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2018-23-51 THE BOEING COMPANY:
Amendment 39-19512; Docket No. FAA-2018-0960; Product Identifier 2018-NM-151-AD.

TDATA NOTE: The original FAA copy had a typo in Figure 2 to paragraph (h).
            Tdata made the correction on the initial release  so no change
            is necessary.

(a) EFFECTIVE DATE

    This  AD  is  effective  December 21, 2018 to all persons except those
    persons  to whom  it was made immediately  effective  by  Emergency AD
    2018-23-51,  issued on November 7, 2018,  which contained the require-
    ments of this amendment.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to all The Boeing Company Model 737-8 and -9 airplanes
    certificated in any category.

(d) SUBJECT

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

(e) UNSAFE CONDITION

    This AD was prompted by analysis performed by the manufacturer showing
    that if an erroneously high single angle of attack (AOA) sensor  input
    is received  by the  flight control  system, there  is a potential for
    repeated nose-down trim commands of the horizontal stabilizer. We  are
    issuing this AD  to address this  potential resulting nose-down  trim,
    which could cause the flight  crew to have difficulty controlling  the
    airplane,  and  lead  to  excessive  nose-down  attitude,  significant
    altitude loss, and possible impact with terrain.

(f) COMPLIANCE

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

(g) REVISION OF AIRPLANE FLIGHT MANUAL (AFM): CERTIFICATE LIMITATIONS

    Within 3 days  after  the  effective  date  of  this  AD,  revise  the
    Certificate Limitations chapter of the applicable AFM  to include  the
    information in figure 1 to paragraph (g) of this AD.


        FIGURE 1 TO PARAGRAPH (G) OF THIS AD  CERTIFICATE LIMITATIONS    
    ______________________________________________________________________
                          REQUIRED BY AD 2018-23-51

                             RUNAWAY STABILIZER
    ______________________________________________________________________
    In the event  of an uncommanded  horizontal stabilizer trim  movement,
    combined with any  of the following  potential effects or  indications
    resulting from an  erroneous Angle of  Attack (AOA) input,  the flight
    crew  must  comply  with  the  Runaway  Stabilizer  procedure  in  the
    Operating Procedures chapter of this manual:

    - Continuous or intermittent stick shaker on the affected side only.
    - Minimum speed bar (red and black) on the affected side only.
    - Increasing nose down control forces.
    - IAS DISAGREE alert.
    - ALT DISAGREE alert.
    - AOA DISAGREE alert (if the option is installed).
    - FEEL DIFF PRESS light.
    - Autopilot may disengage.
    - Inability to engage autopilot.
    ______________________________________________________________________

(h) AFM REVISION: OPERATING PROCEDURES

    Within 3 days after the effective date of this AD,revise the Operating
    Procedures chapter of the applicable AFM to include the information in
    figure 2 to paragraph (h) of this AD.

         FIGURE 2 TO PARAGRAPH (H) OF THIS AD  OPERATING PROCEDURES      
    ______________________________________________________________________
                          REQUIRED BY AD 2018-23-51

                             RUNAWAY STABILIZER
    ______________________________________________________________________
    Disengage autopilot and control  airplane pitch attitude with  control
    column and  main electric  trim as  required. If  relaxing the  column
    causes the trim  to move, set  stabilizer trim switches  to CUTOUT. If
    runaway continues, hold the stabilizer trim wheel against rotation and
    trim the airplane manually.

    Note: The  737-8/-9 uses  a  Flight Control Computer  command of pitch
    trim to improve longitudinal handling characteristics. In the event of
    erroneous Angle of Attack (AOA) input, the pitch trim system can  trim
    the stabilizer nose down in increments lasting up to 10 seconds.

    In the event an uncommanded  nose down stabilizer trim is  experienced
    on the 737-8/-9, in conjunction with one or more of the indications or
    effects listed below, do the existing AFM Runaway Stabilizer procedure
    above, ensuring that the STAB  TRIM CUTOUT switches are set  to CUTOUT
    and stay in the CUTOUT position for the remainder of the flight.

    An erroneous AOA input can cause some or  all of the following indica-
    tions and effects:

    - Continuous or intermittent stick shaker on the affected side only.
    - Minimum speed bar (red and black) on the affected side only.
    - Increasing nose down control forces.
    - IAS DISAGREE alert.
    - ALT DISAGREE alert.
    - AOA DISAGREE alert (if the option is installed).
    - FEEL DIFF PRESS light.
    - Autopilot may disengage.
    - Inability to engage autopilot.

    Initially,  higher control forces may be needed to overcome any stabi-
    lizer nose down trim already applied. Electric stabilizer trim can  be
    used to neutralize control column pitch forces before moving the  STAB
    TRIM CUTOUT  switches to  CUTOUT.  Manual stabilizer trim  can be used
    before and after the STAB TRIM CUTOUT switches are moved to CUTOUT.
    ______________________________________________________________________

(i) 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 (j) of this AD. Information may be emailed to:
    9-ANM-Seattle-ACOAMOC-Requests@faa.gov.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector, or lacking  a principal inspector,  the manager of  the local
    flight standards district office/certificate holding district office.

(j) RELATED INFORMATION

    For further information about this AD,  contact Douglas Tsuji,  Senior
    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: Douglas.Tsuji@faa.gov.

(k) MATERIAL INCORPORATED BY REFERENCE

    None.

Issued in Des Moines, Washington, on November 21, 2018.  Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification Service

FOR FURTHER INFORMATION CONTACT: Douglas Tsuji, Senior 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: Douglas.
Tsuji@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0960; Product Identifier 2018-NM-151-AD; Amendment
39-19512; AD 2018-23-51]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all The
Boeing Company Model 737-8 and -9 airplanes. This emergency AD was sent
previously to all known U.S. owners and operators of these airplanes.
This AD requires revising certificate limitations and operating
procedures of the airplane flight manual (AFM) to provide the flight
crew with runaway horizontal stabilizer trim procedures to follow under
certain conditions. This AD was prompted by analysis performed by the
manufacturer showing that if an erroneously high single angle of attack
(AOA) sensor input is received by the flight control system, there is a
potential for repeated nose-down trim commands of the horizontal
stabilizer. We are issuing this AD to address the unsafe condition on
these products.

DATES: This AD is effective December 21, 2018 to all persons except
those persons to whom it was made immediately effective by Emergency AD
2018-23-51, issued on November 7, 2018, which contained the
requirements of this amendment.
We must receive comments on this AD by January 22, 2019.

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 http://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 p.m., Monday through Friday, except Federal holidays.

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-2018-
0960; 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, the regulatory evaluation, any comments received, and
other information. The street address for Docket Operations (phone:
800-647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Douglas Tsuji, Senior 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: Douglas.Tsuji@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

On November 7, 2018, we issued Emergency AD 2018-23-51, which
requires revising certificate limitations and operating procedures of
the AFM to provide the flight crew with runaway horizontal stabilizer
trim procedures to follow under certain conditions. This emergency AD
was sent previously to all known U.S. owners and operators of these
airplanes. This action was prompted by analysis performed by the
manufacturer showing that if an erroneously high single AOA sensor
input is received by the flight control system, there is a potential
for repeated nose-down trim commands of the horizontal stabilizer. This
condition, if not addressed, could cause the flight crew to have
difficulty controlling the airplane, and lead to excessive nose-down
attitude, significant altitude loss, and possible impact with terrain.

FAA's Determination

We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.

AD Requirements

This AD requires revising certificate limitations and operating
procedures of the AFM to provide the flight crew with runaway
horizontal stabilizer trim procedures to follow under certain
conditions.

Interim Action

We consider this AD interim action. If final action is later
identified, we might consider further rulemaking then.

FAA's Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of
Emergency AD 2018-23-51, issued on November 7, 2018, to all known U.S.
owners and operators of these airplanes. The FAA found that the risk to
the flying public justified waiving notice and comment prior to
adoption of this rule because an erroneously high single AOA sensor
input received by the flight control system can result in a potential
for repeated nose-down trim commands of the horizontal stabilizer,
which could cause the flight crew to have difficulty controlling the
airplane, and lead to excessive nose-down attitude, significant
altitude loss, and possible impact with terrain. These conditions still
exist and the AD is hereby published in the Federal Register as an
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR
39.13) to make it effective to all persons. Therefore, we find good
cause that notice and opportunity for prior public comment are
impracticable. In addition, for the reason(s) stated above, we find
that good cause exists for making this amendment effective in less than
30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this final rule. Send your comments to an address listed under the
ADDRESSES section. Include the docket number FAA-2018-0960 and Product
Identifier 2018-NM-151-AD at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this final rule. We will consider
all comments received by the closing date and may amend this final rule
because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this final rule.

Costs of Compliance

We estimate that this AD affects 45 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:

Estimated Costs for Required Actions

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Revising the AFM 1 work-hour x $85 per hour = $85 $0 $85 $3,825

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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.

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

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]

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