[Federal Register Volume 86, Number 12 (Thursday, January 21, 2021)]
[Proposed Rules]
[Pages 6273-6276]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-01161]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-1140; Project Identifier AD-2020-01009-T]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2017-14-13, which applies to certain The Boeing Company Model 737-600, 
-700, -700C, -800, -900, and -900ER series airplanes. AD 2017-14-13 
requires a torque check of the screws in the cover assembly of the heel 
rest for both the captain's and the first officer's rudder pedals, and 
corrective action if necessary. Since the FAA issued AD 2017-14-13, 
operators have continued to find loose rudder pedal cover fasteners on 
previously inspected airplanes and airplanes outside the applicability 
of AD 2017-14-13. This proposed AD would require modifying the rudder 
pedal cover and shroud, and apply to all The Boeing Company Model 737-
600, -700, -700C, -800, -900, and -900ER series airplanes and Model 
737-8 and 737-9 airplanes. The FAA is proposing this AD to address the 
unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by March 8, 
2021.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5

[[Page 6274]]

p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 
2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; 
telephone 562-797-1717; internet https://www.myboeingfleet.com. You may 
view this service information at the FAA, Airworthiness Products 
Section, Operational Safety Branch, 2200 South 216th St., Des Moines, 
WA. For information on the availability of this material at the FAA, 
call 206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
1140.

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-
1140; 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 NPRM, any comments received, and other information. The street 
address for Docket Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Douglas Tsuji, Aerospace Engineer, 
Systems and Equipment Section, FAA, Seattle ACO Branch, 2200 South 
216th St., Des Moines, WA 98198; phone and fax: 206-231-3548; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2020-1140; 
Project Identifier AD-2020-01009-T'' at the beginning of your comments. 
The most helpful comments reference a specific portion of the proposal, 
explain the reason for any recommended change, and include supporting 
data. The FAA will consider all comments received by the closing date 
and may amend the proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact the FAA receives about this proposed AD.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to the 
person identified in the FOR FURTHER INFORMATION CONTACT section. Any 
commentary that the FAA receives which is not specifically designated 
as CBI will be placed in the public docket for this rulemaking.

Background

    The FAA issued AD 2017-14-13, Amendment 39-18957 (82 FR 33007, July 
19, 2017) (``AD 2017-14-13''), for certain The Boeing Company Model 
737-600, -700, -700C, -800, -900, and -900ER series airplanes. AD 2017-
14-13 requires a torque check of the screws in the cover assembly of 
the heel rest for both the captain's and the first officer's rudder 
pedals, and corrective action if necessary. AD 2017-14-13 resulted from 
a report of an aborted takeoff because the rudder pedals were not 
operating correctly. Investigation revealed a protruding screw in the 
rudder pedal heel rest adjacent to the pedals. The FAA issued AD 2017-
14-13 to address a protruding screw in the cover assembly of the heel 
rest of a rudder pedal. A protruding screw could restrict rudder pedal 
motion and reduce differential braking control during takeoff or 
landing, which could cause a high-speed runway excursion.

Actions Since AD 2017-14-13 Was Issued

    Since the FAA issued AD 2017-14-13, operators have continued to 
find loose rudder pedal cover fasteners on previously inspected 
airplanes and on airplanes outside the applicability of the AD. The FAA 
has determined that this design issue is an unsafe condition that 
affects all The Boeing Company Model 737-600, -700, -700C, -800, -900, 
and -900ER series airplanes and Model 737-8 and 737-9 airplanes.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin 737-27A1313 RB, 
Revision 1, dated June 24, 2020; and Boeing Alert Requirements Bulletin 
737-27A1314 RB, Revision 1, dated June 24, 2020. The service 
information describes procedures for modifying the captain's and first 
officer's rudder pedal cover and shroud assemblies. These documents are 
distinct since they apply to different airplane models. 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.

FAA's Determination

    The FAA is issuing this NPRM after determining the unsafe condition 
described previously is likely to exist or develop in other products of 
the same type design.

Proposed AD Requirements

    This proposed AD would retain none of the requirements of AD 2017-
14-13. This proposed AD would expand the applicability to include all 
The Boeing Company Model -600, -700, -700C, -800, -900, and -900ER 
series airplanes and Model 737-8 and 737-9 airplanes. This proposed AD 
would require accomplishment of the actions identified in Boeing Alert 
Requirements Bulletin 737-27A1313 RB, Revision 1, dated June 24, 2020; 
and Boeing Alert Requirements Bulletin 737-27A1314 RB, Revision 1, 
dated June 24, 2020; described previously, except as discussed under 
``Differences Between this Proposed AD and the Service Information,'' 
and except for any differences identified as exceptions in the 
regulatory text of this proposed AD.
    For information on the procedures and compliance times, see this 
service information at https://www.regulations.gov by searching for and 
locating Docket No. FAA-2020-1140.

Differences Between This Proposed AD and the Service Information

    The effectivity of Boeing Alert Requirements Bulletin 737-27A1313 
RB, Revision 1, dated June 24, 2020, is limited to Model 737-8 and 737-
9 airplanes with certain line numbers. The effectivity of Boeing Alert 
Requirements Bulletin 737-27A1314 RB, Revision 1, dated June 24, 2020, 
is limited to Model 737-600, 737-700, 737-700C, 737-800, 737-900, and 
737-

[[Page 6275]]

900ER series airplanes with certain line numbers. However, the 
applicability of this proposed AD includes all Boeing Model 737-600, -
700, -700C, -800, -900, and -900ER series airplanes and Model 737-8 and 
737-9 airplanes. Because the affected captain's and first officer's 
rudder pedal cover and shroud assemblies are rotable parts, the FAA has 
determined that these parts could later be installed on airplanes that 
were initially delivered with acceptable rudder pedal cover and shroud 
assemblies, thereby subjecting those airplanes to the unsafe condition. 
The agency has confirmed with Boeing that the Accomplishment 
Instructions in Boeing Alert Requirements Bulletin 737-27A1313 RB, 
Revision 1, dated June 24, 2020, and Boeing Alert Requirements Bulletin 
737-27A1314 RB, Revision 1, dated June 24, 2020, are applicable to the 
expanded group of airplanes.

Costs of Compliance

    The FAA estimates that this proposed AD affects 2,048 airplanes of 
U.S. registry. The FAA estimates the following costs to comply with 
this proposed AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                     Labor cost           Parts cost     Cost per  product      operators
----------------------------------------------------------------------------------------------------------------
Modifying rudder pedal shroud    Up to 13 work-hours x            $5,560   Up to $6,665......  Up to
 assemblies.                      $85 per hour = Up to                                          $13,649,920.
                                  $1,105.
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    The FAA has included all costs in its cost estimate. According to 
the manufacturer, however, some or all of the costs of this proposed AD 
may be covered under warranty, thereby reducing the cost impact on 
affected operators.

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 proposed AD would not have 
federalism implications under Executive Order 13132. This proposed AD 
would 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 the proposed 
regulation:
    (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.

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 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2017-14-13, Amendment 39-18957 (82 
FR 33007, July 19, 2017), and
0
b. Adding the following new airworthiness directive:

The Boeing Company: Docket No. FAA-2020-1140; Project Identifier AD-
2020-01009-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) action by March 8, 2021.

(b) Affected ADs

    This AD replaces AD 2017-14-13, Amendment 39-18957 (82 FR 33007, 
July 19, 2017) (AD 2017-14-13).

(c) Applicability

    This AD applies to all The Boeing Company airplanes specified in 
paragraphs (c)(1) and (2) of this AD, certificated in any category.
    (1) Model 737-600, -700, -700C, -800, -900, and -900ER series 
airplanes.
    (2) Model 737-8 and 737-9 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Unsafe Condition

    This AD was prompted by a report of an aborted takeoff because 
the rudder pedals were not operating correctly, and by additional 
reports of loose rudder pedal cover fasteners on previously 
inspected airplanes and on additional airplanes that were not 
included in the applicability of AD 2017-14-13. The FAA is issuing 
this AD to address incorrectly installed cover assembly fasteners 
from interfering with the operation of a rudder pedal. An 
incorrectly installed fastener could restrict rudder pedal motion 
and reduce differential braking control during takeoff or landing, 
which could cause a high-speed runway excursion.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Determination of Modification Status

    For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued before the 
effective date of this AD: Within 27 months after the date of 
issuance of the original airworthiness certificate or original 
export certificate of airworthiness, or within 27 months after the 
effective date of this AD, whichever occurs later, determine whether 
the captain's and first officer's rudder pedal cover and shroud 
assemblies have been modified as specified in Boeing Alert 
Requirements Bulletin 737-27A1313 RB, Revision 1, dated June 24, 
2020, or 737-27A1314 RB, Revision 1, dated June 24, 2020, as 
applicable, or by production equivalent. A review of airplane 
maintenance records is acceptable for this requirement if the 
modification status can be conclusively determined from that review.

(h) Modification

    For airplanes that have not been modified as determined by 
paragraph (g) of this AD: At

[[Page 6276]]

the applicable times specified in the ``Compliance'' paragraph of 
Boeing Alert Requirements Bulletin 737-27A1313 RB, Revision 1, dated 
June 24, 2020, or Boeing Alert Requirements Bulletin 737-27A1314 RB, 
Revision 1, dated June 24, 2020, as applicable, except as specified 
by paragraph (i) of this AD, do all applicable actions identified 
in, and in accordance with, the Accomplishment Instructions of 
Boeing Alert Requirements Bulletin 737-27A1313 RB, Revision 1, dated 
June 24, 2020, or Boeing Alert Requirements Bulletin 737-27A1314 RB, 
Revision 1, dated June 24, 2020, as applicable.
    Note 1 to paragraph (h): Guidance for accomplishing the actions 
required by paragraph (h) of this AD can be found in Boeing Alert 
Service Bulletin 737-27A1313, Revision 1, dated June 24, 2020, and 
Boeing Alert Service Bulletin 737-27A1314, Revision 1, dated June 
24, 2020, which are referred to in Boeing Alert Requirements 
Bulletin 737-27A1313 RB, Revision 1, dated June 24, 2020, and Boeing 
Alert Requirements Bulletin 737-27A1314 RB, Revision 1, dated June 
24, 2020, respectively.

(i) Exception to Service Information Specifications

    Where Boeing Alert Requirements Bulletin 737-27A1313 RB, 
Revision 1, dated June 24, 2020, and Boeing Alert Requirements 
Bulletin 737-27A1314 RB, Revision 1, dated June 24, 2020, use the 
phrase ``the original issue date of'' each Requirements Bulletin for 
compliance, this AD requires using the effective date of this AD.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Alert Requirements Bulletin 
737-27A1313 RB, dated March 18, 2020, or Boeing Alert Requirements 
Bulletin 737-27A1314 RB, dated March 18, 2020.

(k) Parts Installation Limitation

    (1) For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued after the 
effective date of this AD: As of the effective date of this AD, no 
person may install a captain's or first officer's rudder pedal cover 
or shroud assembly on any airplane, unless the cover or shroud 
assembly has been modified in accordance with the requirements of 
paragraph (h) of this AD.
    (2) For airplanes with an original airworthiness certificate or 
original export certificate of airworthiness issued prior to the 
effective date of this AD: After the modification required by 
paragraph (h) of this AD has been done, no person may install a 
captain's or first officer's rudder pedal cover or shroud assembly 
on any airplane, unless the cover or shroud assembly has been 
modified in accordance with the requirements of paragraph (h) of 
this AD. Reinstallation of a rudder pedal cover or shroud assembly 
that has not been modified in accordance with paragraph (h) of this 
AD but has been removed for other maintenance is allowed.

(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 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 (m)(1) of this AD. Information may be 
emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by The Boeing Company Organization Designation 
Authorization (ODA) that has been authorized by the Manager, Seattle 
ACO Branch, FAA, to make those findings. To be approved, the repair 
method, modification deviation, or alteration deviation must meet 
the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved previously for AD 2017-14-13 are not approved 
as AMOCs for the corresponding provisions of this AD.
    (5) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(l)(5)(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.

(m) Related Information

    (1) For more information about this AD, contact Douglas Tsuji, 
Aerospace Engineer, Systems and Equipment Section, FAA, Seattle ACO 
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 
206-231-3548; email: [email protected].
    (2) 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. 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 206-231-3195.

    Issued on December 17, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-01161 Filed 1-19-21; 8:45 am]
BILLING CODE 4910-13-P