Document ID: FAA-2016-7270-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2016-06-28T04:00Z

[Federal Register Volume 81, Number 124 (Tuesday, June 28, 2016)]
[Proposed Rules]
[Pages 41894-41897]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-14966]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7270; Directorate Identifier 2015-NM-116-AD]
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: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 737-700 and -700C series airplanes. 
This proposed AD was prompted by a report that for airplanes with 
blended winglets, the nose-up pitch trim limit and associated warning 
for the horizontal stabilizer control system will allow take-off with 
incorrect trim settings. This proposed AD would require, depending on 
airplane configuration, replacing the pitch trim light plates on the 
flight deck control stand, relocating the position warning horn 
switches of the horizontal stabilizer, revising the software, removing 
the placard, and doing related investigative and corrective actions if 
necessary. We are proposing this AD to prevent take-off with incorrect 
settings of the horizontal stabilizer pitch trim system. Settings 
outside of the appropriate pitch trim limits could result in loss of 
controllability of the airplane during take-off.

DATES: We must receive comments on this proposed AD by August 12, 2016.

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.
    For Aviation Partners Boeing service information identified in this 
NPRM, contact Aviation Partners Boeing, 2811 South 102nd Street, Suite 
200, Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-3355; email: 
leng@aviationpartners.com; Internet: http://www.aviationpartnersboeing.com.

[[Page 41895]]

    For The Boeing Company service information identified in this NPRM, 
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. Boeing Alert Service Bulletin 737-27A1306, dated September 
10, 2015, is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7270.

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-
7270; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Fnu Winarto, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6659; fax: 425-917-6590; email: 
fnu.winarto@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite 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-2016-7270; 
Directorate Identifier 2015-NM-116-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD 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 proposed AD.

Discussion

    We have received a report that for airplanes with blended winglets, 
the nose-up pitch trim limit and associated warning for the horizontal 
stabilizer control system will allow takeoff with incorrect trim 
settings. The trim control system was recently analyzed for potential 
nose-up mis-trim occurrences during take-off for airplanes with blended 
winglets. Results of the analysis indicated that Model 737-700 
airplanes with blended winglets are not compliant with the 
certification rules for specific conditions. This condition, if not 
corrected, could result in the loss of controllability of the airplane 
during take-off.

Related Service Information Under 1 CFR Part 51

    We reviewed Aviation Partners Boeing Service Bulletin AP737-27-002, 
Revision 2, dated March 1, 2016, and Boeing Alert Service Bulletin 737-
27A1306, dated September 10, 2015. The service information describes 
procedures for replacing the pitch trim light plates on the flight deck 
control stand, relocating the position warning horn switches of the 
horizontal stabilizer, revising the software, and doing related 
investigative and corrective actions.
    The related investigative actions include verifying that the 
stabilizer ``B'' measurement is at a certain dimension, performing a 
light plate function test, performing a stabilizer functional test, 
loading and verifying model/engine database software, performing a 
flight management computer configuration check, and verifying all 
settings.
    The corrective actions include adjusting the stabilizer, adjusting 
the light plate, replacing the light plate, rigging and adjusting the 
horizontal stabilizer trim system, and repairing the light plate 
switch.
    We reviewed Aviation Partners Service Bulletin AP737-34-005, dated 
July 17, 2015. The service information describes procedures for 
revising the software and removing the placard.
    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

    We are proposing 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.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' For information on the procedures and compliance times, 
see Boeing Alert Service Bulletin 737-27A1306, dated September 10, 
2015, at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-7270.

Differences Between This Proposed AD and the Service Information

    The service information specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 569 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Relocation.....................  Up to 4 work-hours x                 $0  Up to $340........  Up to $193,460
                                  $85 per hour = $340.
Replacement....................  Up to 3 work-hours x             $1,973  Up to $2,228......  Up to $1,267,732
                                  $85 per hour = $255.
Software installation..........  2 work-hours x $85 per                0  170...............  96,730
                                  hour = $170.

[[Page 41896]]

 
Placard Removal (2 airplanes)..  1 work-hour x $85 per                 0  85................  170
                                  hour = $85.
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    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

    We 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2016-7270; Directorate Identifier 
2015-NM-116-AD.

(a) Comments Due Date

    We must receive comments by August 12, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 737-700 and -700C 
series airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) 
of this AD, certificated in any category.
    (1) Airplanes having supplemental type certificate ST00830SE 
installed (Aviation Partners Boeing blended winglets), as identified 
in Aviation Partners Boeing Service Bulletin AP737-27-002, Revision 
2, dated March 1, 2016.
    (2) Airplanes identified in Boeing Alert Service Bulletin 737-
27A1306, dated September 10, 2015.
    (3) Airplanes identified in Aviation Partners Service Bulletin 
AP737-34-005, dated July 17, 2015.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report that for airplanes with blended 
winglets, the nose-up pitch trim limit and associated warning for 
the horizontal stabilizer control system will allow take-off with 
incorrect trim settings. We are issuing this AD to prevent take-off 
with incorrect settings of the horizontal stabilizer pitch trim 
system. Settings outside of the appropriate pitch trim limits could 
result in loss of controllability of the airplane during take-off.

(f) Compliance

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

(g) Replacement, Relocation, and Applicable Related Investigative and 
Corrective Actions

    (1) For airplanes identified in paragraph (c)(1) of this AD: 
Within 72 months after the effective date of this AD, relocate the 
position warning horn switches of the horizontal stabilizer, replace 
the pitch trim light plates on the flight deck control stand, revise 
the software, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Aviation Partners Boeing Service Bulletin AP737-27-
002, Revision 2, dated March 1, 2016; except as specified in 
paragraph (j) of this AD. Do all applicable related investigative 
and corrective actions before further flight.
    (2) For airplanes identified in paragraph (c)(2) of this AD: 
Within 72 months after the effective date of this AD, relocate the 
position warning horn switches of the horizontal stabilizer, replace 
the pitch trim light plates on the flight deck control stand, revise 
the software, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-27A1306, dated 
September 10, 2015, and Aviation Partners Boeing Service Bulletin 
AP737-27-002, Revision 2, dated March 1, 2016; except as specified 
in paragraph (j) of this AD. Do all applicable related investigative 
and corrective actions before further flight.

(h) Software Revision and Placard Removal

    For airplanes identified in paragraph (c)(3) of this AD: Within 
72 months after the effective date of this AD, revise the software 
and remove the placard, in accordance with the Accomplishment 
Instructions of Aviation Partners Service Bulletin AP737-34-005, 
dated July 17, 2015.

(i) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    This paragraph provides credit for the actions specified in 
paragraphs (g)(1) and (g)(2) of this AD, if those actions were 
performed before the effective date of this AD using Aviation 
Partners Boeing Service Bulletin AP737-27-002, dated March 31, 2015; 
or Aviation Partners Boeing Service Bulletin AP737-27-002, Revision 
1, dated August 6, 2015.

[[Page 41897]]

(j) Exception to the Service Information

    Where Aviation Partners Boeing Service Bulletin AP737-27-002, 
Revision 2, dated March 1, 2016, specifies to contact Boeing for 
appropriate action, and specifies that action as Required for 
Compliance (RC): Before further flight, repair using a method 
approved in accordance with the procedures specified in paragraph 
(k) of this AD.

(k) 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 (l)(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. For a repair method to 
be approved, the repair, 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 required by paragraph (j) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (RC), the provisions of paragraphs (k)(4)(i) and 
(k)(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. 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.

(l) Related Information

    (1) For more information about this AD, contact Fnu Winarto, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6659; fax: 425-917-6590; 
email: fnu.winarto@faa.gov.
    (2) For service information identified in this AD, contact 
Aviation Partners Boeing, 2811 South 102nd Street, Suite 200, 
Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-3355; email: 
leng@aviationpartners.com; Internet: http://www.aviationpartnersboeing.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.

    Issued in Renton, Washington, on June 14, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-14966 Filed 6-27-16; 8:45 am]
 BILLING CODE 4910-13-P