Airworthiness Directives; The Boeing Company Airplanes, 17483-17487 [2020-06508]
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Federal Register / Vol. 85, No. 61 / Monday, March 30, 2020 / Rules and Regulations
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/Pylons.
(e) Unsafe Condition
This AD was prompted by a report of
failure of a wing strut leak test due to a
missing bolt on the firewall. The FAA is
issuing this AD to address a hole in the
firewall, which could allow flammable fluid
to leak from the strut compartment to the
engine compartment when the drainage
provision is overwhelmed. Flammable fluid
leakage into the engine compartment could
result in an uncontrollable engine fire and
consequent structural failure of the wing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Leak Test and Corrective Action
Within 12 months after the effective date
of this AD: Do a one-time leak (functional)
test of the strut upper spar areas for the left
and right wing struts, by doing the actions
specified in paragraphs (g)(1) through (5) of
this AD. A review of airplane maintenance
records is acceptable in lieu of this test if it
can be conclusively determined from that
review that the leak test was previously
accomplished and successfully completed.
(1) Put a plug in the strut forward drain
outlet (this drain outlet is labeled as ‘‘pylon
strut’’). Put an empty container below the
strut forward drain outlet to collect water
drained through this outlet.
(2) Apply 381 to 387 fluid ounces (11.3 to
11.4 liters) of water in 2.5 to 3.5 minutes, to
the systems tubing shroud (area between the
forward and mid-vapor barriers).
(3) Make sure that no leakage occurred
after doing the action specified in paragraph
(g)(2) of this AD.
(4) Remove the plug from the strut forward
drain outlet and make sure that the water is
drained through the strut forward drain
outlet only.
(5) After 3 minutes from accomplishing the
action specified in paragraph (g)(4) of this
AD, measure the water collected in the
container, and do the applicable actions
specified in paragraphs (g)(5)(i) through (iii)
of this AD.
(i) If leaks were found, do corrective action
before further flight using a method approved
in accordance with the procedures specified
in paragraph (h) of this AD.
(ii) If no leaks were found and less than
354 fluid ounces (10.5 liters) of water is
collected in the container, do corrective
action before further flight using a method
approved in accordance with the procedures
specified in paragraph (h) of this AD.
(iii) Before further flight after
accomplishing any corrective action required
by paragraph (g)(5)(i) or (ii) of this AD, repeat
the actions specified in paragraphs (g)(1)
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through (5) of this AD until successful
completion of the test (i.e., no leaks are found
and 354 fluid ounces (10.5 liters) of water or
more is measured in the container).
Note 1 to paragraph (g): Additional
guidance for performing the leak (functional)
test can be found in Boeing 787 Aircraft
Maintenance Manual (AMM), 54–65–01,
Strut Spar—Upper—Functional Test.
(h) 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 (i)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-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.
(i) Related Information
(1) For more information about this AD,
contact Tak Kobayashi, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3553;
email: takahisa.kobayashi@faa.gov.
(2) For service information identified in
this AD that is not incorporated by reference,
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. For information on
the availability of this material at the FAA,
call 206–231–3195.
(j) Material Incorporated by Reference
None.
Issued on March 10, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–06459 Filed 3–27–20; 8:45 am]
BILLING CODE 4910–13–P
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17483
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0438; Product
Identifier 2019–NM–033–AD; Amendment
39–19875; AD 2020–05–25]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
ACTION:
Final rule.
The FAA is adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 757–200,
–200PF, –200CB, and –300 series
airplanes. This AD was prompted by a
report that during a maintenance check
an operator discovered cracking of the
aft cargo compartment frames in the
station 1460 frame web and inner chord
between certain stringers. This AD
requires an inspection of the fuselage
frames for any existing repair, repetitive
surface high frequency eddy current
(HFEC) inspections of the fuselage
frames with a cargo liner support
channel for any cracking, and applicable
on-condition actions. The FAA is
issuing this AD to address the unsafe
condition on these products.
SUMMARY:
DATES:
This AD is effective May 4, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 4, 2020.
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–2019–0438.
ADDRESSES:
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Federal Register / Vol. 85, No. 61 / Monday, March 30, 2020 / Rules and Regulations
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–
0438; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Peter Jarzomb, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5234; fax: 562–627–
5210; email: peter.jarzomb@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
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The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all The Boeing Company Model
757 airplanes. The NPRM published in
the Federal Register on June 28, 2019
(84 FR 30958). The NPRM was
prompted by a report that during a
maintenance check an operator
discovered cracking of the aft cargo
compartment frames in the station 1460
frame web and inner chord between
stringers S–26 and S–27 near an existing
repair. The NPRM proposed to require
an inspection of the fuselage frames for
any existing repair, repetitive surface
HFEC inspections of the fuselage frames
with a cargo liner support channel for
any cracking, and applicable oncondition actions.
The FAA issued a supplemental
notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an
AD that would apply to all The Boeing
Company Model 757 airplanes. The
SNPRM published in the Federal
Register on December 2, 2019 (84 FR
65931). The FAA issued the SNPRM to
reduce the compliance time for certain
airplane configurations.
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The FAA is issuing this AD to address
cracking at the frame web and inner
chord; such cracks could propagate
until they cause a severed frame, which
could result in additional undetected
cracking in adjacent fuselage frames,
and could ultimately result in reduced
structural integrity of the aft cargo
frames and consequent rapid
decompression of the airplane.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The following presents
the comments received on the SNPRM
and the FAA’s response to each
comment.
Support for the SNPRM
Boeing and United Airlines concurred
with the SNPRM. FedEx stated they had
no objection to the SNPRM.
Request To Utilize Actions for a Certain
Airplane Group and a Compliance
Time for Another Airplane Group
VT Mobile Aerospace Engineering
Inc. (VT MAE Inc.) requested to utilize
inspections and methods for Group 7
airplanes, and utilize the compliance
times for Groups 3 and 5 airplanes,
which would reduce the repetitive
inspection interval from 6,000 flight
cycles to 4,000 flight cycles. VT MAE
Inc. stated that its Model 757–200
airplanes were converted to freighter
configuration per VT MAE Inc.
supplemental type certificate (STC)
ST04242AT (15 pallet configuration)
and VT MAE Inc. STC ST03952AT
(combi configuration/14 pallet
configuration), and are no longer
configured as a passenger airplanes. VT
MAE Inc. also stated that Boeing Alert
Requirements Bulletin 757–53A0113
RB, dated February 22, 2019, shows that
its converted Model 757–200 freighter
fleet falls under Group 7 airplanes. VT
MAE Inc. provided no justification for
using compliance times for different
airplane groups.
The FAA agrees to provide additional
clarification. The FAA issued the
SNPRM to add an airplane configuration
to the NPRM that addressed FedEx’s
fleet of 119 airplanes (approximately
22% of the affected U.S. fleet) that were
converted from a passenger
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configuration to a freighter
configuration using VT MAE Inc. STC
ST03562AT. It was determined that
these airplanes are subjected to the same
fatigue loads as Groups 3 and 5
airplanes, as specified in Boeing Alert
Requirements Bulletin 757–53A0113
RB, dated February 22, 2019. Therefore,
paragraph (g)(2) of this AD was added
in the SNPRM to address the required
actions and compliance times for this
added airplane configuration.
The FAA agrees with VT MAE Inc.’s
comments that airplanes modified using
VT MAE Inc. STC ST04242AT and VT
MAE Inc. STC ST03952AT are no longer
configured as passenger airplanes.
However, the FAA disagrees with the
request to include additional exceptions
in this AD that are specific to certain
airplanes converted by VT MAE Inc.
There are many different airplane
configurations across multiple
operators, and ADs cannot
accommodate all possible
configurations.
The FAA has already delayed this AD
to address one configuration. To reduce
the compliance time of the proposed AD
for airplanes modified using VT MAE
Inc. STCs ST04242AT and ST003952AT
would necessitate (under the provisions
of the Administrative Procedure Act)
reissuing the notice, reopening the
period for public comment, considering
additional comments subsequently
received, and eventually issuing a final
rule. That procedure could add
unwarranted time to the rulemaking
process. To delay this AD again would
be inappropriate, since the FAA has
determined that an unsafe condition
exists and that inspections must be
conducted to ensure continued safety.
However, if additional data are
presented that would justify a shorter
compliance time for these airplanes, the
FAA may consider further rulemaking
on this issue. Under the provisions of
paragraph (i) of this AD, the FAA will
consider requests for approval of
alternative actions and compliance
times if sufficient data are submitted to
substantiate that the change would
provide an acceptable level of safety.
The FAA has not changed this AD in
this regard.
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Request To Revise the Language in Note
(a) of the Service Information
DAL requested that the language in
Note (a) of paragraph ‘‘3. Compliance,’’
of Boeing Alert Requirements Bulletin
757–53A0113 RB, dated February 22,
2019, be revised from ‘‘meets the
following criteria’’ to ‘‘meets one of the
following criteria,’’ and to also add
‘‘757–200 SRM [Structural Repair
Manual] 53–00–07 Repair 5’’ to the
criteria. DAL stated that it interprets the
note to mean either criterion 1 or
criterion 2 provides relief from
performing the subject inspections and
that the statement only takes into
consideration that a repair may be
approved using FAA Form 8100–9. DAL
commented that ‘‘757–200 SRM 53–00–
07 Repair 5’’ is also an FAA-approved
repair for aft cargo compartment lower
frames. DAL commented that the Boeing
757 SRM and any repair approved by
The Boeing Organization Designation
Authorization (ODA) using FAA Form
8100–9 are both FAA-approved and
have damage tolerance analyses.
The FAA disagrees with the comment.
Note (a) in Boeing Alert Requirements
Bulletin 757–53A0113 RB, dated
February 22, 2019, is intended to
address repairs that were designed as
corrective actions to the unsafe
condition addressed in the service
information and this AD, are Boeing
ODA-approved, and include a follow-on
inspection program, but were installed
before this AD becomes effective. For
this reason, the FAA allows FAA Form
8100–9 for approved repairs that meet
both criteria (1) and (2) specified in
Note (a) of Boeing Alert Requirements
Bulletin 757–53A0113 RB, dated
February 22, 2019, to be exempted from
the inspections in those repaired areas,
but do not allow just any FAA-approved
repair to be exempted from these
required inspections. However, under
the provisions of paragraph (i) of this
AD, the FAA will consider requests for
approval of certain repairs in this area
that affect compliance with this AD if
sufficient data are submitted to
substantiate that the change would
provide an acceptable level of safety.
The FAA has not changed this AD in
this regard.
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Request To Revise Certain Wording
DAL pointed out that Sheet 3 of 3 of
Figure 21 of Boeing Alert Requirements
Bulletin 757–53A0113 RB, dated
February 22, 2019, contains an error in
the inspection task description. DAL
stated that the inspection task
description and general visual
inspection for station 1260
nomenclature should be ‘‘FRAME’’
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instead of ‘‘FRAME WEB.’’ DAL also
stated that the procedure is to do a
general visual inspection for any
existing repairs in the area prior to
accomplishing a detailed inspection and
HFEC inspection. DAL commented that
this is also consistent with the other
general visual inspection nomenclature
of adjacent frames to a frame found with
a severed inner chord on Group 12
airplanes.
From these statements, the FAA infers
that DAL was requesting that the
SNPRM be revised to correct the error
in Figure 21 (Sheet 3 of 3) of Boeing
Alert Requirements Bulletin 757–
53A0113 RB, dated February 22, 2019.
The FAA disagrees with the
commenter’s request. While the FAA
agrees that the name of the part
specified in Figure 21 (Sheet 3 of 3) of
Boeing Alert Requirements Bulletin
757–53A0113 RB, dated February 22,
2019, is incorrect, it will not affect the
operator’s ability to accomplish the
inspection in Figure 21 (Sheet 3 of 3) of
Boeing Alert Requirements Bulletin
757–53A0113 RB, dated February 22,
2019, as the location where the
inspection is to be performed is clearly
identified in the figure. The FAA has
not changed this AD in this regard.
Request To Define ‘‘Unrepaired
Locations’’
Delta Airlines (DAL) requested that
the FAA define ‘‘unrepaired locations’’
in the SNPRM to eliminate
misinterpretations. DAL stated that it
has interpreted the definition of
‘‘unrepaired locations’’ to mean the
areas of each frame that do not have a
repair, which interferes with
accomplishment of the HFEC
inspection. DAL commented that this
interpretation is based on the possibility
that airplanes in a cargo liner
attachment channel configuration with
two fasteners may have one fastener
location with an interfering repair and
one fastener location without an
interfering repair. DAL also stated that
it possible to interpret ‘‘unrepaired
locations’’ to mean only body stations
with fuselage frames free of existing
repairs.
The FAA disagrees with the
commenter’s request. The service
information defines the locations that
are to be inspected for repairs and
cracks. Boeing Alert Requirements
Bulletin 757–53A0113 RB, dated
February 22, 2019, specifies operators to
do a general visual inspection of the
fuselage frames with a cargo liner
support channel for any existing repair
and provides figures that define the
areas where these inspections for repairs
are to be performed. The on-condition
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17485
actions in Boeing Alert Requirements
Bulletin 757–53A0113 RB, dated
February 22, 2019, then specify that if
a repair in the inspection area is found
to contact Boeing for alternative
inspections and then to do those
inspections and any corrective actions,
as applicable. Paragraph (h) of this AD
requires operators to do the repair, or
alternative inspections and applicable
on-condition actions using a method
approved in accordance with the
procedures specified in paragraph (i) of
this AD. In addition, Boeing Alert
Requirements Bulletin 757–53A0113
RB, dated February 22, 2019, specifies
that operators perform the inspections
for cracks at the locations that did not
have repairs and provides figures that
clearly define those inspection areas.
The FAA has not changed this AD in
this regard.
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. The FAA has
determined that these minor changes:
• Are consistent with the intent that
was proposed in the SNPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin 757–53A0113
RB, dated February 22, 2019. This
service information describes
procedures for a general visual
inspection of the fuselage frames with a
cargo liner support channel for any
existing repair, repetitive surface HFEC
inspections of the fuselage frames with
a cargo liner support channel for any
cracking, and applicable on-condition
actions. On-condition actions include a
general visual inspection of the fuselage
frames adjacent to a frame with a
severed inner chord for any existing
repair, a detailed inspection and a
surface HFEC inspection of the fuselage
frames adjacent to a frame with a
severed inner chord for any cracking,
and repair. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD
affects 544 airplanes of U.S. registry.
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Federal Register / Vol. 85, No. 61 / Monday, March 30, 2020 / Rules and Regulations
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
General visual inspection .......
37 work-hours × $85 per hour
= $3,145.
Up to 37 work-hours × $85
per hour = Up to $3,145
per inspection cycle.
Repetitive surface HFEC inspections.
The FAA estimates the following
costs to do any necessary on-condition
Parts cost
Cost per product
$0
0
Cost on U.S. operators
$3,145 ....................................
$1,710,880.
Up to $3,145 per inspection
cycle.
Up to $1,710,880 per inspection cycle.
inspections that would be required. The
FAA has no way of determining the
number of aircraft that might need these
on-condition inspections:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Up to 20 work-hour × $85 per hour = Up to $1,700 per inspection cycle ...................
$0
The FAA has received no definitive
data that would enable the agency to
provide cost estimates for the oncondition repair specified in this AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: ‘‘General requirements.’’ Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
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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 adding
the following new airworthiness
directive (AD):
■
2020–05–25 The Boeing Company:
Amendment 39–19875; Docket No.
FAA–2019–0438; Product Identifier
2019–NM–033–AD.
(a) Effective Date
This AD is effective May 4, 2020.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing
Company Model 757–200, –200PF, –200CB,
and –300 series airplanes, certificated in any
category.
(2) Installation of Supplemental Type
Certificate (STC) ST01518SE does not affect
the ability to accomplish the actions required
by this AD. Therefore, for airplanes on which
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Cost per product
Up to $1,700 per inspection cycle.
STC ST01518SE 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 a report that
during a maintenance check an operator
discovered cracking of the aft cargo
compartment frames in the station 1460
frame web and inner chord between certain
stringers. The FAA is issuing this AD to
address cracking at the frame web and inner
chord; such cracks could propagate until they
cause a severed frame, which could result in
additional undetected cracking in adjacent
fuselage frames, and could ultimately result
in reduced structural integrity of the aft cargo
frames and consequent rapid decompression
of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Except as specified by paragraphs (g)(2)
and (h) of this AD: At the applicable times
specified in the ‘‘Compliance’’ paragraph of
Boeing Alert Requirements Bulletin 757–
53A0113 RB, dated February 22, 2019, do all
applicable actions identified in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Requirements
Bulletin 757–53A0113 RB, dated February
22, 2019.
(2) For airplanes that have been converted
from a passenger to freighter configuration
using VT Mobile Aerospace Engineering Inc.
(VT MAE Inc.) STC ST03562AT: Except as
specified by paragraph (h) of this AD, at the
times specified for Groups 3 and 5 airplanes,
as applicable, in the ‘‘Compliance’’ paragraph
of Boeing Alert Requirements Bulletin 757–
53A0113 RB, dated February 22, 2019, do all
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applicable actions for Groups 2, 7, and 10
airplanes as identified in, and in accordance
with the Accomplishment Instructions of
Boeing Alert Requirements Bulletin 757–
53A0113 RB, dated February 22, 2019.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 757–53A0113, dated February 22,
2019, which is referred to in Boeing Alert
Requirements Bulletin 757–53A0113 RB,
dated February 22, 2019.
(h) Exceptions To Service Information
Specifications
(1) Where Boeing Alert Requirements
Bulletin 757–53A0113 RB, dated February
22, 2019, uses the phrase ‘‘the original issue
date of Requirements Bulletin 757–53A0113
RB,’’ this AD requires using ‘‘the effective
date of this AD,’’ except where Boeing Alert
Requirements Bulletin 757–53A0113 RB,
dated February 22, 2019, uses the phrase ‘‘the
original issue date of Requirements Bulletin
757–53A0113 RB’’ in a note or flag note.
(2) Where Boeing Alert Requirements
Bulletin 757–53A0113 RB, dated February
22, 2019, specifies contacting Boeing for
repair instructions or for alternative
inspections: This AD requires doing the
repair, or doing the alternative inspections
and applicable on-condition actions before
further flight using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
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(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO Branch,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with
14 CFR 39.19, send your request to your
principal inspector or local Flight Standards
District Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in paragraph (j)(1) of
this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Los Angeles ACO Branch, FAA, to
make those findings. To be approved, the
repair method, modification deviation, or
alteration deviation must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(j) Related Information
(1) For more information about this AD,
contact Peter Jarzomb, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5234; fax: 562–627–5210; email:
peter.jarzomb@faa.gov.
VerDate Sep<11>2014
16:52 Mar 27, 2020
Jkt 250001
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Requirements Bulletin
757–53A0113 RB, dated February 22, 2019.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
email fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on March 10, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2020–06508 Filed 3–27–20; 8:45 am]
BILLING CODE 4910–13–P
17487
incorporate new maintenance
requirements and airworthiness
limitations. This AD retains those
actions and requires revising the
existing maintenance or inspection
program, as applicable, to incorporate
additional new or more restrictive
airworthiness limitations. This AD was
prompted by the FAA’s determination
that new or more restrictive
airworthiness limitations are necessary.
The FAA is issuing this AD to address
the unsafe condition on these products.
This AD is effective May 4, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 4, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 13, 2018 (83 FR
50479, October 9, 2018).
DATES:
For service information
identified in this final rule, contact
Dassault Falcon Jet Corporation,
Teterboro Airport, P.O. Box 2000, South
Hackensack, NJ 07606; phone: 201–440–
6700; internet: https://
www.dassaultfalcon.com. You may
view this referenced service information
at the FAA, Transport Standards
Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0870.
ADDRESSES:
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0870; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
14 CFR Part 39
[Docket No. FAA–2019–0870; Product
Identifier 2019–NM–125–AD; Amendment
39–19858; AD 2020–04–22]
RIN 2120–AA64
Airworthiness Directives; Dassault
Aviation Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2018–19–
27 and AD 2014–16–12, which applied
to certain Dassault Aviation Model
FALCON 2000EX airplanes. AD 2018–
19–27 and AD 2014–16–12 required
revising the existing maintenance or
inspection program, as applicable, to
SUMMARY:
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
Tom
Rodriguez, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
phone and fax: 206–231–3226.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
E:\FR\FM\30MRR1.SGM
30MRR1
]]>Agencies
[Federal Register Volume 85, Number 61 (Monday, March 30, 2020)]
[Rules and Regulations]
[Pages 17483-17487]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-06508]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0438; Product Identifier 2019-NM-033-AD; Amendment
39-19875; AD 2020-05-25]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
The Boeing Company Model 757-200, -200PF, -200CB, and -300 series
airplanes. This AD was prompted by a report that during a maintenance
check an operator discovered cracking of the aft cargo compartment
frames in the station 1460 frame web and inner chord between certain
stringers. This AD requires an inspection of the fuselage frames for
any existing repair, repetitive surface high frequency eddy current
(HFEC) inspections of the fuselage frames with a cargo liner support
channel for any cracking, and applicable on-condition actions. The FAA
is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective May 4, 2020.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 4, 2020.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; 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-
0438.
[[Page 17484]]
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-
0438; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Peter Jarzomb, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5234; fax: 562-627-
5210; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all The Boeing Company
Model 757 airplanes. The NPRM published in the Federal Register on June
28, 2019 (84 FR 30958). The NPRM was prompted by a report that during a
maintenance check an operator discovered cracking of the aft cargo
compartment frames in the station 1460 frame web and inner chord
between stringers S-26 and S-27 near an existing repair. The NPRM
proposed to require an inspection of the fuselage frames for any
existing repair, repetitive surface HFEC inspections of the fuselage
frames with a cargo liner support channel for any cracking, and
applicable on-condition actions.
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 by adding an AD that would apply to all The
Boeing Company Model 757 airplanes. The SNPRM published in the Federal
Register on December 2, 2019 (84 FR 65931). The FAA issued the SNPRM to
reduce the compliance time for certain airplane configurations.
The FAA is issuing this AD to address cracking at the frame web and
inner chord; such cracks could propagate until they cause a severed
frame, which could result in additional undetected cracking in adjacent
fuselage frames, and could ultimately result in reduced structural
integrity of the aft cargo frames and consequent rapid decompression of
the airplane.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the SNPRM and the FAA's response to each comment.
Support for the SNPRM
Boeing and United Airlines concurred with the SNPRM. FedEx stated
they had no objection to the SNPRM.
Request To Utilize Actions for a Certain Airplane Group and a
Compliance Time for Another Airplane Group
VT Mobile Aerospace Engineering Inc. (VT MAE Inc.) requested to
utilize inspections and methods for Group 7 airplanes, and utilize the
compliance times for Groups 3 and 5 airplanes, which would reduce the
repetitive inspection interval from 6,000 flight cycles to 4,000 flight
cycles. VT MAE Inc. stated that its Model 757-200 airplanes were
converted to freighter configuration per VT MAE Inc. supplemental type
certificate (STC) ST04242AT (15 pallet configuration) and VT MAE Inc.
STC ST03952AT (combi configuration/14 pallet configuration), and are no
longer configured as a passenger airplanes. VT MAE Inc. also stated
that Boeing Alert Requirements Bulletin 757-53A0113 RB, dated February
22, 2019, shows that its converted Model 757-200 freighter fleet falls
under Group 7 airplanes. VT MAE Inc. provided no justification for
using compliance times for different airplane groups.
The FAA agrees to provide additional clarification. The FAA issued
the SNPRM to add an airplane configuration to the NPRM that addressed
FedEx's fleet of 119 airplanes (approximately 22% of the affected U.S.
fleet) that were converted from a passenger configuration to a
freighter configuration using VT MAE Inc. STC ST03562AT. It was
determined that these airplanes are subjected to the same fatigue loads
as Groups 3 and 5 airplanes, as specified in Boeing Alert Requirements
Bulletin 757-53A0113 RB, dated February 22, 2019. Therefore, paragraph
(g)(2) of this AD was added in the SNPRM to address the required
actions and compliance times for this added airplane configuration.
The FAA agrees with VT MAE Inc.'s comments that airplanes modified
using VT MAE Inc. STC ST04242AT and VT MAE Inc. STC ST03952AT are no
longer configured as passenger airplanes. However, the FAA disagrees
with the request to include additional exceptions in this AD that are
specific to certain airplanes converted by VT MAE Inc. There are many
different airplane configurations across multiple operators, and ADs
cannot accommodate all possible configurations.
The FAA has already delayed this AD to address one configuration.
To reduce the compliance time of the proposed AD for airplanes modified
using VT MAE Inc. STCs ST04242AT and ST003952AT would necessitate
(under the provisions of the Administrative Procedure Act) reissuing
the notice, reopening the period for public comment, considering
additional comments subsequently received, and eventually issuing a
final rule. That procedure could add unwarranted time to the rulemaking
process. To delay this AD again would be inappropriate, since the FAA
has determined that an unsafe condition exists and that inspections
must be conducted to ensure continued safety. However, if additional
data are presented that would justify a shorter compliance time for
these airplanes, the FAA may consider further rulemaking on this issue.
Under the provisions of paragraph (i) of this AD, the FAA will consider
requests for approval of alternative actions and compliance times if
sufficient data are submitted to substantiate that the change would
provide an acceptable level of safety. The FAA has not changed this AD
in this regard.
[[Page 17485]]
Request To Revise the Language in Note (a) of the Service Information
DAL requested that the language in Note (a) of paragraph ``3.
Compliance,'' of Boeing Alert Requirements Bulletin 757-53A0113 RB,
dated February 22, 2019, be revised from ``meets the following
criteria'' to ``meets one of the following criteria,'' and to also add
``757-200 SRM [Structural Repair Manual] 53-00-07 Repair 5'' to the
criteria. DAL stated that it interprets the note to mean either
criterion 1 or criterion 2 provides relief from performing the subject
inspections and that the statement only takes into consideration that a
repair may be approved using FAA Form 8100-9. DAL commented that ``757-
200 SRM 53-00-07 Repair 5'' is also an FAA-approved repair for aft
cargo compartment lower frames. DAL commented that the Boeing 757 SRM
and any repair approved by The Boeing Organization Designation
Authorization (ODA) using FAA Form 8100-9 are both FAA-approved and
have damage tolerance analyses.
The FAA disagrees with the comment. Note (a) in Boeing Alert
Requirements Bulletin 757-53A0113 RB, dated February 22, 2019, is
intended to address repairs that were designed as corrective actions to
the unsafe condition addressed in the service information and this AD,
are Boeing ODA-approved, and include a follow-on inspection program,
but were installed before this AD becomes effective. For this reason,
the FAA allows FAA Form 8100-9 for approved repairs that meet both
criteria (1) and (2) specified in Note (a) of Boeing Alert Requirements
Bulletin 757-53A0113 RB, dated February 22, 2019, to be exempted from
the inspections in those repaired areas, but do not allow just any FAA-
approved repair to be exempted from these required inspections.
However, under the provisions of paragraph (i) of this AD, the FAA will
consider requests for approval of certain repairs in this area that
affect compliance with this AD if sufficient data are submitted to
substantiate that the change would provide an acceptable level of
safety. The FAA has not changed this AD in this regard.
Request To Revise Certain Wording
DAL pointed out that Sheet 3 of 3 of Figure 21 of Boeing Alert
Requirements Bulletin 757-53A0113 RB, dated February 22, 2019, contains
an error in the inspection task description. DAL stated that the
inspection task description and general visual inspection for station
1260 nomenclature should be ``FRAME'' instead of ``FRAME WEB.'' DAL
also stated that the procedure is to do a general visual inspection for
any existing repairs in the area prior to accomplishing a detailed
inspection and HFEC inspection. DAL commented that this is also
consistent with the other general visual inspection nomenclature of
adjacent frames to a frame found with a severed inner chord on Group 12
airplanes.
From these statements, the FAA infers that DAL was requesting that
the SNPRM be revised to correct the error in Figure 21 (Sheet 3 of 3)
of Boeing Alert Requirements Bulletin 757-53A0113 RB, dated February
22, 2019. The FAA disagrees with the commenter's request. While the FAA
agrees that the name of the part specified in Figure 21 (Sheet 3 of 3)
of Boeing Alert Requirements Bulletin 757-53A0113 RB, dated February
22, 2019, is incorrect, it will not affect the operator's ability to
accomplish the inspection in Figure 21 (Sheet 3 of 3) of Boeing Alert
Requirements Bulletin 757-53A0113 RB, dated February 22, 2019, as the
location where the inspection is to be performed is clearly identified
in the figure. The FAA has not changed this AD in this regard.
Request To Define ``Unrepaired Locations''
Delta Airlines (DAL) requested that the FAA define ``unrepaired
locations'' in the SNPRM to eliminate misinterpretations. DAL stated
that it has interpreted the definition of ``unrepaired locations'' to
mean the areas of each frame that do not have a repair, which
interferes with accomplishment of the HFEC inspection. DAL commented
that this interpretation is based on the possibility that airplanes in
a cargo liner attachment channel configuration with two fasteners may
have one fastener location with an interfering repair and one fastener
location without an interfering repair. DAL also stated that it
possible to interpret ``unrepaired locations'' to mean only body
stations with fuselage frames free of existing repairs.
The FAA disagrees with the commenter's request. The service
information defines the locations that are to be inspected for repairs
and cracks. Boeing Alert Requirements Bulletin 757-53A0113 RB, dated
February 22, 2019, specifies operators to do a general visual
inspection of the fuselage frames with a cargo liner support channel
for any existing repair and provides figures that define the areas
where these inspections for repairs are to be performed. The on-
condition actions in Boeing Alert Requirements Bulletin 757-53A0113 RB,
dated February 22, 2019, then specify that if a repair in the
inspection area is found to contact Boeing for alternative inspections
and then to do those inspections and any corrective actions, as
applicable. Paragraph (h) of this AD requires operators to do the
repair, or alternative inspections and applicable on-condition actions
using a method approved in accordance with the procedures specified in
paragraph (i) of this AD. In addition, Boeing Alert Requirements
Bulletin 757-53A0113 RB, dated February 22, 2019, specifies that
operators perform the inspections for cracks at the locations that did
not have repairs and provides figures that clearly define those
inspection areas. The FAA has not changed this AD in this regard.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule as proposed, except for minor
editorial changes. The FAA has determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin 757-53A0113 RB,
dated February 22, 2019. This service information describes procedures
for a general visual inspection of the fuselage frames with a cargo
liner support channel for any existing repair, repetitive surface HFEC
inspections of the fuselage frames with a cargo liner support channel
for any cracking, and applicable on-condition actions. On-condition
actions include a general visual inspection of the fuselage frames
adjacent to a frame with a severed inner chord for any existing repair,
a detailed inspection and a surface HFEC inspection of the fuselage
frames adjacent to a frame with a severed inner chord for any cracking,
and repair. This service information is reasonably available because
the interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 544 airplanes of U.S.
registry.
[[Page 17486]]
The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
General visual inspection........ 37 work-hours x $85 $0 $3,145............. $1,710,880.
per hour = $3,145.
Repetitive surface HFEC Up to 37 work-hours 0 Up to $3,145 per Up to $1,710,880
inspections. x $85 per hour = inspection cycle. per inspection
Up to $3,145 per cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition inspections that would be required. The FAA has no way of
determining the number of aircraft that might need these on-condition
inspections:
Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Up to 20 work-hour x $85 per hour = Up to $1,700 per $0 Up to $1,700 per inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data that would enable the
agency to provide cost estimates for the on-condition repair specified
in this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2020-05-25 The Boeing Company: Amendment 39-19875; Docket No. FAA-
2019-0438; Product Identifier 2019-NM-033-AD.
(a) Effective Date
This AD is effective May 4, 2020.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing Company Model 757-200, -
200PF, -200CB, and -300 series airplanes, certificated in any
category.
(2) Installation of Supplemental Type Certificate (STC)
ST01518SE does not affect the ability to accomplish the actions
required by this AD. Therefore, for airplanes on which STC ST01518SE
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 a report that during a maintenance check
an operator discovered cracking of the aft cargo compartment frames
in the station 1460 frame web and inner chord between certain
stringers. The FAA is issuing this AD to address cracking at the
frame web and inner chord; such cracks could propagate until they
cause a severed frame, which could result in additional undetected
cracking in adjacent fuselage frames, and could ultimately result in
reduced structural integrity of the aft cargo frames and consequent
rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) Except as specified by paragraphs (g)(2) and (h) of this AD:
At the applicable times specified in the ``Compliance'' paragraph of
Boeing Alert Requirements Bulletin 757-53A0113 RB, dated February
22, 2019, do all applicable actions identified in, and in accordance
with, the Accomplishment Instructions of Boeing Alert Requirements
Bulletin 757-53A0113 RB, dated February 22, 2019.
(2) For airplanes that have been converted from a passenger to
freighter configuration using VT Mobile Aerospace Engineering Inc.
(VT MAE Inc.) STC ST03562AT: Except as specified by paragraph (h) of
this AD, at the times specified for Groups 3 and 5 airplanes, as
applicable, in the ``Compliance'' paragraph of Boeing Alert
Requirements Bulletin 757-53A0113 RB, dated February 22, 2019, do
all
[[Page 17487]]
applicable actions for Groups 2, 7, and 10 airplanes as identified
in, and in accordance with the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 757-53A0113 RB, dated February 22, 2019.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
757-53A0113, dated February 22, 2019, which is referred to in Boeing
Alert Requirements Bulletin 757-53A0113 RB, dated February 22, 2019.
(h) Exceptions To Service Information Specifications
(1) Where Boeing Alert Requirements Bulletin 757-53A0113 RB,
dated February 22, 2019, uses the phrase ``the original issue date
of Requirements Bulletin 757-53A0113 RB,'' this AD requires using
``the effective date of this AD,'' except where Boeing Alert
Requirements Bulletin 757-53A0113 RB, dated February 22, 2019, uses
the phrase ``the original issue date of Requirements Bulletin 757-
53A0113 RB'' in a note or flag note.
(2) Where Boeing Alert Requirements Bulletin 757-53A0113 RB,
dated February 22, 2019, specifies contacting Boeing for repair
instructions or for alternative inspections: This AD requires doing
the repair, or doing the alternative inspections and applicable on-
condition actions before further flight using a method approved in
accordance with the procedures specified in paragraph (i) of this
AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO Branch, FAA, has the authority
to approve AMOCs for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
request to your principal inspector or local Flight Standards
District Office, as appropriate. If sending information directly to
the manager of the certification office, send it to the attention of
the person identified in paragraph (j)(1) of this AD. Information
may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Los
Angeles ACO Branch, FAA, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(j) Related Information
(1) For more information about this AD, contact Peter Jarzomb,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5234; fax: 562-627-5210; email: [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (k)(3) and (4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Requirements Bulletin 757-53A0113 RB, dated
February 22, 2019.
(ii) [Reserved]
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on March 10, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020-06508 Filed 3-27-20; 8:45 am]
BILLING CODE 4910-13-P
