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Federal Register / Vol. 86, No. 123 / Wednesday, June 30, 2021 / Proposed Rules For the reasons discussed above, I
certify this proposed regulation:
1 Is not a significant regulatory action under Executive Order 12866, 2 Would not affect intrastate aviation in Alaska, and 3 Would 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.
The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by adding the following new airworthiness directive:

The Boeing Company: Docket No. FAA
20210457; Project Identifier AD2020
01461T.
a Comments Due Date The FAA must receive comments on this airworthiness directive AD by August 16, 2021.
b Affected ADs None.
c Applicability This AD applies to The Boeing Company Model 7878, 7879, and 78710 airplanes, certificated in any category, as identified in Boeing Alert Requirements Bulletin B787
81205SB32004500 RB, Issue 001, dated November 9, 2020.

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d Subject Air Transport Association ATA of America Code 32, Main landing gear.
e Unsafe Condition This AD was prompted by a report that during a fleet sampling inspection, cracks were found on the inner cylinder pivot pins of the left and right main landing gear MLG
on one of the airplanes. The FAA is issuing this AD to address any heat damage and cracking to the MLG inner cylinder pivot pin, which could result in a fractured pivot pin and lead to loss of all or part of the pivot pin assembly, and subsequent collapse of the MLG and reduced controllability of the airplane during takeoff and landing.

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f Compliance Comply with this AD within the compliance times specified, unless already done.
g Required Actions Except as specified by paragraph h of this AD: At the applicable times specified in the Compliance paragraph of Boeing Alert Requirements Bulletin B78781205
SB32004500 RB, Issue 001, dated November 9, 2020, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin B78781205
SB32004500 RB, Issue 001, dated November 9, 2020. Actions identified as terminating action in Boeing Alert Requirements Bulletin B78781205SB32004500 RB, Issue 001, dated November 9, 2020, terminate the applicable required actions of this AD, provided the terminating action is done in accordance with the Accomplishment Instructions of Boeing Alert Requirements Bulletin B78781205SB32004500 RB, Issue 001, dated November 9, 2020.
Note 1 to paragraph g: Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin B78781205SB32004500, Issue 001, dated November 9, 2020, which is referred to in Boeing Alert Requirements Bulletin B78781205SB32004500 RB, Issue 001, dated November 9, 2020.
h Exceptions to Service Information Specifications 1 Where Boeing Alert Requirements Bulletin B78781205SB32004500 RB, Issue 001, dated November 9, 2020, uses the phrase the Issue 001 date of Requirements Bulletin B78781205SB32004500 RB, this AD
requires using the effective date of this AD.
2 Where Boeing Alert Requirements Bulletin B78781205SB32004500 RB, Issue 001, dated November 9, 2020, specifies contacting Boeing for repair instructions:
This AD requires doing the repair using a method approved in accordance with the procedures specified in paragraph l of this AD.
3 Where the action for CONDITION 2
in Table 7 of the Compliance paragraph of Boeing Alert Requirements Bulletin B787
81205SB32004500 RB, Issue 001, dated November 9, 2020, specifies Do a detailed FPI inspection of the inner cylinder lug bore for heat and friction damage, for this AD, the action is Do a detailed and FPI
inspection on the inner cylinder lug bore for heat and friction damage.
i Optional Terminating Action Revising the existing maintenance or inspection program, as applicable, to incorporate the information in CMR item number 32CMR01 of Section G, Certification Maintenance Requirement Task, of Boeing 787 Certification Maintenance Requirements CMRs, D011Z0090303, dated June 2020, terminates the repetitive lubrications required by paragraph g of this AD.
j No Alternative Actions and Intervals After the existing maintenance or inspection program has been revised as
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required by paragraph i of this AD, no alternative actions e.g., inspections and intervals may be used unless the actions and intervals are approved as an alternative method of compliance AMOC in accordance with the procedures specified in paragraph l of this AD.
k Parts Installation Prohibition At the applicable time specified in paragraph k1 or 2 of this AD, do not install an aluminum-nickel-bronze inner cylinder bushing on a MLG inner cylinder on any airplane.
1 For airplanes with aluminum-nickelbronze inner cylinder bushings installed on a MLG inner cylinder as of the effective date of this AD: After the bushing has been replaced with a copper-nickel-tin inner cylinder bushing.
2 For airplanes with copper-nickel-tin inner cylinder bushings installed on a MLG
inner cylinder as of the effective date of this AD: As of the effective date of this AD.
l 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in Related Information.
Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.
2 Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards 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.
m Related Information 1 For more information about this AD, contact Allen Rauschendorfer, Senior Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206
2313528; email: allen.rauschendorfer@
faa.gov.
2 For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services C&DS, 2600 Westminster Blvd., MC 110SK57, Seal Beach, CA 907405600;
telephone 5627971717; internet https
www.myboeingfleet.com. You may view this referenced 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 2062313195.

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