursuant to
5 U.S.C. 553 to adopt a rule without
prior notice and comment. Because the
FAA has determined that it has good
cause to adopt this rule without notice
61535
and comment, RFA analysis is not
required.
Costs of Compliance
The FAA estimates that this AD
affects 1,911 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS
Parts
cost
Cost per
product
Action
Labor cost
Inspection (retained action from AD
2019–20–02).
Reporting (retained action from AD
2019–20–02).
Inspection (new action) ...........................
1 work-hour × $85 per hour = $85 per
inspection cycle.
1 work-hour × $85 per hour = $85 ..........
$0
1 work-hour(s) × $85 per hour = $85 per
inspection cycle.
1 work-hour × $85 per hour = $85 ..........
0
Reporting (new action) ............................
The FAA has received no definitive
data that would enable the agency to
provide cost estimates for the oncondition actions specified in this AD.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to Information
Collection Clearance Officer, Federal
Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX
76177–1524.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701, ‘‘General requirements.’’ Under
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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
The FAA has determined that this AD
will not have federalism implications
under Executive Order 13132. This AD
will not have a substantial direct effect
on the States, on the relationship
between the national government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
and
(2) Will not affect intrastate aviation
in Alaska.
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0
0
Cost on U.S.
operators
$85 per inspection
cycle.
$85 ..........................
$162,435 per inspection cycle.
$162,435.
$85 per inspection
cycle.
$85 ..........................
$162,435 per inspection cycle.
$162,435.
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2019–20–02, Amendment 39–19755 (84
FR 52754, October 3, 2019), and adding
the following new AD:
■
2019–22–10 The Boeing Company:
Amendment 39–19789; Docket No.
FAA–2019–0866; Product Identifier
2019–NM–174–AD.
(a) Effective Date
This AD is effective November 13, 2019.
(b) Affected ADs
This AD replaces AD 2019–20–02,
Amendment 39–19755 (84 FR 52754, October
3, 2019) (‘‘AD 2019–20–02’’).
(c) Applicability
This AD applies to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
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(e) Unsafe Condition
This AD was prompted by reports of
cracking discovered in the left- and righthand side outboard chords of the station
(STA) 663.75 frame fittings and failsafe straps
adjacent to the stringer S–18A straps and a
determination that the area inspected by AD
2019–20–02 needs to be expanded. The FAA
is issuing this AD to address cracking in the
STA 663.75 frame fitting outboard chords
and failsafe straps adjacent to the stringer S–
18A straps, which could result in failure of
a Principal Structural Element (PSE) to
sustain limit load. This condition could
adversely affect the structural integrity of the
airplane and result in loss of control of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspection and Corrective
Action, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2019–20–02, with no
changes. At the earlier of the times specified
in paragraphs (g)(1) and (2) of this AD: Do a
detailed inspection for cracking of the leftand right-hand side outboard chords of the
STA 663.75 frame fittings and failsafe straps
adjacent to the stringer S–18A straps, in
accordance with Boeing Multi-Operator
Message MOM–MOM–19–0536–01B, dated
September 30, 2019. If any crack is found,
repair before further flight using a method
approved in accordance with the procedures
specified in paragraph (n) of this AD. Repeat
the inspection thereafter at intervals not to
exceed 3,500 flight cycles until the initial
inspection required by paragraph (i) of this
AD is done.
(1) Prior to the accumulation of 30,000
total flight cycles, or within 7 days after
October 3, 2019 (the effective date of AD
2019–20–02), whichever occurs later.
(2) Prior to the accumulation of 22,600
total flight cycles, or within 1,000 flight
cycles after October 3, 2019 (the effective
date of AD 2019–20–02), whichever occurs
later.
(h) Retained Reporting Requirement With
No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2019–20–02, with no
changes. At the applicable time specified in
paragraph (h)(1) or (2) of this AD, submit a
report of all findings, positive and negative,
of the initial inspection required by
paragraph (g) of this AD. Submit the report
in accordance with Boeing Multi-Operator
Message MOM–MOM–19–0536–01B, dated
September 30, 2019.
(1) If the inspection was done on or after
October 3, 3019 (the effective date of AD
2019–20–02): Submit the report within 3
days after the inspection.
(2) If the inspection was done before
October 3, 2019 (the effective date of AD
2019–20–02): Submit the report within 3
days after October 3, 2019.
(i) New Inspection and Corrective Action
Except as specified in paragraph (j) of this
AD: At the applicable initial compliance time
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15:58 Nov 12, 2019
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specified in Table 1 of ‘‘Ref F’’ of Boeing
Multi-Operator Message MOM–MOM–19–
0623–01B, dated November 5, 2019, do a
detailed inspection of the left- and right-hand
side outboard chords of the STA 663.75
frame fittings and failsafe straps around eight
fasteners adjacent to the stringer S–18A
straps, in accordance with Boeing MultiOperator Message MOM–MOM–19–0623–
01B, dated November 5, 2019. If any crack is
found, repair before further flight using a
method approved in accordance with the
procedures specified in paragraph (n) of this
AD. Repeat the inspection thereafter at the
intervals specified in Table 1 of ‘‘Ref F’’ of
Boeing Multi-Operator Message MOM–
MOM–19–0623–01B, dated November 5,
2019. Accomplishing the initial inspection
required by this paragraph terminates the
inspections required by paragraph (g) of this
AD.
(j) Exception to Service Information
Specifications
Where Table 1 of ‘‘Ref F’’ of Boeing MultiOperator Message MOM–MOM–19–0623–
01B, dated November 5, 2019, uses the
phrase ‘‘the original issue date of MOM–
MOM–19–0623–01B,’’ this AD requires using
‘‘the effective date of this AD.’’
(k) New Reporting Requirement
At the applicable time specified in
paragraph (k)(1) or (2) of this AD, submit a
report of all findings, positive and negative,
of the initial inspection required by
paragraph (i) of this AD. Submit the report
in accordance with Boeing Multi-Operator
Message MOM–MOM–19–0623–01B, dated
November 5, 2019.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 3 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 3 days after the effective date of this
AD.
(l) Special Flight Permit
Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
to operate the airplane to a location where
the airplane can be repaired if any crack is
found, provided the Manager, Seattle ACO
Branch, FAA, concurs with issuance of the
special flight permit. Send requests for
concurrence by email to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov.
(m) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 1 hour per
response, including the time for reviewing
instructions, searching existing data sources,
gathering and maintaining the data needed,
and completing and reviewing the collection
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of information. All responses to this
collection of information are mandatory as
required by this AD; the nature and extent of
confidentiality to be provided, if any. Send
comments regarding this burden estimate or
any other aspect of this collection of
information, including suggestions for
reducing this burden to Information
Collection Clearance Officer, Federal
Aviation Administration, 10101 Hillwood
Parkway, Fort Worth, TX 76177–1524.
(n) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or 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 (o) of this
AD. Information may be emailed to: 9-ANMSeattle-ACO-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, Seattle ACO Branch, FAA, to make
those findings. To be approved, the repair
method, modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously for AD
2019–20–02 are approved as AMOCs for the
corresponding provisions of this AD.
(o) Related Information
For more information about this AD,
contact Greg Rutar, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA
98198; phone and fax: 206–231–3529; email:
Greg.Rutar@faa.gov.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on November 13, 2019.
(i) Boeing Multi-Operator Message MOM–
MOM–19–0623–01B, dated November 5,
2019.
(ii) [Reserved]
(4) The following service information was
approved for IBR on October 3, 2019 (84 FR
52754, October 3, 2019).
(i) Boeing Multi-Operator Message MOM–
MOM–19–0536–01B, dated September 30,
2019.
(ii) [Reserved]
E:\FR\FM\13NOR1.SGM
13NOR1
Federal Register / Vol. 84, No. 219 / Wednesday, November 13, 2019 / Rules and Regulations
(5) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com.
(6) 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email fedreg.legal@nara.gov, or go to https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
[Docket No. FAA–2018–0686; Airspace
Docket No. 18–ANM–10]
Effective 0901 UTC, January 30,
2020. The Director of the Federal
Register approves this incorporation by
reference action under Title 1 Code of
Federal Regulations part 51, subject to
the annual revision of FAA Order
7400.11 and publication of conforming
amendments.
ADDRESSES: FAA Order 7400.11D,
Airspace Designations and Reporting
Points, and subsequent amendments can
be viewed on line at https://
www.faa.gov/air_traffic/publications/.
For further information, you can contact
the Airspace Policy Group, Federal
Aviation Administration, 800
Independence Avenue SW, Washington,
DC, 20591 telephone: (202) 267–8783.
The Order is also available for
inspection at the National Archives and
Records Administration (NARA). For
information on the availability of FAA
Order 7400.11C at NARA, email
fedreg.legal@nara.gov or go to https://
www.archives.gov/federal-register/cfr/
ibr-locations.html.
FOR FURTHER INFORMATION CONTACT:
Richard Roberts, Federal Aviation
Administration, Western Service Center,
Operations Support Group, 2200 S
216th Street, Des Moines, WA 98198;
telephone (206) 231–2245.
SUPPLEMENTARY INFORMATION:
RIN 2120–AA66
Authority for This Rulemaking
Issued in Des Moines, Washington, on
November 7, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–24716 Filed 11–12–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
Amendment of Class D and Class E
Airspace, and Establishment of Class
E Airspace; Spokane, WA
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action modifies Class D
airspace, Class E surface area airspace,
and establishes Class E airspace
extending upward from 700 feet above
the surface at Felts Field Airport,
Spokane, WA. After a biennial review,
the FAA found it necessary to amend
existing airspace and establish new
controlled airspace for the safety and
management of Instrument Flight Rules
(IFR) operations at this airport. This
action makes a minor editorial change to
the airspace designation and replaces
the outdated term Airport/Facility
Directory with the term Chart
Supplement. The Class D and Class E
surface areas are extended to the
Spokane International Airport Class C
surface area on the southwest and
expanded 1.2 miles on the northeast.
The Class E airspace extending upward
from 700 feet above the surface is
established to provide airspace for
aircraft transitioning to and from Felts
Field airport.
SUMMARY:
VerDate Sep<11>2014
15:58 Nov 12, 2019
Jkt 250001
DATES:
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it amends
Class D and Class E surface area
airspace and establishes Class E airspace
extending upward from 700 feet above
the earth at Felts Field, Spokane, WA,
to support IFR operations at the airport.
History
The FAA published a notice of
proposed rulemaking in the Federal
Register (84 FR 29431; June 24, 2019)
for Docket No. FAA–2018–0686 to
modify Class D airspace and Class E
surface area airspace and establish Class
E airspace extending upward from 700
feet above the surface at Felts Field
Airport, Spokane, WA. Interested
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
61537
parties were invited to participate in
this rulemaking effort by submitting
written comments on the proposal to the
FAA. No comments were received.
Class D and Class E airspace
designations are published in paragraph
5000, 6002, and 6005, respectively, of
FAA Order 7400.11D, dated August 8,
2019 and effective September 15, 2019,
which is incorporated by reference in 14
CFR 71.1. The Class D and Class E
airspace designations listed in this
document will be published
subsequently in that Order. FAA Order
7400.11, Airspace Designations and
Reporting Points, is published yearly
and effective on September 15.
Availability and Summary of
Documents for Incorporation by
Reference
This document amends FAA Order
7400.11D, Airspace Designations and
Reporting Points, dated August 8, 2019,
and effective September 15, 2019. FAA
Order 7400.11D is publicly available as
listed in the ADDRESSES section of this
document. FAA Order 7400.11D lists
Class A, B, C, D, and E airspace areas,
air traffic service routes, and reporting
points.
The Rule
The FAA is amending Title 14 Code
of Federal Regulations (14 CFR) part 71
by modifying Class D airspace, and
Class E surface area airspace at Felts
Field Airport, Spokane, WA, by
expanding an area that will extend to
the Spokane International Airport Class
C surface area on the southwest and
expanded 1.2 miles on the northeast;
and Establishing Class E airspace
extending upward from 700 feet above
the surface within a 4-mile radius of
Felts Field Airport, Spokane, WA, and
within 1.8 miles each side of the 53°
bearing from the airport extending from
the 4-mile radius to 6.5 miles from the
airport, and within 3.0 miles each side
of the 75° bearing from the point in
space at (lat. 47°37′46″ N, long.
117°26′30″ W), extending 12.6 miles
from the point in space coordinates.
After a biennial review of the airspace,
the FAA found modification of the
airspace necessary for the safety and
management of aircraft departing and
arriving under IFR operations at the
airport.
Regulatory Notices and Analyses
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current, is non-controversial and
unlikely to result in adverse or negative
E:\FR\FM\13NOR1.SGM
13NOR1
]]>Agencies
[Federal Register Volume 84, Number 219 (Wednesday, November 13, 2019)]
[Rules and Regulations]
[Pages 61533-61537]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-24716]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0866; Product Identifier 2019-NM-174-AD; Amendment
39-19789; AD 2019-22-10]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-20-
02, which applied to all The Boeing Company Model 737-600, -700, -700C,
-800, -900, and -900ER series airplanes. AD 2019-20-02 required
repetitive inspections for cracking of the left- and right-hand side
outboard chords of frame fittings and failsafe straps at a certain
station around two fasteners, and repair if any cracking is found. This
AD also requires repetitive inspections for cracking of the left- and
right-hand side outboard chords of frame fittings and failsafe straps
at a certain station, but expands the inspection to the area around
eight fasteners, and also requires repair if any cracking is found.
This AD was prompted by a determination that the inspection area needs
to be expanded. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November 13, 2019.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 13,
2019.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
October 3, 2019 (84 FR 52754, October 3, 2019).
The FAA must receive any comments on this AD by December 30, 2019.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this final rule, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600;
telephone 562-797-1717; 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-2019-0866.
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-
0866; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The street address for Docket Operations is listed
above. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Greg Rutar, Aerospace Engineer,
Airframe
[[Page 61534]]
Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA
98198; phone and fax: 206-231-3529; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued AD 2019-20-02, Amendment 39-19755 (84 FR 52754,
October 3, 2019) (``AD 2019-20-02''), for all The Boeing Company Model
737-600, -700, -700C, -800, -900, and -900ER series airplanes. AD 2019-
20-02 required repetitive inspections for cracking of the left- and
right-hand side outboard chords of frame fittings and failsafe straps
at a certain station around two fasteners, and repair if any cracking
is found. AD 2019-20-02 was prompted by reports of cracking in this
area found on multiple Boeing Model 737-800 airplanes during a
passenger-to-freighter conversion. The FAA issued AD 2019-20-02 to
address this cracking, which could result in failure of a Principal
Structural Element (PSE) to sustain limit load. This condition could
adversely affect the structural integrity of the airplane, and result
in loss of control of the airplane.
Actions Since AD 2019-20-02 Was Issued
Since AD 2019-20-02 was issued, the FAA has reviewed inspection
findings submitted as required by paragraph (h) of AD 2019-20-02. From
these findings, four airplanes have been identified to have cracking
outside the initial inspection area. Based on these findings, the FAA
has determined that the inspection area must be expanded from the area
around two fasteners to the area around eight fasteners on both the
left- and right-hand sides (which includes the area around the two
fasteners inspected as required by AD 2019-20-02) to adequately address
the unsafe condition.
The FAA has taken all inspection findings into consideration in
assessing the merits of the existing regulatory action. The findings
support that the initial inspection thresholds are adequate to ensure
fleet safety. All airplane structure has an initial period when fatigue
cracking is not anticipated. Beyond this period, structural safety can
be maintained with a damage-tolerant design and inspection program. The
compliance times for the initial and repetitive inspections as
specified in paragraph (g) of AD 2019-20-02 were determined using
standard damage tolerance principles. Residual strength is the load
that damaged (cracked) structure can still carry without failing.
Structure is damage-tolerant if damage that may occur can be detected
and repaired before the residual strength capability falls below the
minimum residual strength required under Title 14 Code of Federal
Regulations (14 CFR) 25.571.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Multi-Operator Message MOM-MOM-19-0623-01B,
dated November 5, 2019. This service information describes procedures
for repetitive detailed inspections for cracking of the left- and
right-hand side outboard chords of the station (STA) 663.75 frame
fittings and failsafe straps around eight fasteners adjacent to the
stringer S-18A straps.
This AD also requires Boeing Multi-Operator Message MOM-MOM-19-
0536-01B, dated September 30, 2019, which the Director of the Federal
Register approved for incorporation by reference as of October 3, 2019
(84 FR 52754, October 3, 2019).
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination
The FAA is issuing this AD because the agency evaluated all the
relevant information and determined the unsafe condition described
previously is likely to exist or develop in other products of the same
type design.
AD Requirements
This AD requires repetitive inspections for cracking of the left-
and right-hand side outboard chords of the STA 663.75 frame fittings
and failsafe straps around eight fasteners adjacent to the stringer S-
18A straps. This AD also requires repair of all cracking using a method
approved by the FAA or The Boeing Company Organization Designation
Authorization (ODA). Accomplishing the initial inspection required by
paragraph (i) of this AD terminates the inspections originally required
by AD 2019-20-02 and retained in this AD. This AD also requires sending
a report of all results of the initial inspections to Boeing.
Interim Action
The FAA considers this AD interim action. The inspection reports
that are required by this AD will enable the manufacturer to obtain
better insight into the nature, cause, and extent of the cracking, and
eventually to develop final action to address the unsafe condition.
Once final action has been identified, the FAA might consider further
rulemaking.
Justification for Immediate Adoption and Determination of the Effective
Date
Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5
U.S.C.) authorizes agencies to dispense with notice and comment
procedures for rules when the agency, for ``good cause,'' finds that
those procedures are ``impracticable, unnecessary, or contrary to the
public interest.'' Under this section, an agency, upon finding good
cause, may issue a final rule without seeking comment prior to the
rulemaking. Similarly, Section 553(d) of the APA authorizes agencies to
make rules effective in less than thirty days, upon a finding of good
cause.
An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies forgoing notice and comment prior to adoption of this rule
because cracking in the STA 663.75 frame fitting outboard chords and
failsafe straps around eight fasteners adjacent to the stringer S-18A
straps could result in failure of a PSE to sustain limit load. This
condition could adversely affect the structural integrity of the
airplane and result in loss of control of the airplane. The compliance
time for the required action is shorter than the time necessary for the
public to comment and for publication of the final rule.
Accordingly, notice and opportunity for prior public comment are
impracticable and contrary to the public interest pursuant to 5 U.S.C.
553(b)(3)(B). In addition, for the reasons stated above, the FAA finds
that good cause exists pursuant to 5 U.S.C. 553(d) for making this
amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, the FAA invites you to send any written data, views,
or arguments about this final rule. Send your comments to an address
listed under the ADDRESSES section. Include the docket number FAA-2019-
0866 and Product Identifier 2019-NM-174-AD at the beginning of your
comments. The FAA specifically invites comments on the overall
regulatory, economic, environmental, and energy aspects of this final
rule. The FAA will consider all comments received by the closing date
and may amend this final rule because of those comments.
[[Page 61535]]
The FAA will post all comments received, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this final rule.
Regulatory Flexibility Act
The requirements of the Regulatory Flexibility Act (RFA) do not
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt
a rule without prior notice and comment. Because the FAA has determined
that it has good cause to adopt this rule without notice and comment,
RFA analysis is not required.
Costs of Compliance
The FAA estimates that this AD affects 1,911 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection (retained action from 1 work-hour x $85 $0 $85 per inspection $162,435 per
AD 2019-20-02). per hour = $85 per cycle. inspection cycle.
inspection cycle.
Reporting (retained action from 1 work-hour x $85 0 $85................. $162,435.
AD 2019-20-02). per hour = $85.
Inspection (new action).......... 1 work-hour(s) x $85 0 $85 per inspection $162,435 per
per hour = $85 per cycle. inspection cycle.
inspection cycle.
Reporting (new action)........... 1 work-hour x $85 0 $85................. $162,435.
per hour = $85.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition actions specified
in this AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to
Information Collection Clearance Officer, Federal Aviation
Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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
The FAA has determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866, and
(2) Will not affect intrastate aviation in Alaska.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2019-20-02, Amendment 39-19755 (84 FR 52754, October 3, 2019), and
adding the following new AD:
2019-22-10 The Boeing Company: Amendment 39-19789; Docket No. FAA-
2019-0866; Product Identifier 2019-NM-174-AD.
(a) Effective Date
This AD is effective November 13, 2019.
(b) Affected ADs
This AD replaces AD 2019-20-02, Amendment 39-19755 (84 FR 52754,
October 3, 2019) (``AD 2019-20-02'').
(c) Applicability
This AD applies to all The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
[[Page 61536]]
(e) Unsafe Condition
This AD was prompted by reports of cracking discovered in the
left- and right-hand side outboard chords of the station (STA)
663.75 frame fittings and failsafe straps adjacent to the stringer
S-18A straps and a determination that the area inspected by AD 2019-
20-02 needs to be expanded. The FAA is issuing this AD to address
cracking in the STA 663.75 frame fitting outboard chords and
failsafe straps adjacent to the stringer S-18A straps, which could
result in failure of a Principal Structural Element (PSE) to sustain
limit load. This condition could adversely affect the structural
integrity of the airplane and result in loss of control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspection and Corrective Action, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2019-20-02, with no changes. At the earlier of the times specified
in paragraphs (g)(1) and (2) of this AD: Do a detailed inspection
for cracking of the left- and right-hand side outboard chords of the
STA 663.75 frame fittings and failsafe straps adjacent to the
stringer S-18A straps, in accordance with Boeing Multi-Operator
Message MOM-MOM-19-0536-01B, dated September 30, 2019. If any crack
is found, repair before further flight using a method approved in
accordance with the procedures specified in paragraph (n) of this
AD. Repeat the inspection thereafter at intervals not to exceed
3,500 flight cycles until the initial inspection required by
paragraph (i) of this AD is done.
(1) Prior to the accumulation of 30,000 total flight cycles, or
within 7 days after October 3, 2019 (the effective date of AD 2019-
20-02), whichever occurs later.
(2) Prior to the accumulation of 22,600 total flight cycles, or
within 1,000 flight cycles after October 3, 2019 (the effective date
of AD 2019-20-02), whichever occurs later.
(h) Retained Reporting Requirement With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2019-20-02, with no changes. At the applicable time specified in
paragraph (h)(1) or (2) of this AD, submit a report of all findings,
positive and negative, of the initial inspection required by
paragraph (g) of this AD. Submit the report in accordance with
Boeing Multi-Operator Message MOM-MOM-19-0536-01B, dated September
30, 2019.
(1) If the inspection was done on or after October 3, 3019 (the
effective date of AD 2019-20-02): Submit the report within 3 days
after the inspection.
(2) If the inspection was done before October 3, 2019 (the
effective date of AD 2019-20-02): Submit the report within 3 days
after October 3, 2019.
(i) New Inspection and Corrective Action
Except as specified in paragraph (j) of this AD: At the
applicable initial compliance time specified in Table 1 of ``Ref F''
of Boeing Multi-Operator Message MOM-MOM-19-0623-01B, dated November
5, 2019, do a detailed inspection of the left- and right-hand side
outboard chords of the STA 663.75 frame fittings and failsafe straps
around eight fasteners adjacent to the stringer S-18A straps, in
accordance with Boeing Multi-Operator Message MOM-MOM-19-0623-01B,
dated November 5, 2019. If any crack is found, repair before further
flight using a method approved in accordance with the procedures
specified in paragraph (n) of this AD. Repeat the inspection
thereafter at the intervals specified in Table 1 of ``Ref F'' of
Boeing Multi-Operator Message MOM-MOM-19-0623-01B, dated November 5,
2019. Accomplishing the initial inspection required by this
paragraph terminates the inspections required by paragraph (g) of
this AD.
(j) Exception to Service Information Specifications
Where Table 1 of ``Ref F'' of Boeing Multi-Operator Message MOM-
MOM-19-0623-01B, dated November 5, 2019, uses the phrase ``the
original issue date of MOM-MOM-19-0623-01B,'' this AD requires using
``the effective date of this AD.''
(k) New Reporting Requirement
At the applicable time specified in paragraph (k)(1) or (2) of
this AD, submit a report of all findings, positive and negative, of
the initial inspection required by paragraph (i) of this AD. Submit
the report in accordance with Boeing Multi-Operator Message MOM-MOM-
19-0623-01B, dated November 5, 2019.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 3 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 3 days after the effective date of this
AD.
(l) Special Flight Permit
Special flight permits may be issued in accordance with 14 CFR
21.197 and 21.199 to operate the airplane to a location where the
airplane can be repaired if any crack is found, provided the
Manager, Seattle ACO Branch, FAA, concurs with issuance of the
special flight permit. Send requests for concurrence by email to [email protected].
(m) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 1 hour per response, including the
time for reviewing instructions, searching existing data sources,
gathering and maintaining the data needed, and completing and
reviewing the collection of information. All responses to this
collection of information are mandatory as required by this AD; the
nature and extent of confidentiality to be provided, if any. Send
comments regarding this burden estimate or any other aspect of this
collection of information, including suggestions for reducing this
burden to Information Collection Clearance Officer, Federal Aviation
Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524.
(n) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or 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 (o) of this AD. Information may be
emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the 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, Seattle
ACO Branch, FAA, to make those findings. To be approved, the repair
method, modification deviation, or alteration deviation must meet
the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously for AD 2019-20-02 are approved as
AMOCs for the corresponding provisions of this AD.
(o) Related Information
For more information about this AD, contact Greg Rutar,
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198; phone and fax: 206-231-3529;
email: [email protected].
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
November 13, 2019.
(i) Boeing Multi-Operator Message MOM-MOM-19-0623-01B, dated
November 5, 2019.
(ii) [Reserved]
(4) The following service information was approved for IBR on
October 3, 2019 (84 FR 52754, October 3, 2019).
(i) Boeing Multi-Operator Message MOM-MOM-19-0536-01B, dated
September 30, 2019.
(ii) [Reserved]
[[Page 61537]]
(5) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com.
(6) 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.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on November 7, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-24716 Filed 11-12-19; 8:45 am]
BILLING CODE 4910-13-P
