Document ID: FAA-2016-9506-0008
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2017-07-19T04:00Z

[Federal Register Volume 82, Number 137 (Wednesday, July 19, 2017)]
[Rules and Regulations]
[Pages 33007-33009]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-14584]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9506; Directorate Identifier 2016-NM-090-AD; 
Amendment 39-18957; AD 2017-14-13]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER 
series airplanes. This AD was prompted by 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. This AD requires a torque check of the screws 
in the cover assembly of the heel rest for both the Captain and the 
First Officer's rudder pedals, and corrective action if necessary. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective August 23, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 23, 
2017.

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9506.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9506; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, 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: Kelly McGuckin, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6490; fax: 425-917-6590; email: 
Kelly.McGuckin@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. 
The NPRM published in the Federal Register on December 20, 2016 (81 FR 
92753). The NPRM was prompted by 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. It was determined that the screws in the cover assembly of the 
heel rest for both the Captain and the First Officer's rudder pedals 
might not have been properly torqued. The NPRM proposed to require a 
torque check of the screws in the cover assembly of the heel rest for 
both the Captain and the First Officer's rudder pedals, and corrective 
action if necessary. We are issuing this AD to detect and correct 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.

Comments

    We 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

    Boeing, Air Line Pilots Association, International, and Tyler Myers 
supported the intent of the NPRM.

Request To Allow Credit for Previously Accomplished Actions

    United Airlines noted that the NPRM did not address whether or not 
the final rule would allow operators to take credit for accomplishment 
of the actions in Boeing Alert Service Bulletin 737-25A1732, Revision 
1, dated August 15, 2016 (``BASB 737-25A1732, Revision 1''), if 
completed prior to the effective date of the final rule. We infer that 
the commenter is requesting that the final rule include a statement 
that accomplishment of the actions specified in BASB 737-25A1732, 
Revision 1, prior to the effective date of the final rule is acceptable 
for compliance with the requirements of the final rule.
    We agree with the commenter that operators should be able to take 
credit for accomplishment of the actions in BASB 737-25A1732, Revision 
1, prior to the effective date of this AD. This allowance was provided 
in paragraph (f) of the proposed AD in the statement ``Comply with this 
AD within the compliance times specified unless already done.'' 
However, since the NPRM was issued, Boeing has published, and we have 
reviewed, Boeing Alert Service Bulletin 737-25A1732, Revision 2, dated 
April 13,

[[Page 33008]]

2017 (``BASB 737-25A1732, Revision 2''). BASB 737-25A1732, Revision 2, 
provides clarification of the actions described in the work 
instructions by providing supplementary details and including 
additional descriptive figures. No additional work is necessary and the 
scope of this AD is not expanded.
    We have revised paragraphs (c), (g), and (h) of this AD to refer to 
BASB 737-25A1732, Revision 2. We have also added paragraph (i) to this 
AD to give credit for actions accomplished using the work instructions 
in BASB 737-25A1732, Revision 1; and redesignated the subsequent 
paragraphs accordingly.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that the installation of winglets 
per Supplemental Type Certificate (STC) ST00830SE does not affect the 
accomplishment of the manufacturer's service instructions.
    We agree with the commenter that STC ST00830SE does not affect the 
accomplishment of the manufacturer's service instructions. Therefore, 
the installation of STC ST00830SE does not affect the ability to 
accomplish the actions required by this AD. We have not changed this AD 
in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed, except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-25A1732, Revision 2, 
dated April 13, 2017. The service information describes procedures for 
a torque check of the screws in the cover assembly of the heel rest for 
both the Captain and the First Officer's rudder pedals, and corrective 
action. 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

    We estimate that this AD affects 1,187 airplanes of U.S. registry. 
We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
              Action                        Labor cost            Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Torque check......................  2 work-hours x $85 per                 $0             $170         $201,790
                                     hour = $170.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions 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.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2017-14-13 The Boeing Company: Amendment 39-18957; Docket No. FAA-
2016-9506; Directorate Identifier 2016-NM-090-AD.

(a) Effective Date

    This AD is effective August 23, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any 
category, as identified in Boeing Alert Service Bulletin 737-
25A1732, Revision 2, dated April 13, 2017.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment 
and Furnishings.

(e) Unsafe Condition

    This AD was prompted by 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. It was determined that the screws in the cover 
assembly of the heel rest for both the Captain and the First 
Officer's rudder pedals might

[[Page 33009]]

not have been properly torqued. We are issuing this AD to detect and 
correct 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.

(f) Compliance

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

(g) Torque Check

    Within 21 months after the effective date of this AD: Do a one-
time torque check of the screws in the cover assembly of the heel 
rest for both the Captain and the First Officer's rudder pedals, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-25A1732, Revision 2, dated April 13, 2017.

(h) Corrective Action

    If the results of the torque check required by paragraph (g) of 
this AD indicate that any screw does not hold torque to the required 
value, before further flight, replace the affected screw and 
associated nutplate, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-25A1732, Revision 
2, dated April 13, 2017.

(i) Credit for Actions Accomplished Previously

    This paragraph provides credit for the actions specified in 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin 737-25A1732, Revision 1, dated August 15, 2016.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
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 ACO, send it to the 
attention of the person identified in paragraph (k)(1) of this AD. 
Information may be emailed to: 9-ANM-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 Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, 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 (j)(4)(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 sub-step is labeled ``RC Exempt,'' then 
the RC requirement is removed from that step or sub-step. 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 Kelly McGuckin, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 
425-917-6490; fax: 425-917-6590; email: Kelly.McGuckin@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(3) and (l)(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 Alert Service Bulletin 737-25A1732, Revision 2, dated 
April 13, 2017.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (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, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 29, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-14584 Filed 7-18-17; 8:45 am]
 BILLING CODE 4910-13-P