AD 2020-20-10

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2020-21994]


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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.

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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: <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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: <a href="https://www.aviationpartnersboeing.com">https://www.aviationpartnersboeing.com</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-2020-
0094.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#0c7c6978697e22666d7e7663616e4c6a6d6d226b637a"><span class="__cf_email__" data-cfemail="5c2c3928392e72363d2e2633313e1c3a3d3d723b332a">[email&#160;protected]</span></a>.

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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
    <bullet> 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: <a href="/cdn-cgi/l/email-protection#b1889cf0fffc9cfdf0f0f2fe9cf0fcfef29ce3d4c0c4d4c2c5c2f1d7d0d09fd6dec7"><span class="__cf_email__" data-cfemail="675e4a26292a4a2b262624284a262a28244a35021612021413142701060649000811">[email&#160;protected]</span></a>.
    (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: <a href="/cdn-cgi/l/email-protection#3e4e5b4a5b4c10545f4c4451535c7e585f5f10595148"><span class="__cf_email__" data-cfemail="f28297869780dc989380889d9f90b2949393dc959d84">[email&#160;protected]</span></a>.

(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: <a href="https://www.aviationpartnersboeing.com">https://www.aviationpartnersboeing.com</a>.
    (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: <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (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 <a href="/cdn-cgi/l/email-protection#f5939091879092db9990929499b59b948794db929a83"><span class="__cf_email__" data-cfemail="bfd9dadbcddad891d3dad8ded3ffd1decdde91d8d0c9">[email&#160;protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    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