AD 2017-12-01

[Federal Register Volume 82, Number 109 (Thursday, June 8, 2017)]
[Rules and Regulations]
[Pages 26576-26579]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-11624]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0531; Directorate Identifier 2016-NM-178-AD; 
Amendment 39-18916; AD 2017-12-01]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 767-200 series airplanes. This AD requires 
repetitive inspections for damage of a certain drive arm assembly, and 
related investigative and corrective actions if necessary. This AD was 
prompted by a report indicating that during an inspection associated 
with a flap, the extend overtravel stops on an actuator crank arm 
assembly were making contact with an adjacent drive arm assembly when 
the flaps were retracted. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective June 23, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 23, 
2017.
    We must receive comments on this AD by July 24, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this final rule, 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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2017-0531.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
0531; 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 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: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6447; fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#f08791899e95de9c9f939b958484b0969191de979f86"><span class="__cf_email__" data-cfemail="99eef8e0f7fcb7f5f6faf2fcededd9fff8f8b7fef6ef">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    We have received a report indicating that during an inspection of 
the outboard support assembly number 3 of the inboard flap of the left 
wing, an operator observed that the extend overtravel stops on the 4-5 
actuator crank arm assembly were making contact with the adjacent 6-9 
drive arm assembly when the flaps were totally retracted. The problem 
occurred with the installation of 767-400ER flaps, modified as 
specified in supplemental type certificate (STC) ST01329WI-D, on 767-
200 airplanes. This condition, if not corrected, could result in 
interference between the 6-9 drive arm assembly and the 4-5 actuator 
crank arm assembly, which causes a fatigue load on the 5-7 link that 
could result in failure of the 5-7 link and subsequent loss of the 
inboard flap. Continued safe flight and landing could be adversely 
affected after the departure of a flap during takeoff or landing. We 
are issuing this AD to correct the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 767-57A0134, dated May 
27, 2016. The service information describes procedures for repetitive 
inspections for damage caused by interference between the 6-9 drive arm 
assembly and the 4-5 actuator crank arm assembly on the inboard flap 
outboard support assembly number 3 and number 6, and related 
investigative and corrective actions. 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 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 accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between this AD and the Service Information.'' For 
information on the procedures and compliance times, see this service 
information at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2017-0531.
    The phrase ``related investigative actions'' is used in this AD. 
Related investigative actions are follow-on actions that (1) are 
related to the primary action, and (2) further investigate the nature 
of any condition found. Related investigative actions in an AD could 
include, for example, inspections.
    The phrase ``corrective actions'' is used in this AD. Corrective 
actions correct or address any condition found. Corrective actions in 
an AD could include, for example, repairs.

Differences Between This AD and the Service Information

    Boeing Alert Service Bulletin 767-57A0134, dated May 27, 2016, 
specifies to contact the manufacturer for certain instructions, but 
this AD would require using repair methods, modification deviations, 
and alteration deviations in one of the following ways:

[[Page 26577]]

    <bullet> In accordance with a method that we approve; or
    <bullet> 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.
    Boeing Alert Service Bulletin 767-57A0134, dated May 27, 2016, 
affects eight airplanes: Those already modified by STC ST01329WI-D. 
This AD applies to any airplane modified by STC ST01329WI-D, including 
any airplanes modified in the future. We have coordinated this 
difference with Boeing.

FAA's Justification and Determination of the Effective Date

    There are currently no domestic operators of this product. 
Therefore, we find that notice and opportunity for prior public comment 
are unnecessary and 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 AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2017-0531 and 
Directorate Identifier 2016-NM-178-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    Currently, there are no affected U.S.-registered airplanes. If an 
affected airplane is imported and placed on the U.S. Register in the 
future, we provide the following cost estimates to comply with this AD:

                                                 Estimated Costs
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              Action                     Labor cost         Parts cost               Cost per product
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Inspection........................  3 work-hours x $85                $0  $255 per inspection cycle.
                                     per hour = $255 per
                                     inspection cycle.
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                                      Estimated Costs for Optional Actions
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                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
4-5 actuator crank arm assembly modification..  34 work-hours x $85 per hour =                $0          $2,890
                                                 $2,890.
4-5 actuator crank arm assembly replacement...  16 work-hours x $85 per hour =             \1\ 0           1,360
                                                 $1,360.
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\1\ We have received no definitive data that would enable us to provide parts cost estimates for the 4-5
  actuator crank arm assembly replacement.

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the inspection. We have no 
way of determining the number of aircraft that might need these 
actions:

                                               On-Condition Costs
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                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
4-5 actuator crank arm assembly interim blend   8 work-hours x $85 per hour =                 $0            $680
 repair.                                         $680.
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    We have received no definitive data that would enable us to provide 
cost estimates for the 6-9 drive arm assembly repair because the work-
hours required for repair depend on the damage found.
    According to the manufacturer, some of the costs of this 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 available 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

    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,

[[Page 26578]]

    (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):

2017-12-01 The Boeing Company: Amendment 39-18916; Docket No. FAA-
2017-0531; Directorate Identifier 2016-NM-178-AD.

(a) Effective Date

    This AD is effective June 23, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 767-200 series 
airplanes, equipped with 767-400ER flaps modified as specified in 
supplemental type certificate (STC) ST01329WI-D.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report indicating that during an 
inspection associated with a flap, the extend overtravel stops on an 
actuator crank arm assembly were making contact with an adjacent 
drive arm assembly when the flaps were retracted. We are issuing 
this AD to detect and correct interference between a drive arm 
assembly and an actuator crank arm assembly, which causes a fatigue 
load on a certain link that could result in failure of that link and 
subsequent loss of the flap. Continued safe flight and landing could 
be adversely affected after the departure of a flap during takeoff 
or landing.

(f) Compliance

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

(g) Inspection of the 6-9 Drive Arm Assembly and Related Investigative 
and Corrective Actions

    Except as provided by paragraph (i)(1) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 767-57A0134, dated May 27, 2016: Do a 
general visual inspection of the 6-9 drive arm assembly on the left 
and right wing for any damage, and all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 767-
57A0134, dated May 27, 2016, except as required by paragraph (i)(2) 
of this AD. Do all applicable related investigative and corrective 
actions before further flight. Repeat the inspection at the interval 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 767-57A0134, dated May 27, 2016.

(h) Optional Terminating Actions

    Doing the action specified in either paragraph (h)(1) or 
paragraph (h)(2) of this AD, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 767-57A0134, dated May 
27, 2016, except as required by paragraph (i)(2) of this AD, 
terminates the repetitive inspections required by paragraph (g) of 
this AD for the drive arm assembly associated with the replacement 
or modification.
    (1) A 4-5 actuator crank arm assembly replacement.
    (2) A 4-5 actuator crank arm assembly modification, including 
all applicable related investigative and corrective actions.

(i) Service Information Exceptions

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 767-57A0134, dated May 27, 2016, specifies a 
compliance time ``after the original issue date of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (2) Where Boeing Alert Service Bulletin 767-57A0134, dated May 
27, 2016, specifies to contact Boeing for appropriate action as an 
``RC'' (Required for Compliance) step, this AD requires repair using 
a method approved in accordance with the procedures specified in 
paragraph (j) of this AD.

(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) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#724b5f333c3f5f21171306061e175f33313d5f333f3d315f2017030717010601321413135c151d04"><span class="__cf_email__" data-cfemail="477e6a06090a6a14222633332b226a0604086a060a08046a15223632223433340721262669202831">[email&#160;protected]</span></a>.
    (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) Except as required by paragraph (i)(2) of this AD: 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 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.

(k) Related Information

    For more information about this AD, contact Wayne Lockett, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; 
fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#fd8a9c849398d391929e96988989bd9b9c9cd39a928b"><span class="__cf_email__" data-cfemail="4334223a2d266d2f2c2028263737032522226d242c35">[email&#160;protected]</span></a>.

(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 767-57A0134, dated May 27, 
2016.
    (ii) Reserved.
    (3) 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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (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

[[Page 26579]]

202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on May 26, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-11624 Filed 6-7-17; 8:45 am]
BILLING CODE 4910-13-P