Airworthiness Directives; The Boeing Company Airplanes, 63002-63006 [2020-21994]
Download as PDF
<![CDATA[
63002
Federal Register / Vol. 85, No. 194 / Tuesday, October 6, 2020 / Rules and Regulations
including any circuits that might pass
through a main fuel tank, from other airplane
wiring that is not intrinsically safe, and do
all applicable corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 767–
28–0122, Revision 1, dated February 26,
2020. Do all applicable corrective actions
before further flight.
(i) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (h)(2)(ii) of
this AD, if those actions were performed
before the effective date of this AD using
Boeing Service Bulletin 767–28–0122, dated
October 11, 2016.
khammond on DSKJM1Z7X2PROD with RULES
(j) 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 (k)(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.
(4) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (j)(4)(i) and (ii) apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(k) Related Information
(1) For more information about this AD,
contact Jon Regimbal, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3557;
email: Jon.Regimbal@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
VerDate Sep<11>2014
16:34 Oct 05, 2020
Jkt 253001
available at the addresses specified in
paragraphs (l)(3) and (4) of this AD.
(l) 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 Service Bulletin 767–28–0118,
dated July 15, 2014.
(ii) Boeing Service Bulletin 767–28–0122,
Revision 1, dated February 26, 2020.
(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, 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.
(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 August 26, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–21997 Filed 10–5–20; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0094; Product
Identifier 2019–NM–188–AD; Amendment
39–21266; AD 2020–20–10]
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) 2018–06–
07, which applied to certain The Boeing
Company Model 757–200, –200CB, and
–300 series airplanes. AD 2018–06–07
required inspecting the fuselage frame at
a certain station for existing repairs,
repetitive inspections, and applicable
repairs. This AD requires the actions in
AD 2018–06–07, with an expanded
SUMMARY:
PO 00000
Frm 00070
Fmt 4700
Sfmt 4700
inspection area, additional inspections,
a modified inspection type, and
applicable repairs. This AD was
prompted by a report of fatigue cracking
found in the fuselage frame at a certain
station, which severed the inner chord
and web. The FAA is issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective November
10, 2020.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 10, 2020.
ADDRESSES: For Boeing service
information identified in this final rule,
contact Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110 SK57, Seal Beach, CA 90740–5600;
phone: 562–797–1717; internet: https://
www.myboeingfleet.com. For Aviation
Partners Boeing service information
identified in this final rule, contact
Aviation Partners Boeing, 2811 S. 102nd
Street, Suite 200, Seattle, WA 98168;
phone: 206–830–7699; internet: https://
www.aviationpartnersboeing.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–2020–0094.
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–2020–
0094; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
any comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
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
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
E:\FR\FM\06OCR1.SGM
06OCR1
Federal Register / Vol. 85, No. 194 / Tuesday, October 6, 2020 / Rules and Regulations
part 39 to supersede AD 2018–06–07,
Amendment 39–19227 (83 FR 13398,
March 29, 2018) (‘‘AD 2018–06–07’’).
AD 2018–06–07 applied to all The
Boeing Company Model 757–200,
–200CB, and –300 series airplanes. The
NPRM published in the Federal
Register on February 18, 2020 (85 FR
8773). The NPRM was prompted by a
report of fatigue cracking found in the
fuselage frame at station (STA) 1640,
which severed the inner chord and web.
The NPRM proposed to continue to
require the actions in AD 2018–06–07.
The NPRM also proposed to require an
expanded inspection area, additional
inspections, a modified inspection type,
and applicable repairs. The FAA is
issuing this AD to address cracking of
the fuselage frame at STA 1640, which
could result in reduced structural
integrity of the airplane.
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.
Support for the NPRM
United Airlines stated concurrence
with the proposed actions in the NPRM.
FedEx Express expressed support for the
NPRM.
khammond on DSKJM1Z7X2PROD with RULES
Request To Clarify Repetitive Intervals
as a Function of Configuration and
Most Recent Inspections Accomplished
Boeing requested that the ‘‘Proposed
AD Requirements’’ paragraph of the
NPRM be revised to specify that the
repetitive intervals are a function of
both the configuration and the most
recent inspection option accomplished.
Boeing pointed out that the repeat
intervals in tables 2 through 11 of
Boeing Alert Service Bulletin 757–
53A0108, Revision 1, dated July 17,
2019, each provide two options for
repeat inspections, depending on
whether certain other inspections were
last accomplished. Boeing requested
that the following wording be used:
‘‘. . . depending on the configuration,
and the most recent inspection option
accomplished.’’
The FAA agrees that the requested
change would be an accurate
clarification. However, the ‘‘Proposed
AD Requirements’’ section is included
in an NPRM as background information
on the proposed requirements to
provide adequate information for the
public on which to comment. The
‘‘Proposed AD Requirements’’ section is
not included in the final rule. The FAA
has not changed this AD in this regard.
VerDate Sep<11>2014
16:34 Oct 05, 2020
Jkt 253001
Request To Clarify Estimated Costs for
Required Actions
Boeing requested that the FAA clarify
the estimated costs for the required
actions specified in the NPRM. Boeing
pointed out that the most significant
amount of time for the inspections is
open and close access, which would be
required for each inspection, unless the
inspections are combined. Boeing
mentioned that the estimated costs in
the NPRM only include these hours for
the repetitive high frequency eddy
current (HFEC) and low frequency eddy
current (LFEC) inspections, and
suggested separating the costs for open
and close access from the inspections.
Boeing also mentioned that the detailed
inspection is listed as taking 1 workhour, whereas the service information
specifies 0.20 hours per side of each
airplane. Boeing went on to point out
that the costs for the repetitive HFEC
and LFEC inspections in the NPRM
appear to include possible combinations
of inspections, and to include
inspections that are not repetitive.
Additionally, Boeing specified that the
service information contained some
mathematical errors in the manpower
estimates.
The FAA agrees to clarify the
estimated costs. The work hours
required for open and close access are
provided under the line item costs for
the repetitive HFEC and LFEC
inspections, as these are on-going
inspections required by this AD. The
work-hour estimates in this AD are
based on the service information
provided to the FAA by the
manufacturer; however, it is FAA policy
in ADs to round work-hour estimates up
to the next full hour. The FAA is unable
to predict whether operators will choose
to do Option 1 or Option 2 inspections,
thus the FAA estimates the highest costs
to do the required actions using the best
industry data available at the time of
publication. The cost estimates in this
final rule have been revised to indicate
that the costs could be ‘‘up to’’ the
highest number of work hours needed
for the specified actions.
Request for Matching Compliance
Times
American Airlines (AAL) requested
that the FAA revise the proposed
compliance times for the general visual
inspection and the detailed visual
inspection to match. AAL stated that the
compliance times for the two separate
actions should be the same to align with
CONDITION 2, specified in Aviation
Partners Boeing Service Bulletin
AP757–53–001, Revision 2, dated
PO 00000
Frm 00071
Fmt 4700
Sfmt 4700
63003
October 22, 2019. AAL did not provide
further reasoning.
The FAA disagrees with the request
for matching compliance times. The
compliance times do not need to match
to align with CONDITION 2, specified
in Aviation Partners Boeing Service
Bulletin AP757–53–001, Revision 2,
dated October 22, 2019. The general
visual inspection for repairs was
included in Aviation Partners Boeing
Alert Service Bulletin AP757–53–001,
Revision 1, dated June 21, 2017, and
mandated by AD 2018–06–07, and is
carried over from the requirements of
AD 2018–06–07. Aviation Partners
Boeing Service Bulletin AP757–53–001,
Revision 2, dated October 22, 2019,
introduced a new detailed visual
inspection for any crack, nick, or gouge,
which specifies a new grace period.
Both the general visual and detailed
visual inspections must be performed.
The FAA expects that most operators
will choose to do both the general visual
and detailed visual inspections at the
earlier compliance time, because the
inspections are in the same area and the
access requirements are the same;
however, from a safety perspective, the
inspections do not need to be performed
at the same time, and can be performed
at their respective compliance times.
This AD has not been changed in this
regard.
Request To Use Alternative Service
Information for Certain Modified
Airplanes
VT Mobile Aerospace Engineering
Inc. (VT MAE) requested that the FAA
allow inspection of certain passenger
airplanes converted to a specific
freighter configuration (VT MAE
Supplemental Type Certificate (STC)
ST04242AT, Passenger to 15-Pallet
Configuration) using VT MAE 15-Pallet
Maintenance Planning Data (MPD)
Supplement 757SF–MPD–01. VT MAE
pointed out that the STA 1640 frame is
completely modified (the existing
passenger frame is removed and new
frame section is installed). VT MAE also
pointed out that the 11866470 FRAME
INSTL–STA 1640 drawing is used for
the analysis, and that Boeing has
performed analysis of the modified
airplane, which also includes the
Fatigue and Damage Tolerance Analysis
of modified aft fuselage structures from
STA 1640 to STA 1720 to accommodate
15 full-size pallets. VT MAE then
specified that the new STA 1640 frame
is inspected as part of the VT MAE MPD
Supplement 757SF–MPD–01, which
specifies inspections for all of the
affected frames and also requires
inspection of this new STA 1640 frame
(left-hand and right-hand) at the frame
E:\FR\FM\06OCR1.SGM
06OCR1
63004
Federal Register / Vol. 85, No. 194 / Tuesday, October 6, 2020 / Rules and Regulations
inner chord and the frame web between
stringer (S) 16 and S–17. VT MAE also
mentioned its plan to submit a request
for approval of an alternative method of
compliance (AMOC) for airplanes
modified using VT MAE STC
ST04242AT.
The FAA acknowledges that airplanes
modified using VT MAE STC
ST04242AT are no longer configured as
passenger airplanes. However, the FAA
disagrees with the request to include
inspections using VT MAE MPD
Supplement 757SF–MPD–01 as an
appropriate source of service
information because sufficient data was
not submitted to substantiate that the
inspections specified in VT MAE MPD
Supplement 757SF–MPD–01 would
provide an acceptable level of safety.
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.
khammond on DSKJM1Z7X2PROD with RULES
Request To Refer to Airplanes Modified
Using Different STCs
VT MAE requested that the FAA
revise paragraphs (g)(3) and (4) of the
proposed AD to include reference to
airplanes modified using VT MAE STC
ST03952AT (Combi to 14-Pallet
Configuration). VT MAE explained that
the modification to the STA 1640 frame
is identical to that of Boeing Model 757–
200 special freighter airplanes identified
as Group 2 and Group 5 in Boeing Alert
Service Bulletin 757–53A0108, Revision
1, dated July 17, 2019. VT MAE pointed
out that the modification instructions
for the STA 1640 frame is contained in
Drawing 657N3160—Frame Instl—
Modified, Aft Pallet Mod. VT MAE also
proposed utilizing all of the inspections,
methods, and compliance times
specified in Boeing Alert Service
Bulletin 757–53A0108, Revision 1,
dated July 17, 2019, for those airplanes.
The FAA agrees for the reasons
provided and has revised paragraphs
(g)(3) and (4) of this AD to include
reference to airplanes modified using
VT MAE STC ST03952AT.
Request for Clarification of Interaction
of Certain Airplane Configurations
Aviation Partners Boeing (APB)
requested that the FAA clarify the
interaction of the configurations
specified in paragraphs (g)(2) and (3) of
the proposed AD (airplanes that have
been converted from passenger to
freighter configuration using VT MAE
STC ST03562AT, and on which APB
blended or scimitar blended winglets
VerDate Sep<11>2014
16:34 Oct 05, 2020
Jkt 253001
are installed using STC ST01518SE).
APB stated that it is not clear whether
the freighter configuration compliance
times or the winglet configuration
compliance times take precedence. APB
pointed out that STC ST01518SE was
not certified for a freighter configuration
(factory or STC). APB noted that other
STC holders have obtained FAA
approval for freighter conversion STCs
that include a statement of compatibility
with STC ST01518SE (e.g., ST03562AT,
ST04242AT, and ST01529SE). APB also
mentioned that Aviation Partners
Boeing Alert Service Bulletin AP757–
53–001, Revision 2, dated October 22,
2019, reduces the compliance times for
airplanes identified as Group 1 or Group
3 in Boeing Alert Service Bulletin 757–
53A0108, Revision 1, dated July 17,
2019. APB explained that the
compliance time reduction is based
solely on the interaction of STC
ST01518SE with the Boeing type
certificated configuration, and does not
include effects from any other STCs.
APB also stated that Group 4 airplanes
are not eligible to install STC
ST01518SE, and therefore, there is no
conflict for Group 4 airplanes. APB
requested that the FAA modify
paragraph (g)(2) of the proposed AD to
exclude airplanes identified in
paragraph (g)(3) of the proposed AD.
The FAA agrees that it is possible for
both STC ST03562AT and STC
ST01518SE to be incorporated on the
same airplane. However, the FAA does
not agree that revising paragraph (g)(2)
of this AD as requested by the
commenter is appropriate. The FAA
acknowledges that the compliance times
for airplanes with APB winglets
installed were developed based solely
on the interaction of STC ST01518SE
with the Boeing type certificated
configuration. However, the FAA also
acknowledges that the effects of
installing APB winglets on Model 757–
200 passenger airplanes converted to
freighter configuration in accordance
with VT MAE STC ST03562AT have not
been evaluated, and that sufficient data
was not submitted to substantiate any
positive or negative effects on the unsafe
condition. The FAA has therefore added
paragraph (g)(5) to this AD to
specifically address airplanes with both
STCs installed.
Request To Allow Certain AMOCs
FedEx Express requested that the FAA
allow certain AMOCs approved for AD
2018–06–07, including local frame
replacements. FedEx Express stated that
it defines a local frame replacement as
a frame repair splice between stringers
S–9 and S–20 along the STA 1640
fuselage frame, and explained that the
PO 00000
Frm 00072
Fmt 4700
Sfmt 4700
local frame replacement replaces the
entire inspection area and does not
interfere with the inspections specified
in the NPRM. FedEx Express pointed
out that its fleet has several local frame
replacements along the STA 1640
fuselage frame that have AMOC
approval for AD 2018–06–07. FedEx
Express also pointed out that it would
be required to request new AMOCs for
the existing repairs, possibly extending
ground time for its fleet.
The FAA agrees for the reasons
provided and has included paragraph
(i)(5) of this AD to specifically allow
AMOCs approved in FAA Letters 790–
18–8737, 790–18–9637, 790–18–10097,
790–18–10177, and 790–20–10108, as
AMOCs for certain actions required by
this AD. The FAA has also included
paragraph (g)(6) of this AD to provide
inspection instructions for Group 1
airplanes that have been converted from
passenger to freighter configuration
using VT MAE STC ST03562AT or STC
ST03952AT and that have local frame
replacements that do not include a
reinforcement repair or repair splice
member between stringers S–11 and S–
16 as specified in FAA AMOC approval
Letters 790–18–8737, 790–18–9637,
790–18–10097, 790–18–10177, and 790–
20–10108.
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 Alert
Service Bulletin 757–53A0108, Revision
1, dated July 17, 2019. This service
information describes procedures for an
inspection of the STA 1640 fuselage
frame between S–11 and S–16 for
existing frame repairs or replacements,
a detailed inspection for any crack, nick,
or gouge, and repetitive HFEC and LFEC
inspections for cracking and repair.
The FAA also reviewed Aviation
Partners Boeing Alert Service Bulletin
AP757–53–001, Revision 2, dated
E:\FR\FM\06OCR1.SGM
06OCR1
Federal Register / Vol. 85, No. 194 / Tuesday, October 6, 2020 / Rules and Regulations
October 22, 2019. This service
information provides compliance times
for accomplishing the procedures
identified in Boeing Alert Service
Bulletin 757–53A0108, Revision 1,
dated July 17, 2019, for airplanes on
63005
Costs of Compliance
which APB blended or scimitar blended
winglets are installed.
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.
The FAA estimates that this AD
affects 606 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Inspection for existing frame repairs or replacements.
Detailed inspection ........................................
Repetitive high and low frequency inspections for Groups 1 through 3 airplanes
(598 airplanes).
Repetitive high and low frequency inspections for Groups 4 and 5 airplanes (8 airplanes).
1 work-hour × $85 per hour =
$85.
1 work-hour × $85 per hour .......
Up to 54 work-hours × $85 per
hour = Up to $4,590 per inspection cycle.
Up to 48 work-hours × $85 per
hour = Up to $4,080 per inspection cycle.
The FAA has received no definitive
data that would enable the FAA to
provide cost estimates for the oncondition repair specified in this AD.
khammond on DSKJM1Z7X2PROD with RULES
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
VerDate Sep<11>2014
16:34 Oct 05, 2020
Jkt 253001
Parts cost
Cost per product
$0
$85 ............................
$51,510.
0
0
$85 ............................
Up to $4,590 per inspection cycle.
$51,510.
Up to $2,744,820 per
inspection cycle.
0
Up to $4,080 per inspection cycle.
Up to $32,640 per inspection cycle.
(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
removing Airworthiness Directive (AD)
2018–06–07, Amendment 39–19227 (83
FR 13398, March 29, 2018), and adding
the following new AD:
■
2020–20–10 The Boeing Company:
Amendment 39–21266; Docket No.
FAA–2020–0094; Product Identifier
2019–NM–188–AD.
(a) Effective Date
This AD is effective November 10, 2020.
(b) Affected ADs
This AD replaces AD 2018–06–07,
Amendment 39–19227 (83 FR 13398, March
29, 2018) (‘‘AD 2018–06–07’’).
(c) Applicability
This AD applies to all The Boeing
Company Model 757–200, –200CB, and –300
series airplanes, certificated in any category.
PO 00000
Frm 00073
Fmt 4700
Sfmt 4700
Cost on U.S.
operators
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of
fatigue cracking found in the fuselage frame
at station (STA) 1640, which severed the
inner chord and web. The FAA is issuing this
AD to address cracking of the fuselage frame
at STA 1640, which could result in reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Actions Required for Compliance
(1) For all airplanes except those identified
in paragraphs (g)(2) through (6) of this AD:
Except as specified by paragraph (h) of this
AD, at the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 757–53A0108,
Revision 1, dated July 17, 2019, do all
applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin
757–53A0108, Revision 1, dated July 17,
2019.
(2) For airplanes on which Aviation
Partners Boeing (APB) blended or scimitar
blended winglets are installed using
Supplemental Type Certificate (STC)
ST01518SE: Except as specified by paragraph
(h) of this AD, at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
Aviation Partners Boeing Alert Service
Bulletin AP757–53–001, Revision 2, dated
October 22, 2019, do all applicable actions
identified as ‘‘RC’’ in, and in accordance
with, the Accomplishment Instructions of
Aviation Partners Boeing Alert Service
Bulletin AP757–53–001, Revision 2, dated
October 22, 2019.
(3) For Group 1 airplanes that have been
converted from passenger to freighter
configuration using VT Mobile Aerospace
Engineering Inc. (VT MAE) STC ST03562AT
E:\FR\FM\06OCR1.SGM
06OCR1
63006
Federal Register / Vol. 85, No. 194 / Tuesday, October 6, 2020 / Rules and Regulations
khammond on DSKJM1Z7X2PROD with RULES
or STC ST03952AT: Except as specified by
paragraph (h) of this AD, at the applicable
times specified for Group 2 airplanes in the
‘‘Compliance’’ paragraph of Boeing Alert
Service Bulletin 757–53A0108, Revision 1,
dated July 17, 2019, do all applicable Group
2 actions, as identified in, and in accordance
with, the Accomplishment Instructions of
Boeing Alert Service Bulletin 757–53A0108,
Revision 1, dated July 17, 2019.
(4) For Group 4 airplanes that have been
converted from a passenger to freighter
configuration using VT MAE STC
ST03562AT or VT MAE STC ST03952AT:
Except as specified by paragraph (h) of this
AD, at the applicable times specified for
Group 5 airplanes in the ‘‘Compliance’’
paragraph of Boeing Alert Service Bulletin
757–53A0108, Revision 1, dated July 17,
2019, do all applicable Group 5 actions as
identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Service Bulletin 757–53A0108, Revision 1,
dated July 17, 2019.
(5) For Group 1 airplanes that have been
converted from passenger to freighter
configuration using VT MAE STC
ST03562AT, and on which APB blended or
scimitar blended winglets were installed
using STC ST01518SE: Except as specified by
paragraph (h) of this AD, before further flight,
do all applicable actions using a method
approved in accordance with the procedures
specified in paragraph (i) of this AD.
(6) For Group 1 airplanes that have been
converted from passenger to freighter
configuration using VT MAE STC
ST03562AT and that have local frame
replacements that do not include a
reinforcement repair or repair splice member
between stringers S–11 and S–16 as specified
in FAA AMOC approval Letters 790–18–
8737, 790–18–9637, 790–18–10097, 790–18–
10177, and 790–20–10108: Do the actions
required by paragraph (g)(3) of this AD;
except where paragraph (g)(3) requires to do
the applicable actions for Group 2,
Configuration 2, CONDITION 3, specified in
Boeing Alert Service Bulletin 757–53A0108,
Revision 1, dated July 17, 2019, do the
actions for Group 2, Configuration 2,
CONDITION 4, and follow-on actions
instead.
(h) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
757–53A0108, Revision 1, dated July 17,
2019, specifies contacting Boeing for repair
instructions or for alternative inspections:
This AD requires doing the repair, or doing
the alternative inspections and applicable oncondition actions using a method approved
in accordance with the procedures specified
in paragraph (i) of this AD.
(2) Where Boeing Alert Service Bulletin
757–53A0108, Revision 1, dated July 17,
2019, uses the phrase ‘‘the original issue date
of this service bulletin,’’ this AD requires
using ‘‘May 3, 2018 (the effective date of AD
2018–06–07),’’ except where Boeing Alert
Service Bulletin 757–53A0108, Revision 1,
dated July 17, 2019, uses the phrase ‘‘the
original issue date of this service bulletin’’ in
a note or flag note.
(3) Where Boeing Alert Service Bulletin
757–53A0108, Revision 1, dated July 17,
VerDate Sep<11>2014
16:34 Oct 05, 2020
Jkt 253001
2019, uses the phrase ‘‘the revision 1 date of
this service bulletin,’’ this AD requires using
‘‘the effective date of this AD.’’
(4) Where Aviation Partners Boeing Alert
Service Bulletin AP757–53–001, Revision 2,
dated October 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, using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
(5) Where Aviation Partners Boeing Alert
Service Bulletin AP757–53–001, Revision 2,
dated October 22, 2019, uses the phrase ‘‘the
revision 1 issue date of this service bulletin,’’
this AD requires using ‘‘May 3, 2018 (the
effective date of AD 2018–06–07),’’ except
where Aviation Partners Boeing Alert Service
Bulletin AP757–53–001, Revision 2, dated
October 22, 2019, uses the phrase ‘‘the
revision 1 issue date of this service bulletin’’
in a note or flag note.
(6) Where Aviation Partners Boeing Alert
Service Bulletin AP757–53–001, Revision 2,
dated October 22, 2019, uses the phrase ‘‘the
revision 2 issue date of this service bulletin,’’
this AD requires using ‘‘the effective date 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) of this
AD. Information may be emailed to: 9-ANMLAACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Los Angeles ACO Branch, FAA, to
make those findings. To be approved, the
repair method, modification deviation, or
alteration deviation must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as specified in paragraph (i)(5)
of this AD, AMOCs approved previously for
AD 2018–06–07 are not approved as AMOCs
for the corresponding provisions of this AD.
(5) AMOCs approved in FAA Letters 790–
18–8737, 790–18–9637, 790–18–10097, 790–
18–10177, and 790–20–10108, are approved
as AMOCs for this AD.
(6) Except as specified by paragraph (h) of
this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (i)(6)(i) and (ii) of this AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
PO 00000
Frm 00074
Fmt 4700
Sfmt 4700
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(j) Related Information
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.
(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) Aviation Partners Boeing Alert Service
Bulletin AP757–53–001, Revision 2, dated
October 22, 2019.
(ii) Boeing Alert Service Bulletin 757–
53A0108, Revision 1, dated July 17, 2019.
(3) For Aviation Partners Boeing service
information identified in this AD, contact
Aviation Partners Boeing, 2811 S 102nd
Street, Suite 200, Seattle, WA 98168; phone:
206 830 7699; internet: https://www.aviation
partnersboeing.com.
(4) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS), 2600
Westminster Blvd., MC 110 SK57, Seal
Beach, CA 90740–5600; phone: 562–797–
1717; internet: https://
www.myboeingfleet.com.
(5) You may view this service information
at the FAA, 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.
(6) 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 September 23, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–21994 Filed 10–5–20; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\06OCR1.SGM
06OCR1
]]>Agencies
[Federal Register Volume 85, Number 194 (Tuesday, October 6, 2020)]
[Rules and Regulations]
[Pages 63002-63006]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-21994]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0094; Product Identifier 2019-NM-188-AD; Amendment
39-21266; AD 2020-20-10]
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) 2018-06-
07, which applied to certain The Boeing Company Model 757-200, -200CB,
and -300 series airplanes. AD 2018-06-07 required inspecting the
fuselage frame at a certain station for existing repairs, repetitive
inspections, and applicable repairs. This AD requires the actions in AD
2018-06-07, with an expanded inspection area, additional inspections, a
modified inspection type, and applicable repairs. This AD was prompted
by a report of fatigue cracking found in the fuselage frame at a
certain station, which severed the inner chord and web. The FAA is
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective November 10, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 10,
2020.
ADDRESSES: For Boeing service information identified in this final
rule, contact Boeing Commercial Airplanes, Attention: Contractual &
Data Services (C&DS), 2600 Westminster Blvd., MC 110 SK57, Seal Beach,
CA 90740-5600; phone: 562-797-1717; internet: https://www.myboeingfleet.com. For Aviation Partners Boeing service information
identified in this final rule, contact Aviation Partners Boeing, 2811
S. 102nd Street, Suite 200, Seattle, WA 98168; phone: 206-830-7699;
internet: https://www.aviationpartnersboeing.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-
0094.
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-2020-
0094; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, any comments received, and other information. The
address for Docket Operations is U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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
[[Page 63003]]
part 39 to supersede AD 2018-06-07, Amendment 39-19227 (83 FR 13398,
March 29, 2018) (``AD 2018-06-07''). AD 2018-06-07 applied to all The
Boeing Company Model 757-200, -200CB, and -300 series airplanes. The
NPRM published in the Federal Register on February 18, 2020 (85 FR
8773). The NPRM was prompted by a report of fatigue cracking found in
the fuselage frame at station (STA) 1640, which severed the inner chord
and web. The NPRM proposed to continue to require the actions in AD
2018-06-07. The NPRM also proposed to require an expanded inspection
area, additional inspections, a modified inspection type, and
applicable repairs. The FAA is issuing this AD to address cracking of
the fuselage frame at STA 1640, which could result in reduced
structural integrity of the airplane.
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.
Support for the NPRM
United Airlines stated concurrence with the proposed actions in the
NPRM. FedEx Express expressed support for the NPRM.
Request To Clarify Repetitive Intervals as a Function of Configuration
and Most Recent Inspections Accomplished
Boeing requested that the ``Proposed AD Requirements'' paragraph of
the NPRM be revised to specify that the repetitive intervals are a
function of both the configuration and the most recent inspection
option accomplished. Boeing pointed out that the repeat intervals in
tables 2 through 11 of Boeing Alert Service Bulletin 757-53A0108,
Revision 1, dated July 17, 2019, each provide two options for repeat
inspections, depending on whether certain other inspections were last
accomplished. Boeing requested that the following wording be used: ``.
. . depending on the configuration, and the most recent inspection
option accomplished.''
The FAA agrees that the requested change would be an accurate
clarification. However, the ``Proposed AD Requirements'' section is
included in an NPRM as background information on the proposed
requirements to provide adequate information for the public on which to
comment. The ``Proposed AD Requirements'' section is not included in
the final rule. The FAA has not changed this AD in this regard.
Request To Clarify Estimated Costs for Required Actions
Boeing requested that the FAA clarify the estimated costs for the
required actions specified in the NPRM. Boeing pointed out that the
most significant amount of time for the inspections is open and close
access, which would be required for each inspection, unless the
inspections are combined. Boeing mentioned that the estimated costs in
the NPRM only include these hours for the repetitive high frequency
eddy current (HFEC) and low frequency eddy current (LFEC) inspections,
and suggested separating the costs for open and close access from the
inspections. Boeing also mentioned that the detailed inspection is
listed as taking 1 work-hour, whereas the service information specifies
0.20 hours per side of each airplane. Boeing went on to point out that
the costs for the repetitive HFEC and LFEC inspections in the NPRM
appear to include possible combinations of inspections, and to include
inspections that are not repetitive. Additionally, Boeing specified
that the service information contained some mathematical errors in the
manpower estimates.
The FAA agrees to clarify the estimated costs. The work hours
required for open and close access are provided under the line item
costs for the repetitive HFEC and LFEC inspections, as these are on-
going inspections required by this AD. The work-hour estimates in this
AD are based on the service information provided to the FAA by the
manufacturer; however, it is FAA policy in ADs to round work-hour
estimates up to the next full hour. The FAA is unable to predict
whether operators will choose to do Option 1 or Option 2 inspections,
thus the FAA estimates the highest costs to do the required actions
using the best industry data available at the time of publication. The
cost estimates in this final rule have been revised to indicate that
the costs could be ``up to'' the highest number of work hours needed
for the specified actions.
Request for Matching Compliance Times
American Airlines (AAL) requested that the FAA revise the proposed
compliance times for the general visual inspection and the detailed
visual inspection to match. AAL stated that the compliance times for
the two separate actions should be the same to align with CONDITION 2,
specified in Aviation Partners Boeing Service Bulletin AP757-53-001,
Revision 2, dated October 22, 2019. AAL did not provide further
reasoning.
The FAA disagrees with the request for matching compliance times.
The compliance times do not need to match to align with CONDITION 2,
specified in Aviation Partners Boeing Service Bulletin AP757-53-001,
Revision 2, dated October 22, 2019. The general visual inspection for
repairs was included in Aviation Partners Boeing Alert Service Bulletin
AP757-53-001, Revision 1, dated June 21, 2017, and mandated by AD 2018-
06-07, and is carried over from the requirements of AD 2018-06-07.
Aviation Partners Boeing Service Bulletin AP757-53-001, Revision 2,
dated October 22, 2019, introduced a new detailed visual inspection for
any crack, nick, or gouge, which specifies a new grace period. Both the
general visual and detailed visual inspections must be performed. The
FAA expects that most operators will choose to do both the general
visual and detailed visual inspections at the earlier compliance time,
because the inspections are in the same area and the access
requirements are the same; however, from a safety perspective, the
inspections do not need to be performed at the same time, and can be
performed at their respective compliance times. This AD has not been
changed in this regard.
Request To Use Alternative Service Information for Certain Modified
Airplanes
VT Mobile Aerospace Engineering Inc. (VT MAE) requested that the
FAA allow inspection of certain passenger airplanes converted to a
specific freighter configuration (VT MAE Supplemental Type Certificate
(STC) ST04242AT, Passenger to 15-Pallet Configuration) using VT MAE 15-
Pallet Maintenance Planning Data (MPD) Supplement 757SF-MPD-01. VT MAE
pointed out that the STA 1640 frame is completely modified (the
existing passenger frame is removed and new frame section is
installed). VT MAE also pointed out that the 11866470 FRAME INSTL-STA
1640 drawing is used for the analysis, and that Boeing has performed
analysis of the modified airplane, which also includes the Fatigue and
Damage Tolerance Analysis of modified aft fuselage structures from STA
1640 to STA 1720 to accommodate 15 full-size pallets. VT MAE then
specified that the new STA 1640 frame is inspected as part of the VT
MAE MPD Supplement 757SF-MPD-01, which specifies inspections for all of
the affected frames and also requires inspection of this new STA 1640
frame (left-hand and right-hand) at the frame
[[Page 63004]]
inner chord and the frame web between stringer (S) 16 and S-17. VT MAE
also mentioned its plan to submit a request for approval of an
alternative method of compliance (AMOC) for airplanes modified using VT
MAE STC ST04242AT.
The FAA acknowledges that airplanes modified using VT MAE STC
ST04242AT are no longer configured as passenger airplanes. However, the
FAA disagrees with the request to include inspections using VT MAE MPD
Supplement 757SF-MPD-01 as an appropriate source of service information
because sufficient data was not submitted to substantiate that the
inspections specified in VT MAE MPD Supplement 757SF-MPD-01 would
provide an acceptable level of safety. 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.
Request To Refer to Airplanes Modified Using Different STCs
VT MAE requested that the FAA revise paragraphs (g)(3) and (4) of
the proposed AD to include reference to airplanes modified using VT MAE
STC ST03952AT (Combi to 14-Pallet Configuration). VT MAE explained that
the modification to the STA 1640 frame is identical to that of Boeing
Model 757-200 special freighter airplanes identified as Group 2 and
Group 5 in Boeing Alert Service Bulletin 757-53A0108, Revision 1, dated
July 17, 2019. VT MAE pointed out that the modification instructions
for the STA 1640 frame is contained in Drawing 657N3160--Frame Instl--
Modified, Aft Pallet Mod. VT MAE also proposed utilizing all of the
inspections, methods, and compliance times specified in Boeing Alert
Service Bulletin 757-53A0108, Revision 1, dated July 17, 2019, for
those airplanes.
The FAA agrees for the reasons provided and has revised paragraphs
(g)(3) and (4) of this AD to include reference to airplanes modified
using VT MAE STC ST03952AT.
Request for Clarification of Interaction of Certain Airplane
Configurations
Aviation Partners Boeing (APB) requested that the FAA clarify the
interaction of the configurations specified in paragraphs (g)(2) and
(3) of the proposed AD (airplanes that have been converted from
passenger to freighter configuration using VT MAE STC ST03562AT, and on
which APB blended or scimitar blended winglets are installed using STC
ST01518SE). APB stated that it is not clear whether the freighter
configuration compliance times or the winglet configuration compliance
times take precedence. APB pointed out that STC ST01518SE was not
certified for a freighter configuration (factory or STC). APB noted
that other STC holders have obtained FAA approval for freighter
conversion STCs that include a statement of compatibility with STC
ST01518SE (e.g., ST03562AT, ST04242AT, and ST01529SE). APB also
mentioned that Aviation Partners Boeing Alert Service Bulletin AP757-
53-001, Revision 2, dated October 22, 2019, reduces the compliance
times for airplanes identified as Group 1 or Group 3 in Boeing Alert
Service Bulletin 757-53A0108, Revision 1, dated July 17, 2019. APB
explained that the compliance time reduction is based solely on the
interaction of STC ST01518SE with the Boeing type certificated
configuration, and does not include effects from any other STCs. APB
also stated that Group 4 airplanes are not eligible to install STC
ST01518SE, and therefore, there is no conflict for Group 4 airplanes.
APB requested that the FAA modify paragraph (g)(2) of the proposed AD
to exclude airplanes identified in paragraph (g)(3) of the proposed AD.
The FAA agrees that it is possible for both STC ST03562AT and STC
ST01518SE to be incorporated on the same airplane. However, the FAA
does not agree that revising paragraph (g)(2) of this AD as requested
by the commenter is appropriate. The FAA acknowledges that the
compliance times for airplanes with APB winglets installed were
developed based solely on the interaction of STC ST01518SE with the
Boeing type certificated configuration. However, the FAA also
acknowledges that the effects of installing APB winglets on Model 757-
200 passenger airplanes converted to freighter configuration in
accordance with VT MAE STC ST03562AT have not been evaluated, and that
sufficient data was not submitted to substantiate any positive or
negative effects on the unsafe condition. The FAA has therefore added
paragraph (g)(5) to this AD to specifically address airplanes with both
STCs installed.
Request To Allow Certain AMOCs
FedEx Express requested that the FAA allow certain AMOCs approved
for AD 2018-06-07, including local frame replacements. FedEx Express
stated that it defines a local frame replacement as a frame repair
splice between stringers S-9 and S-20 along the STA 1640 fuselage
frame, and explained that the local frame replacement replaces the
entire inspection area and does not interfere with the inspections
specified in the NPRM. FedEx Express pointed out that its fleet has
several local frame replacements along the STA 1640 fuselage frame that
have AMOC approval for AD 2018-06-07. FedEx Express also pointed out
that it would be required to request new AMOCs for the existing
repairs, possibly extending ground time for its fleet.
The FAA agrees for the reasons provided and has included paragraph
(i)(5) of this AD to specifically allow AMOCs approved in FAA Letters
790-18-8737, 790-18-9637, 790-18-10097, 790-18-10177, and 790-20-10108,
as AMOCs for certain actions required by this AD. The FAA has also
included paragraph (g)(6) of this AD to provide inspection instructions
for Group 1 airplanes that have been converted from passenger to
freighter configuration using VT MAE STC ST03562AT or STC ST03952AT and
that have local frame replacements that do not include a reinforcement
repair or repair splice member between stringers S-11 and S-16 as
specified in FAA AMOC approval Letters 790-18-8737, 790-18-9637, 790-
18-10097, 790-18-10177, and 790-20-10108.
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 Alert Service Bulletin 757-53A0108,
Revision 1, dated July 17, 2019. This service information describes
procedures for an inspection of the STA 1640 fuselage frame between S-
11 and S-16 for existing frame repairs or replacements, a detailed
inspection for any crack, nick, or gouge, and repetitive HFEC and LFEC
inspections for cracking and repair.
The FAA also reviewed Aviation Partners Boeing Alert Service
Bulletin AP757-53-001, Revision 2, dated
[[Page 63005]]
October 22, 2019. This service information provides compliance times
for accomplishing the procedures identified in Boeing Alert Service
Bulletin 757-53A0108, Revision 1, dated July 17, 2019, for airplanes on
which APB blended or scimitar blended winglets are installed.
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 606 airplanes of U.S.
registry. 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
----------------------------------------------------------------------------------------------------------------
Inspection for existing frame 1 work-hour x $85 $0 $85................ $51,510.
repairs or replacements. per hour = $85.
Detailed inspection.............. 1 work-hour x $85 0 $85................ $51,510.
per hour.
Repetitive high and low frequency Up to 54 work-hours 0 Up to $4,590 per Up to $2,744,820
inspections for Groups 1 through x $85 per hour = inspection cycle. per inspection
3 airplanes (598 airplanes). Up to $4,590 per cycle.
inspection cycle.
Repetitive high and low frequency Up to 48 work-hours 0 Up to $4,080 per Up to $32,640 per
inspections for Groups 4 and 5 x $85 per hour = inspection cycle. inspection cycle.
airplanes (8 airplanes). Up to $4,080 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data that would enable the FAA
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
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
(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 removing Airworthiness Directive (AD)
2018-06-07, Amendment 39-19227 (83 FR 13398, March 29, 2018), and
adding the following new AD:
2020-20-10 The Boeing Company: Amendment 39-21266; Docket No. FAA-
2020-0094; Product Identifier 2019-NM-188-AD.
(a) Effective Date
This AD is effective November 10, 2020.
(b) Affected ADs
This AD replaces AD 2018-06-07, Amendment 39-19227 (83 FR 13398,
March 29, 2018) (``AD 2018-06-07'').
(c) Applicability
This AD applies to all The Boeing Company Model 757-200, -200CB,
and -300 series airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of fatigue cracking found in
the fuselage frame at station (STA) 1640, which severed the inner
chord and web. The FAA is issuing this AD to address cracking of the
fuselage frame at STA 1640, which could result in reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions Required for Compliance
(1) For all airplanes except those identified in paragraphs
(g)(2) through (6) of this AD: Except as specified by paragraph (h)
of this AD, at the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 757-53A0108,
Revision 1, dated July 17, 2019, do all applicable actions
identified as ``RC'' (required for compliance) in, and in accordance
with, the Accomplishment Instructions of Boeing Alert Service
Bulletin 757-53A0108, Revision 1, dated July 17, 2019.
(2) For airplanes on which Aviation Partners Boeing (APB)
blended or scimitar blended winglets are installed using
Supplemental Type Certificate (STC) ST01518SE: Except as specified
by paragraph (h) of this AD, at the applicable times specified in
paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Alert
Service Bulletin AP757-53-001, Revision 2, dated October 22, 2019,
do all applicable actions identified as ``RC'' in, and in accordance
with, the Accomplishment Instructions of Aviation Partners Boeing
Alert Service Bulletin AP757-53-001, Revision 2, dated October 22,
2019.
(3) For Group 1 airplanes that have been converted from
passenger to freighter configuration using VT Mobile Aerospace
Engineering Inc. (VT MAE) STC ST03562AT
[[Page 63006]]
or STC ST03952AT: Except as specified by paragraph (h) of this AD,
at the applicable times specified for Group 2 airplanes in the
``Compliance'' paragraph of Boeing Alert Service Bulletin 757-
53A0108, Revision 1, dated July 17, 2019, do all applicable Group 2
actions, as identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
53A0108, Revision 1, dated July 17, 2019.
(4) For Group 4 airplanes that have been converted from a
passenger to freighter configuration using VT MAE STC ST03562AT or
VT MAE STC ST03952AT: Except as specified by paragraph (h) of this
AD, at the applicable times specified for Group 5 airplanes in the
``Compliance'' paragraph of Boeing Alert Service Bulletin 757-
53A0108, Revision 1, dated July 17, 2019, do all applicable Group 5
actions as identified in, and in accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin 757-53A0108, Revision
1, dated July 17, 2019.
(5) For Group 1 airplanes that have been converted from
passenger to freighter configuration using VT MAE STC ST03562AT, and
on which APB blended or scimitar blended winglets were installed
using STC ST01518SE: Except as specified by paragraph (h) of this
AD, before further flight, do all applicable actions using a method
approved in accordance with the procedures specified in paragraph
(i) of this AD.
(6) For Group 1 airplanes that have been converted from
passenger to freighter configuration using VT MAE STC ST03562AT and
that have local frame replacements that do not include a
reinforcement repair or repair splice member between stringers S-11
and S-16 as specified in FAA AMOC approval Letters 790-18-8737, 790-
18-9637, 790-18-10097, 790-18-10177, and 790-20-10108: Do the
actions required by paragraph (g)(3) of this AD; except where
paragraph (g)(3) requires to do the applicable actions for Group 2,
Configuration 2, CONDITION 3, specified in Boeing Alert Service
Bulletin 757-53A0108, Revision 1, dated July 17, 2019, do the
actions for Group 2, Configuration 2, CONDITION 4, and follow-on
actions instead.
(h) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 757-53A0108, Revision 1,
dated July 17, 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 using a method approved in accordance with the
procedures specified in paragraph (i) of this AD.
(2) Where Boeing Alert Service Bulletin 757-53A0108, Revision 1,
dated July 17, 2019, uses the phrase ``the original issue date of
this service bulletin,'' this AD requires using ``May 3, 2018 (the
effective date of AD 2018-06-07),'' except where Boeing Alert
Service Bulletin 757-53A0108, Revision 1, dated July 17, 2019, uses
the phrase ``the original issue date of this service bulletin'' in a
note or flag note.
(3) Where Boeing Alert Service Bulletin 757-53A0108, Revision 1,
dated July 17, 2019, uses the phrase ``the revision 1 date of this
service bulletin,'' this AD requires using ``the effective date of
this AD.''
(4) Where Aviation Partners Boeing Alert Service Bulletin AP757-
53-001, Revision 2, dated October 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, using a method approved in
accordance with the procedures specified in paragraph (i) of this
AD.
(5) Where Aviation Partners Boeing Alert Service Bulletin AP757-
53-001, Revision 2, dated October 22, 2019, uses the phrase ``the
revision 1 issue date of this service bulletin,'' this AD requires
using ``May 3, 2018 (the effective date of AD 2018-06-07),'' except
where Aviation Partners Boeing Alert Service Bulletin AP757-53-001,
Revision 2, dated October 22, 2019, uses the phrase ``the revision 1
issue date of this service bulletin'' in a note or flag note.
(6) Where Aviation Partners Boeing Alert Service Bulletin AP757-
53-001, Revision 2, dated October 22, 2019, uses the phrase ``the
revision 2 issue date of this service bulletin,'' this AD requires
using ``the effective date 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) of this AD. Information may
be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by The Boeing Company Organization Designation
Authorization (ODA) that has been authorized by the Manager, Los
Angeles ACO Branch, FAA, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) Except as specified in paragraph (i)(5) of this AD, AMOCs
approved previously for AD 2018-06-07 are not approved as AMOCs for
the corresponding provisions of this AD.
(5) AMOCs approved in FAA Letters 790-18-8737, 790-18-9637, 790-
18-10097, 790-18-10177, and 790-20-10108, are approved as AMOCs for
this AD.
(6) Except as specified by paragraph (h) of this AD: For service
information that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (i)(6)(i) and (ii) of
this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(j) Related Information
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].
(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) Aviation Partners Boeing Alert Service Bulletin AP757-53-
001, Revision 2, dated October 22, 2019.
(ii) Boeing Alert Service Bulletin 757-53A0108, Revision 1,
dated July 17, 2019.
(3) For Aviation Partners Boeing service information identified
in this AD, contact Aviation Partners Boeing, 2811 S 102nd Street,
Suite 200, Seattle, WA 98168; phone: 206 830 7699; internet: https://www.aviationpartnersboeing.com.
(4) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110 SK57, Seal Beach, CA
90740-5600; phone: 562-797-1717; internet: https://www.myboeingfleet.com.
(5) You may view this service information at the FAA,
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.
(6) 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 September 23, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-21994 Filed 10-5-20; 8:45 am]
BILLING CODE 4910-13-P
