Airworthiness Directives; The Boeing Company Airplanes, 23595-23599 [2021-08849]
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Federal Register / Vol. 86, No. 84 / Tuesday, May 4, 2021 / Rules and Regulations
AD 2020–0214 within 90 days after the
effective date of this AD.
(3) The initial compliance time for doing
the tasks specified in paragraph (3) of EASA
AD 2020–0214 is at the applicable
‘‘associated thresholds’’ specified in
paragraph (3) of EASA AD 2020–0214, or
within 90 days after the effective date of this
AD, whichever occurs later.
(4) The provisions specified in paragraphs
(4) and (5) of EASA AD 2019–0257 do not
apply to this AD.
(5) The ‘‘Remarks’’ section of EASA AD
2020–0214 does not apply to this AD.
(l) New Provisions for Alternative Actions,
Intervals, and CDCCLs
After the maintenance or inspection
program has been revised as required by
paragraph (j) of this AD, no alternative
actions (e.g., inspections), intervals, or
CDCCLs are allowed except as specified in
the provisions of the ‘‘Ref. Publications’’
section of EASA AD 2020–0214.
(m) Terminating Action for Certain
Requirements in AD 2014–16–23
Accomplishing the actions required by
paragraphs (g) or (j) of this AD terminates the
requirements of paragraph (q) of AD 2014–
16–23.
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(n) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, International Validation 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 Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (o) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(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, Large Aircraft Section,
International Validation Branch, FAA; or
EASA; or Dassault Aviation’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(o) Related Information
For more information about this AD,
contact Tom Rodriguez, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3226; email tom.rodriguez@
faa.gov.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
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(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 June 8, 2021.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0214, dated October 6,
2020.
(ii) [Reserved]
(4) The following service information was
approved for IBR on May 18, 2020 (85 FR
20405, April 13, 2020).
(i) European Union Aviation Safety Agency
(EASA) AD 2019–0257, dated October 17,
2019.
(ii) [Reserved]
(5) For EASA AD 2020–0214, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(6) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195. This material may be found
in the AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2020–1169.
(7) You may view this material 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/ibr-locations.html.
Issued on April 21, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–08852 Filed 5–3–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0789; Project
Identifier AD–2020–00849–T; Amendment
39–21519; AD 2021–09–06]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2019–22–
10, which applied to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series
SUMMARY:
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23595
airplanes. AD 2019–22–10 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 eight
fasteners, and repair if any cracking is
found. For certain airplanes, this AD
reduces the compliance time for the
initial inspection, and for all airplanes
this AD reduces the repetitive interval.
This AD was prompted by a
determination that the initial inspection
threshold and repetitive inspection
interval are inadequate to address the
cracking in a timely manner. The FAA
is issuing this AD to address the unsafe
condition on these products.
This AD is effective June 8, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 8, 2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 13, 2019 (84 FR
61533, 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).
DATES:
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, Airworthiness Products Section,
Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0789.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.govby searching for
and locating Docket No. FAA–2020–
0789; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
any comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
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Federal Register / Vol. 86, No. 84 / Tuesday, May 4, 2021 / Rules and Regulations
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.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2019–22–10,
Amendment 39–19789 (84 FR 61533,
November 13, 2019) (AD 2019–22–10).
AD 2019–22–10 applied to all The
Boeing Company Model 737–600, –700,
–700C, –800, –900, and –900ER series
airplanes. The NPRM published in the
Federal Register on September 8, 2020
(85 FR 55391). The NPRM was
prompted by an engineering analysis of
the inspection reporting results and
metallurgical evaluation of the
submitted frame fitting assemblies,
which indicated that the initial
inspection threshold for Model 737–
900ER series airplanes and the
repetitive inspection interval for all
affected airplanes are inadequate to
address the cracking in a timely manner.
For certain airplanes, the NPRM
proposed to reduce the compliance time
for the initial inspection, and for all
airplanes the NPRM proposed to reduce
the repetitive inspection interval.
Comments
The FAA gave the public the
opportunity to participate in developing
this AD. The following presents the
comments received on the NPRM and
the FAA’s response to each comment.
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Request To Extend the Compliance
Time for the Reporting Requirement
American Airlines (AA) asked that the
compliance time for the reporting
requirements in paragraphs (h) and (k)
of the proposed AD be extended to 30
days after the date of inspection. AA
stated that the cracking of the station
(STA) 663.75 fitting is now a known
problem, and Boeing has been receiving
reports for almost a year. AA added that
extending the reporting requirement to
30 days would provide relief to the
operators while not decreasing safety.
Hainan Airlines (HNA) recommended
that the compliance time for the
reporting requirement in paragraph (k)
of the proposed AD be extended from 3
to 30 days after the inspection or after
the effective date of the proposed AD, or
an equivalent date, to alleviate the
burden on operators. HNA believes that
Boeing already received a large number
of inspection reporting results for its
root cause analysis over the past year.
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Southwest Airlines (SWA) asked that
the compliance time for the reporting
requirement be extended to 10 days.
SWA stated that the 3-day reporting
requirement was developed for AD
2019–20–02, Amendment 39–19755 (84
FR 52754, October 3, 2019). SWA added
that the inspection program has matured
within Boeing and the Model 737–600,
–700, –700C, –800, –900, and –900ER
operators, and the reporting requirement
of initial inspections can be relaxed
from 3 to 10 days to reduce the burden
on airline operations for reporting noncrack findings. Additionally, SWA
noted that Boeing’s airworthiness
limitation (Document D626A001–9–01)
has a requirement to report any crack
found during these inspections to
Boeing within 10 days.
AIRDO Airlines asked that the
reporting requirement be changed from
3 to 7 days, since the statistical data of
the inspection results for most of the
aging 737NG airplanes has been
reported.
Boeing stated that it has been
receiving inspection reports over the
past year and has accumulated
substantial data, and asked that the
reporting requirement be extended to 10
days.
Because of the information available
from the inspection findings that have
already been reported to Boeing, the
FAA agrees to extend the reporting
requirements in paragraphs (h) and (k)
of this AD to 10 days, which would
reduce the reporting burden on
operators and would provide an
acceptable level of safety. However,
Boeing and the FAA are still relying on
those inspection results both to provide
repair instructions when cracks are
found and to better understand the
nature, cause, and extent of the cracking
and ultimately develop a terminating
action. The FAA, therefore, does not
agree to extend the reporting
requirement to 30 days.
Request To Provide Credit for Previous
Reporting Requirement
Boeing and AIRDO Airlines asked that
reporting as specified in paragraph (k) of
the proposed AD not be required if an
inspection report was previously
submitted in accordance with AD 2019–
20–02 or AD 2019–22–10.
The FAA partially agrees with the
commenters’ request. Although
reporting per AD 2019–20–02 alone is
not adequate for credit with the
reporting requirement specified in
paragraph (k) of this AD, reporting per
AD 2019–22–10 meets the reporting
requirement specified in paragraph (k)
of this AD. Therefore, the FAA has
revised paragraph (k) of this AD to
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specify that a report submitted as
required in paragraph (h) of this AD is
acceptable for compliance with the
requirements of paragraph (k) of this
AD.
Request To Clarify Reporting
Requirement
One commenter asked that the
reporting requirement in paragraph (k)
of the proposed AD be clarified. The
commenter stated that inspection report
example specified in Boeing MultiOperator Message MOM–MOM–20–
0443–01B (R1), dated June 2, 2020, has
columns for repetitive inspections. The
commenter noted that reporting findings
only for the initial inspection is
required by the proposed AD, and
would like conformation that reporting
findings for repetitive inspections
thereafter is not required if no cracks are
found.
The FAA acknowledges the
commenter’s concern and confirms that
paragraph (k) of this AD requires
reporting findings for only the initial
inspection, and no reporting is required
for any repetitive inspection regardless
of the findings.
Effects of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing, SWA, and
HNA stated that the installation of
blended or split scimitar winglets per
Supplemental Type Certificate (STC)
ST00830SE does not affect compliance
with the proposed actions.
The FAA agrees with the commenters
that STC ST00830SE does not affect the
accomplishment of the manufacturer’s
service instructions. Operators of
airplanes with these winglets do not
need to request a ‘‘change in product’’
alternative method of compliance
(AMOC) approval as specified in 14 CFR
39.17. The FAA has redesignated
paragraph (c) of the proposed AD as
paragraph (c)(1) of this AD, and added
paragraph (c)(2) to this AD accordingly.
Request To Use Figures To Accomplish
the Refined Inspection
AA asked that it be allowed to use the
figures for the refined inspection areas
in FAA Letter 782–19–14004. AA stated
that the global AMOC provided in FAA
Letter 782–19–14004 and Boeing MultiOperator Message MOM–MOM–19–
0536–01B, dated September 30, 2019, is
referenced in Boeing Multi-Operator
Message MOM–MOM–20–0443–01B
(R1), dated June 2, 2020; however, it is
not mentioned in the proposed AD.
The FAA partially agrees with the
commenter’s request. Paragraph (n)(5) of
this AD states that AMOCs approved
previously for AD 2019–22–10, which
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include the referenced global AMOC,
are approved as AMOCs for the
corresponding provisions of this AD.
Therefore, no change to this AD is
necessary regarding this issue.
Request for Correction of
Typographical Error
Boeing and HNA requested the FAA
correct a typographical error for the
effective date of AD 2019–22–10, which
is referenced in paragraph (h)(1) of the
proposed AD as October 3, 3019, when
the correct date is October 3, 2019.
The FAA agrees with the commenters’
request. The FAA has corrected the
effective date of AD 2019–22–10 in
paragraph (h)(1) of this AD accordingly.
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
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 AD.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing MultiOperator Message MOM–MOM–20–
0443–01B (R1), dated June 2, 2020. This
service information specifies procedures
for repetitive detailed inspections for
cracking of the left- and right-hand
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 Boeing MultiOperator Message MOM–MOM–19–
0623–01B, dated November 5, 2019,
which the Director of the Federal
Register approved for incorporation by
reference as of November 13, 2019 (84
FR 61533, November 13, 2019).
23597
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.
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.
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
Action
Labor cost
Inspection (retained action from
AD 2019–22–10).
Reporting (retained action from AD
2019–22–10).
Inspection (new action) .................
1 work-hour × $85 per hour = $85
per inspection cycle.
1 work-hour × $85 per hour = $85
$0
1 work-hour × $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.
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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
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Parts cost
Cost per product
0
0
Cost on U.S. operators
$85 per inspection cycle.
$85 ....................
$162,435 per inspection cycle.
$85 per inspection cycle.
$85 ....................
$162,435 per inspection cycle.
$162,435.
$162,435.
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.
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.
Authority for This Rulemaking
Regulatory Findings
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
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,
(2) Will not affect intrastate aviation
in Alaska, and
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(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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:
a. Removing Airworthiness Directive
2019–22–10, Amendment 39–19789 (84
FR 61533, November 13, 2019); and
■ b. Adding the following new
airworthiness directive:
■
■
2021–09–06 The Boeing Company:
Amendment 39–21519; Docket No.
FAA–2020–0789; Project Identifier AD–
2020–00849–T.
(a) Effective Date
This airworthiness directive (AD) is
effective June 8, 2021.
(b) Affected ADs
This AD replaces AD 2019–22–10,
Amendment 39–19789 (84 FR 61533,
November 13, 2019) (AD 2019–22–10).
(c) Applicability
(1) This AD applies to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series airplanes,
certificated in any category.
(2) Installation of Supplemental Type
Certificate (STC) ST00830SE does not affect
the ability to accomplish the actions required
by this AD. Therefore, for airplanes on which
STC ST00830SE is installed, a ‘‘change in
product’’ alternative method of compliance
(AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
39.17.
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(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
cracking discovered in the station (STA)
663.75 frame fitting outboard chords and
failsafe straps adjacent to the stringer S–18A
straps and a determination that the initial
inspection threshold for certain airplanes and
the repetitive inspection interval specified in
AD 2019–22–10 are inadequate to address the
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cracking in a timely manner. 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 2019–22–10, 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, Amendment 39–19755 (84 FR
52754, October 3, 2019) (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 2019–22–10, 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, 2019 (the effective date of AD
2019–20–02): Submit the report within 10
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 10
days after October 3, 2019.
(i) Inspection and Corrective Action With
Reduced Compliance Times
Except as specified in paragraph (j) of this
AD: At the applicable initial compliance time
specified in Tables 1 and 2 of ‘‘Ref I’’ of
Boeing Multi-Operator Message MOM–
MOM–20–0443–01B (R1), dated June 2, 2020,
do a detailed inspection of the left- and right-
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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–20–0443–
01B (R1), dated June 2, 2020. 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
applicable intervals specified in Tables 1 and
2 of ‘‘Ref I’’ of Boeing Multi-Operator
Message MOM–MOM–20–0443–01B (R1),
dated June 2, 2020. Accomplishing the initial
inspection required by this paragraph or an
initial inspection specified in Boeing MultiOperator Message MOM–MOM–19–0623–
01B, dated November 5, 2019, terminates the
inspections required by paragraph (g) of this
AD.
(j) Exceptions to Service Information
Specifications
Where Boeing Multi-Operator Message
MOM–MOM–20–0443–01B (R1), dated June
2, 2020, uses the phrase ‘‘the original issue
date of MOM–MOM–20–0443–01B(R1),’’ 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 MOM–MOM–20–0443–
01B (R1), dated June 2, 2020. A report
submitted as specified in paragraph (h) of
this AD is acceptable for compliance with the
requirements of this paragraph.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 10 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 10 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,
E:\FR\FM\04MYR1.SGM
04MYR1
Federal Register / Vol. 86, No. 84 / Tuesday, May 4, 2021 / Rules and Regulations
and completing and reviewing the collection
of information. All responses to this
collection of information are mandatory as
required by this AD. 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.
(5) AMOCs approved previously for AD
2019–22–10 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.
khammond on DSKJM1Z7X2PROD with RULES
(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 June 8, 2021.
(i) Boeing Multi-Operator Message MOM–
MOM–20–0443–01B (R1), dated June 2, 2020.
(ii) [Reserved]
(4) The following service information was
approved for IBR on November 13, 2019 (84
FR 61533, November 13, 2019).
VerDate Sep<11>2014
16:02 May 03, 2021
Jkt 253001
(i) Boeing Multi-Operator Message MOM–
MOM–19–0623–01B, dated November 5,
2019.
(ii) [Reserved]
(5) 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]
(6) 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.
(7) You may view this service information
at the FAA, Airworthiness Products Section,
Operational Safety Branch, 2200 South 216th
St., Des Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(8) 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 on April 15, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–08849 Filed 5–3–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0346; Project
Identifier AD–2021–00465–E; Amendment
39–21539; AD 2021–10–06]
RIN 2120–AA64
Airworthiness Directives; CFM
International, S.A. Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
CFM International, S.A. (CFM) LEAP–
1B model turbofan engines. This AD
was prompted by multiple reports of
pressure sub-system (PSS) unit faults
due to pressure transducer corrosion
following extended storage periods. For
an engine in service, this AD requires
checks for engine maintenance messages
related to the pressure transducer and,
depending on the results of the check,
replacement of the PSS unit before
SUMMARY:
PO 00000
Frm 00023
Fmt 4700
Sfmt 4700
23599
further flight. The AD requires this
repetitive check for faults prior to each
flight until the PSS has accumulated at
least 15 hours of electrical power. For
an engine not in service, this AD
requires applying electrical power to the
PSS unit before further flight. The FAA
is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective May 10,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 10, 2021.
The FAA must receive comments on
this AD by June 18, 2021.
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 CFM
International, S.A., Aviation Operations
Center, 1 Neumann Way, M/D Room
285, Cincinnati, OH 45125; phone: (877)
432–3272; fax: (877) 432–3329; email:
aviation.fleetsupport@ge.com. You may
view this service information at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (781) 238–
7759. It is also available at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0346.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0346; or in person at Docket
Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays. The AD docket contains this
final rule, any comments received, and
other information. The street address for
the Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Mehdi Lamnyi, Aviation Safety
Engineer, ECO Branch, FAA, 1200
District Avenue, Burlington, MA 01803;
phone: (781) 238–7743; fax: (781) 238–
7199; email: Mehdi.Lamnyi@faa.gov.
E:\FR\FM\04MYR1.SGM
04MYR1
]]>Agencies
[Federal Register Volume 86, Number 84 (Tuesday, May 4, 2021)]
[Rules and Regulations]
[Pages 23595-23599]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-08849]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0789; Project Identifier AD-2020-00849-T;
Amendment 39-21519; AD 2021-09-06]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-22-
10, which applied to all The Boeing Company Model 737-600, -700, -700C,
-800, -900, and -900ER series airplanes. AD 2019-22-10 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 eight fasteners, and repair if any cracking is found.
For certain airplanes, this AD reduces the compliance time for the
initial inspection, and for all airplanes this AD reduces the
repetitive interval. This AD was prompted by a determination that the
initial inspection threshold and repetitive inspection interval are
inadequate to address the cracking in a timely manner. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective June 8, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 8,
2021.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 13, 2019 (84 FR 61533, 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).
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; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the
FAA, Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability of
this material at the FAA, call 206-231-3195. It is also available on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2020-0789.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.govby searching for and locating Docket No. FAA-2020-
0789; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, any comments received, and other information. The
address for Docket Operations is U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE, Washington, DC 20590.
[[Page 23596]]
FOR FURTHER INFORMATION 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].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2019-22-10, Amendment 39-19789 (84 FR
61533, November 13, 2019) (AD 2019-22-10). AD 2019-22-10 applied to all
The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER
series airplanes. The NPRM published in the Federal Register on
September 8, 2020 (85 FR 55391). The NPRM was prompted by an
engineering analysis of the inspection reporting results and
metallurgical evaluation of the submitted frame fitting assemblies,
which indicated that the initial inspection threshold for Model 737-
900ER series airplanes and the repetitive inspection interval for all
affected airplanes are inadequate to address the cracking in a timely
manner. For certain airplanes, the NPRM proposed to reduce the
compliance time for the initial inspection, and for all airplanes the
NPRM proposed to reduce the repetitive inspection interval.
Comments
The FAA gave the public the opportunity to participate in
developing this AD. The following presents the comments received on the
NPRM and the FAA's response to each comment.
Request To Extend the Compliance Time for the Reporting Requirement
American Airlines (AA) asked that the compliance time for the
reporting requirements in paragraphs (h) and (k) of the proposed AD be
extended to 30 days after the date of inspection. AA stated that the
cracking of the station (STA) 663.75 fitting is now a known problem,
and Boeing has been receiving reports for almost a year. AA added that
extending the reporting requirement to 30 days would provide relief to
the operators while not decreasing safety. Hainan Airlines (HNA)
recommended that the compliance time for the reporting requirement in
paragraph (k) of the proposed AD be extended from 3 to 30 days after
the inspection or after the effective date of the proposed AD, or an
equivalent date, to alleviate the burden on operators. HNA believes
that Boeing already received a large number of inspection reporting
results for its root cause analysis over the past year.
Southwest Airlines (SWA) asked that the compliance time for the
reporting requirement be extended to 10 days. SWA stated that the 3-day
reporting requirement was developed for AD 2019-20-02, Amendment 39-
19755 (84 FR 52754, October 3, 2019). SWA added that the inspection
program has matured within Boeing and the Model 737-600, -700, -700C, -
800, -900, and -900ER operators, and the reporting requirement of
initial inspections can be relaxed from 3 to 10 days to reduce the
burden on airline operations for reporting non-crack findings.
Additionally, SWA noted that Boeing's airworthiness limitation
(Document D626A001-9-01) has a requirement to report any crack found
during these inspections to Boeing within 10 days.
AIRDO Airlines asked that the reporting requirement be changed from
3 to 7 days, since the statistical data of the inspection results for
most of the aging 737NG airplanes has been reported.
Boeing stated that it has been receiving inspection reports over
the past year and has accumulated substantial data, and asked that the
reporting requirement be extended to 10 days.
Because of the information available from the inspection findings
that have already been reported to Boeing, the FAA agrees to extend the
reporting requirements in paragraphs (h) and (k) of this AD to 10 days,
which would reduce the reporting burden on operators and would provide
an acceptable level of safety. However, Boeing and the FAA are still
relying on those inspection results both to provide repair instructions
when cracks are found and to better understand the nature, cause, and
extent of the cracking and ultimately develop a terminating action. The
FAA, therefore, does not agree to extend the reporting requirement to
30 days.
Request To Provide Credit for Previous Reporting Requirement
Boeing and AIRDO Airlines asked that reporting as specified in
paragraph (k) of the proposed AD not be required if an inspection
report was previously submitted in accordance with AD 2019-20-02 or AD
2019-22-10.
The FAA partially agrees with the commenters' request. Although
reporting per AD 2019-20-02 alone is not adequate for credit with the
reporting requirement specified in paragraph (k) of this AD, reporting
per AD 2019-22-10 meets the reporting requirement specified in
paragraph (k) of this AD. Therefore, the FAA has revised paragraph (k)
of this AD to specify that a report submitted as required in paragraph
(h) of this AD is acceptable for compliance with the requirements of
paragraph (k) of this AD.
Request To Clarify Reporting Requirement
One commenter asked that the reporting requirement in paragraph (k)
of the proposed AD be clarified. The commenter stated that inspection
report example specified in Boeing Multi-Operator Message MOM-MOM-20-
0443-01B (R1), dated June 2, 2020, has columns for repetitive
inspections. The commenter noted that reporting findings only for the
initial inspection is required by the proposed AD, and would like
conformation that reporting findings for repetitive inspections
thereafter is not required if no cracks are found.
The FAA acknowledges the commenter's concern and confirms that
paragraph (k) of this AD requires reporting findings for only the
initial inspection, and no reporting is required for any repetitive
inspection regardless of the findings.
Effects of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing, SWA, and HNA stated that the installation
of blended or split scimitar winglets per Supplemental Type Certificate
(STC) ST00830SE does not affect compliance with the proposed actions.
The FAA agrees with the commenters that STC ST00830SE does not
affect the accomplishment of the manufacturer's service instructions.
Operators of airplanes with these winglets do not need to request a
``change in product'' alternative method of compliance (AMOC) approval
as specified in 14 CFR 39.17. The FAA has redesignated paragraph (c) of
the proposed AD as paragraph (c)(1) of this AD, and added paragraph
(c)(2) to this AD accordingly.
Request To Use Figures To Accomplish the Refined Inspection
AA asked that it be allowed to use the figures for the refined
inspection areas in FAA Letter 782-19-14004. AA stated that the global
AMOC provided in FAA Letter 782-19-14004 and Boeing Multi-Operator
Message MOM-MOM-19-0536-01B, dated September 30, 2019, is referenced in
Boeing Multi-Operator Message MOM-MOM-20-0443-01B (R1), dated June 2,
2020; however, it is not mentioned in the proposed AD.
The FAA partially agrees with the commenter's request. Paragraph
(n)(5) of this AD states that AMOCs approved previously for AD 2019-22-
10, which
[[Page 23597]]
include the referenced global AMOC, are approved as AMOCs for the
corresponding provisions of this AD. Therefore, no change to this AD is
necessary regarding this issue.
Request for Correction of Typographical Error
Boeing and HNA requested the FAA correct a typographical error for
the effective date of AD 2019-22-10, which is referenced in paragraph
(h)(1) of the proposed AD as October 3, 3019, when the correct date is
October 3, 2019.
The FAA agrees with the commenters' request. The FAA has corrected
the effective date of AD 2019-22-10 in paragraph (h)(1) of this AD
accordingly.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this AD 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 AD.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Multi-Operator Message MOM-MOM-20-0443-01B
(R1), dated June 2, 2020. This service information specifies procedures
for repetitive detailed inspections for cracking of the left- and
right-hand 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 Boeing Multi-Operator Message MOM-MOM-19-
0623-01B, dated November 5, 2019, which the Director of the Federal
Register approved for incorporation by reference as of November 13,
2019 (84 FR 61533, November 13, 2019).
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.
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.
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 2019-22-10). per hour = $85 per cycle. inspection cycle.
inspection cycle.
Reporting (retained action from 1 work-hour x $85 0 $85................ $162,435.
AD 2019-22-10). per hour = $85.
Inspection (new action).......... 1 work-hour 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.
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,
(2) Will not affect intrastate aviation in Alaska, and
[[Page 23598]]
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive 2019-22-10, Amendment 39-19789 (84
FR 61533, November 13, 2019); and
0
b. Adding the following new airworthiness directive:
2021-09-06 The Boeing Company: Amendment 39-21519; Docket No. FAA-
2020-0789; Project Identifier AD-2020-00849-T.
(a) Effective Date
This airworthiness directive (AD) is effective June 8, 2021.
(b) Affected ADs
This AD replaces AD 2019-22-10, Amendment 39-19789 (84 FR 61533,
November 13, 2019) (AD 2019-22-10).
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-600, -
700, -700C, -800, -900, and -900ER series airplanes, certificated in
any category.
(2) Installation of Supplemental Type Certificate (STC)
ST00830SE does not affect the ability to accomplish the actions
required by this AD. Therefore, for airplanes on which STC ST00830SE
is installed, a ``change in product'' alternative method of
compliance (AMOC) approval request is not necessary to comply with
the requirements of 14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking discovered in the
station (STA) 663.75 frame fitting outboard chords and failsafe
straps adjacent to the stringer S-18A straps and a determination
that the initial inspection threshold for certain airplanes and the
repetitive inspection interval specified in AD 2019-22-10 are
inadequate to address the cracking in a timely manner. 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
2019-22-10, 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, Amendment 39-19755 (84 FR 52754, October 3, 2019) (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
2019-22-10, 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, 2019 (the
effective date of AD 2019-20-02): Submit the report within 10 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 10 days
after October 3, 2019.
(i) Inspection and Corrective Action With Reduced Compliance Times
Except as specified in paragraph (j) of this AD: At the
applicable initial compliance time specified in Tables 1 and 2 of
``Ref I'' of Boeing Multi-Operator Message MOM-MOM-20-0443-01B (R1),
dated June 2, 2020, 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-20-0443-01B (R1), dated June 2, 2020. 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 applicable intervals specified in
Tables 1 and 2 of ``Ref I'' of Boeing Multi-Operator Message MOM-
MOM-20-0443-01B (R1), dated June 2, 2020. Accomplishing the initial
inspection required by this paragraph or an initial inspection
specified in Boeing Multi-Operator Message MOM-MOM-19-0623-01B,
dated November 5, 2019, terminates the inspections required by
paragraph (g) of this AD.
(j) Exceptions to Service Information Specifications
Where Boeing Multi-Operator Message MOM-MOM-20-0443-01B (R1),
dated June 2, 2020, uses the phrase ``the original issue date of
MOM-MOM-20-0443-01B(R1),'' 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 MOM-MOM-20-0443-01B (R1), dated June
2, 2020. A report submitted as specified in paragraph (h) of this AD
is acceptable for compliance with the requirements of this
paragraph.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 10 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 10 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,
[[Page 23599]]
and completing and reviewing the collection of information. All
responses to this collection of information are mandatory as
required by this AD. 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.
(5) AMOCs approved previously for AD 2019-22-10 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
June 8, 2021.
(i) Boeing Multi-Operator Message MOM-MOM-20-0443-01B (R1),
dated June 2, 2020.
(ii) [Reserved]
(4) The following service information was approved for IBR on
November 13, 2019 (84 FR 61533, November 13, 2019).
(i) Boeing Multi-Operator Message MOM-MOM-19-0623-01B, dated
November 5, 2019.
(ii) [Reserved]
(5) 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]
(6) 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.
(7) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability
of this material at the FAA, call 206-231-3195.
(8) 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 on April 15, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-08849 Filed 5-3-21; 8:45 am]
BILLING CODE 4910-13-P
