82_FR_26685 82 FR 26576 - Airworthiness Directives; The Boeing Company Airplanes

82 FR 26576 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 109 (June 8, 2017)

Page Range26576-26579
FR Document2017-11624

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.

Federal Register, Volume 82 Issue 109 (Thursday, June 8, 2017) 
[Federal Register Volume 82, Number 109 (Thursday, June 8, 2017)]
[Rules and Regulations]
[Pages 26576-26579]
From the Federal Register Online  [www.thefederalregister.org]
[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.

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

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:
     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 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 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-2017-0531.

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-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: [email protected].

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 http://www.regulations.gov 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]]

     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.
    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 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 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
----------------------------------------------------------------------------------------------------------------
              Action                     Labor cost         Parts cost               Cost per product
----------------------------------------------------------------------------------------------------------------
Inspection........................  3 work-hours x $85                $0  $255 per inspection cycle.
                                     per hour = $255 per
                                     inspection cycle.
----------------------------------------------------------------------------------------------------------------


                                      Estimated Costs for Optional Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     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.
----------------------------------------------------------------------------------------------------------------
\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
----------------------------------------------------------------------------------------------------------------
                                                                                                     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.
----------------------------------------------------------------------------------------------------------------

    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: [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 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: [email protected].

(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 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

[[Page 26579]]

202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    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

26576 Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations www.archives.gov/federal-register/cfr/ibr- p.m., Monday through Friday, except loss of the inboard flap. Continued safe locations.html. Federal holidays. flight and landing could be adversely Issued in Renton, Washington, on May 15, For service information identified in affected after the departure of a flap 2017. this final rule, contact Boeing during takeoff or landing. We are Michael Kaszycki, Commercial Airplanes, Attention: issuing this AD to correct the unsafe Acting Manager, Transport Airplane Contractual & Data Services (C&DS), condition on these products. Directorate, Aircraft Certification Service. 2600 Westminster Blvd., MC 110–SK57, Related Service Information Under 1 [FR Doc. 2017–11131 Filed 6–7–17; 8:45 am] Seal Beach, CA 90740–5600; telephone CFR Part 51 BILLING CODE 4910–13–P 562–797–1717; Internet https:// www.myboeingfleet.com. You may view We reviewed Boeing Alert Service this referenced service information at Bulletin 767–57A0134, dated May 27, DEPARTMENT OF TRANSPORTATION the FAA, Transport Airplane 2016. The service information describes Directorate, 1601 Lind Avenue SW., procedures for repetitive inspections for Federal Aviation Administration Renton, WA. For information on the damage caused by interference between availability of this material at the FAA, the 6–9 drive arm assembly and the 4– 14 CFR Part 39 call 425–227–1221. It is also available 5 actuator crank arm assembly on the on the Internet at http:// inboard flap outboard support assembly [Docket No. FAA–2017–0531; Directorate Identifier 2016–NM–178–AD; Amendment www.regulations.gov by searching for number 3 and number 6, and related 39–18916; AD 2017–12–01] and locating Docket No. FAA–2017– investigative and corrective actions. 0531. This service information is reasonably RIN 2120–AA64 available because the interested parties Examining the AD Docket have access to it through their normal Airworthiness Directives; The Boeing course of business or by the means You may examine the AD docket on Company Airplanes identified in the ADDRESSES section. the Internet at http:// AGENCY: Federal Aviation www.regulations.gov by searching for FAA’s Determination Administration (FAA), DOT. and locating Docket No. FAA–2017– 0531; or in person at the Docket We are issuing this AD because we ACTION: Final rule; request for Management Facility between 9 a.m. evaluated all the relevant information comments. and 5 p.m., Monday through Friday, and determined the unsafe condition SUMMARY: We are adopting a new except Federal holidays. The AD docket described previously is likely to exist or airworthiness directive (AD) for certain contains this AD, the regulatory develop in other products of the same The Boeing Company Model 767–200 evaluation, any comments received, and type design. series airplanes. This AD requires other information. The street address for AD Requirements repetitive inspections for damage of a the Docket Office (phone: 800–647– certain drive arm assembly, and related 5527) is in the ADDRESSES section. This AD requires accomplishing the investigative and corrective actions if Comments will be available in the AD actions specified in the service necessary. This AD was prompted by a docket shortly after receipt. information described previously, report indicating that during an except as discussed under ‘‘Differences FOR FURTHER INFORMATION CONTACT: inspection associated with a flap, the Between this AD and the Service Wayne Lockett, Aerospace Engineer, Information.’’ For information on the extend overtravel stops on an actuator Airframe Branch, ANM–120S, FAA, crank arm assembly were making procedures and compliance times, see Seattle Aircraft Certification Office this service information at http:// contact with an adjacent drive arm (ACO), 1601 Lind Avenue SW., Renton, assembly when the flaps were retracted. www.regulations.gov by searching for WA 98057–3356; phone: 425–917–6447; and locating Docket No. FAA–2017– We are issuing this AD to address the fax: 425–917–6590; email: unsafe condition on these products. 0531. wayne.lockett@faa.gov. The phrase ‘‘related investigative DATES: This AD is effective June 23, SUPPLEMENTARY INFORMATION: actions’’ is used in this AD. Related 2017. investigative actions are follow-on The Director of the Federal Register Discussion actions that (1) are related to the approved the incorporation by reference We have received a report indicating primary action, and (2) further of a certain publication listed in this AD that during an inspection of the investigate the nature of any condition as of June 23, 2017. outboard support assembly number 3 of found. Related investigative actions in We must receive comments on this the inboard flap of the left wing, an an AD could include, for example, AD by July 24, 2017. operator observed that the extend inspections. ADDRESSES: You may send comments, overtravel stops on the 4–5 actuator The phrase ‘‘corrective actions’’ is using the procedures found in 14 CFR crank arm assembly were making used in this AD. Corrective actions 11.43 and 11.45, by any of the following contact with the adjacent 6–9 drive arm correct or address any condition found. methods: assembly when the flaps were totally Corrective actions in an AD could • Federal eRulemaking Portal: Go to retracted. The problem occurred with include, for example, repairs. http://www.regulations.gov. Follow the the installation of 767–400ER flaps, instructions for submitting comments. modified as specified in supplemental Differences Between This AD and the asabaliauskas on DSKBBXCHB2PROD with RULES • Fax: 202–493–2251. type certificate (STC) ST01329WI–D, on Service Information • Mail: U.S. Department of 767–200 airplanes. This condition, if Boeing Alert Service Bulletin 767– Transportation, Docket Operations, not corrected, could result in 57A0134, dated May 27, 2016, specifies M–30, West Building Ground Floor, interference between the 6–9 drive arm to contact the manufacturer for certain Room W12–140, 1200 New Jersey assembly and the 4–5 actuator crank instructions, but this AD would require Avenue SE., Washington, DC 20590. arm assembly, which causes a fatigue using repair methods, modification • Hand Delivery: Deliver to Mail load on the 5–7 link that could result in deviations, and alteration deviations in address above between 9 a.m. and 5 failure of the 5–7 link and subsequent one of the following ways: VerDate Sep<11>2014 16:16 Jun 07, 2017 Jkt 241001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\08JNR1.SGM 08JNR1

Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations 26577 • In accordance with a method that find that notice and opportunity for environmental, and energy aspects of we approve; or prior public comment are unnecessary this AD. We will consider all comments • Using data that meet the and that good cause exists for making received by the closing date and may certification basis of the airplane, and this amendment effective in less than 30 amend this AD because of those that have been approved by the Boeing days. comments. Commercial Airplanes Organization Designation Authorization (ODA) whom Comments Invited We will post all comments we we have authorized to make those receive, without change, to http:// This AD is a final rule that involves www.regulations.gov, including any findings. Boeing Alert Service Bulletin 767– requirements affecting flight safety and personal information you provide. We 57A0134, dated May 27, 2016, affects was not preceded by notice and an will also post a report summarizing each eight airplanes: Those already modified opportunity for public comment. substantive verbal contact we receive by STC ST01329WI–D. This AD applies However, we invite you to send any about this AD. to any airplane modified by STC written data, views, or arguments about this AD. Send your comments to an Costs of Compliance ST01329WI–D, including any airplanes modified in the future. We have address listed under the ADDRESSES Currently, there are no affected U.S.- coordinated this difference with Boeing. section. Include the docket number registered airplanes. If an affected FAA–2017–0531 and Directorate FAA’s Justification and Determination Identifier 2016–NM–178–AD at the airplane is imported and placed on the of the Effective Date beginning of your comments. We U.S. Register in the future, we provide There are currently no domestic specifically invite comments on the the following cost estimates to comply operators of this product. Therefore, we overall regulatory, economic, with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Inspection ..................... 3 work-hours × $85 per hour = $255 per inspection cycle ..................... $0 $255 per inspection cycle. ESTIMATED COSTS FOR OPTIONAL ACTIONS Cost per Action Labor cost Parts cost product 4–5 actuator crank arm assembly modification ........... 34 work-hours × $85 per hour = $2,890 ...................... $0 $2,890 4–5 actuator crank arm assembly replacement ........... 16 work-hours × $85 per hour = $1,360 ...................... 10 1,360 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 required based on the results of the determining the number of aircraft that any necessary repairs that would be inspection. We have no way of might need these actions: ON-CONDITION COSTS Cost per Action Labor cost Parts cost product 4–5 actuator crank arm assembly interim blend repair 8 work-hours × $85 per hour = $680 ........................... $0 $680 We have received no definitive data section 106, describes the authority of products identified in this rulemaking that would enable us to provide cost the FAA Administrator. ‘‘Subtitle VII: action. estimates for the 6–9 drive arm Aviation Programs’’ describes in more assembly repair because the work-hours Regulatory Findings detail the scope of the Agency’s required for repair depend on the authority. This AD will not have federalism damage found. We are issuing this rulemaking under implications under Executive Order According to the manufacturer, some the authority described in Subtitle VII, 13132. This AD will not have a of the costs of this AD may be covered Part A, Subpart III, Section 44701: substantial direct effect on the States, on under warranty, thereby reducing the cost impact on affected individuals. We ‘‘General requirements.’’ Under that the relationship between the national do not control warranty coverage for section, Congress charges the FAA with government and the States, or on the asabaliauskas on DSKBBXCHB2PROD with RULES affected individuals. As a result, we promoting safe flight of civil aircraft in distribution of power and have included all available costs in our air commerce by prescribing regulations responsibilities among the various cost estimate. for practices, methods, and procedures levels of government. the Administrator finds necessary for For the reasons discussed above, I Authority for This Rulemaking safety in air commerce. This regulation certify that this AD: Title 49 of the United States Code is within the scope of that authority specifies the FAA’s authority to issue because it addresses an unsafe condition (1) Is not a ‘‘significant regulatory rules on aviation safety. Subtitle I, that is likely to exist or develop on action’’ under Executive Order 12866, VerDate Sep<11>2014 16:16 Jun 07, 2017 Jkt 241001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\08JNR1.SGM 08JNR1

26578 Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations (2) Is not a ‘‘significant rule’’ under (f) Compliance or lacking a principal inspector, the manager DOT Regulatory Policies and Procedures Comply with this AD within the of the local flight standards district office/ (44 FR 11034, February 26, 1979), compliance times specified, unless already certificate holding district office. done. (3) An AMOC that provides an acceptable (3) Will not affect intrastate aviation level of safety may be used for any repair, in Alaska, and (g) Inspection of the 6–9 Drive Arm modification, or alteration required by this (4) Will not have a significant Assembly and Related Investigative and AD if it is approved by the Boeing Corrective Actions Commercial Airplanes Organization economic impact, positive or negative, on a substantial number of small entities Except as provided by paragraph (i)(1) of Designation Authorization (ODA) that has this AD, at the applicable time specified in been authorized by the Manager, Seattle under the criteria of the Regulatory ACO, to make those findings. To be paragraph 1.E., ‘‘Compliance,’’ of Boeing Flexibility Act. Alert Service Bulletin 767–57A0134, dated approved, the repair method, modification List of Subjects in 14 CFR Part 39 May 27, 2016: Do a general visual inspection deviation, or alteration deviation must meet of the 6–9 drive arm assembly on the left and the certification basis of the airplane, and the Air transportation, Aircraft, Aviation right wing for any damage, and all applicable approval must specifically refer to this AD. safety, Incorporation by reference, related investigative and corrective actions, (4) Except as required by paragraph (i)(2) Safety. in accordance with the Accomplishment of this AD: For service information that Instructions of Boeing Alert Service Bulletin contains steps that are labeled as Required Adoption of the Amendment 767–57A0134, dated May 27, 2016, except as for Compliance (RC), the provisions of required by paragraph (i)(2) of this AD. Do all paragraphs (j)(4)(i) and (j)(4)(ii) of this AD Accordingly, under the authority applicable related investigative and apply. delegated to me by the Administrator, corrective actions before further flight. (i) The steps labeled as RC, including the FAA amends 14 CFR part 39 as Repeat the inspection at the interval substeps under an RC step and any figures follows: specified in paragraph 1.E., ‘‘Compliance,’’ of identified in an RC step, must be done to Boeing Alert Service Bulletin 767–57A0134, comply with the AD. If a step or substep is PART 39—AIRWORTHINESS dated May 27, 2016. labeled ‘‘RC Exempt,’’ then the RC DIRECTIVES (h) Optional Terminating Actions requirement is removed from that step or substep. An AMOC is required for any Doing the action specified in either deviations to RC steps, including substeps ■ 1. The authority citation for part 39 paragraph (h)(1) or paragraph (h)(2) of this and identified figures. continues to read as follows: AD, in accordance with the Accomplishment (ii) Steps not labeled as RC may be Instructions of Boeing Alert Service Bulletin Authority: 49 U.S.C. 106(g), 40113, 44701. deviated from using accepted methods in 767–57A0134, dated May 27, 2016, except as accordance with the operator’s maintenance § 39.13 [Amended] required by paragraph (i)(2) of this AD, or inspection program without obtaining terminates the repetitive inspections required by paragraph (g) of this AD for the drive arm approval of an AMOC, provided the RC steps, ■ 2. The FAA amends § 39.13 by adding including substeps and identified figures, can the following new airworthiness assembly associated with the replacement or modification. still be done as specified, and the airplane directive (AD): (1) A 4–5 actuator crank arm assembly can be put back in an airworthy condition. 2017–12–01 The Boeing Company: replacement. (k) Related Information Amendment 39–18916; Docket No. (2) A 4–5 actuator crank arm assembly For more information about this AD, FAA–2017–0531; Directorate Identifier modification, including all applicable related contact Wayne Lockett, Aerospace Engineer, 2016–NM–178–AD. investigative and corrective actions. Airframe Branch, ANM–120S, FAA, Seattle (a) Effective Date (i) Service Information Exceptions ACO, 1601 Lind Avenue SW., Renton, WA This AD is effective June 23, 2017. (1) Where paragraph 1.E., ‘‘Compliance,’’ of 98057–3356; phone: 425–917–6447; fax: 425– Boeing Alert Service Bulletin 767–57A0134, 917–6590; email: wayne.lockett@faa.gov. (b) Affected ADs dated May 27, 2016, specifies a compliance (l) Material Incorporated by Reference None. time ‘‘after the original issue date of this service bulletin,’’ this AD requires (1) The Director of the Federal Register (c) Applicability approved the incorporation by reference compliance within the specified compliance This AD applies to The Boeing Company time after the effective date of this AD. (IBR) of the service information listed in this Model 767–200 series airplanes, equipped (2) Where Boeing Alert Service Bulletin paragraph under 5 U.S.C. 552(a) and 1 CFR with 767–400ER flaps modified as specified 767–57A0134, dated May 27, 2016, specifies part 51. in supplemental type certificate (STC) to contact Boeing for appropriate action as an (2) You must use this service information ST01329WI–D. ‘‘RC’’ (Required for Compliance) step, this as applicable to do the actions required by AD requires repair using a method approved this AD, unless the AD specifies otherwise. (d) Subject (i) Boeing Alert Service Bulletin 767– in accordance with the procedures specified Air Transport Association (ATA) of in paragraph (j) of this AD. 57A0134, dated May 27, 2016. America Code 57, Wings. (ii) Reserved. (j) Alternative Methods of Compliance (3) For service information identified in (e) Unsafe Condition (AMOCs) this AD, contact Boeing Commercial This AD was prompted by a report (1) The Manager, Seattle Aircraft Airplanes, Attention: Contractual & Data indicating that during an inspection Certification Office (ACO), FAA, has the Services (C&DS), 2600 Westminster Blvd., associated with a flap, the extend overtravel authority to approve AMOCs for this AD, if MC 110–SK57, Seal Beach, CA 90740–5600; stops on an actuator crank arm assembly requested using the procedures found in 14 telephone 562–797–1717; Internet https:// were making contact with an adjacent drive CFR 39.19. In accordance with 14 CFR 39.19, www.myboeingfleet.com. arm assembly when the flaps were retracted. send your request to your principal inspector (4) You may view this service information asabaliauskas on DSKBBXCHB2PROD with RULES We are issuing this AD to detect and correct or local Flight Standards District Office, as at the FAA, Transport Airplane Directorate, interference between a drive arm assembly appropriate. If sending information directly 1601 Lind Avenue SW., Renton, WA. For and an actuator crank arm assembly, which to the manager of the ACO, send it to the information on the availability of this causes a fatigue load on a certain link that attention of the person identified in material at the FAA, call 425–227–1221. could result in failure of that link and paragraph (k) of this AD. Information may be (5) You may view this service information subsequent loss of the flap. Continued safe emailed to: 9-ANM-Seattle-ACO-AMOC- that is incorporated by reference at the flight and landing could be adversely affected Requests@faa.gov. National Archives and Records after the departure of a flap during takeoff or (2) Before using any approved AMOC, Administration (NARA). For information on landing. notify your appropriate principal inspector, the availability of this material at NARA, call VerDate Sep<11>2014 16:16 Jun 07, 2017 Jkt 241001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\08JNR1.SGM 08JNR1

Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations 26579 202–741–6030, or go to: http:// 9490; or in person at the Docket this AD that the affected HPT spacer/ www.archives.gov/federal-register/cfr/ibr- Management Facility between 9 a.m. impeller is installed on GE CF6– locations.html. and 5 p.m., Monday through Friday, 80C2L1F engines only. GE Aviation Issued in Renton, Washington, on May 26, except Federal holidays. The AD docket commented that this P/N impeller is 2017. contains this AD, the regulatory also installed on other models of the Michael Kaszycki, evaluation, any comments received, and CF6–80C2 engine. Acting Manager, Transport Airplane other information. The address for the We disagree. We believe that the Directorate, Aircraft Certification Service. Docket Office (phone: 800–647–5527) is applicability section is clear that this [FR Doc. 2017–11624 Filed 6–7–17; 8:45 am] Document Management Facility, U.S. AD applies to GE CF6–80C2L1F Department of Transportation, Docket BILLING CODE 4910–13–P turbofan engines with a HPT spacer/ Operations, M–30, West Building impeller, P/N 1539M12P02, installed. Ground Floor, Room W12–140, 1200 We did not change this AD. DEPARTMENT OF TRANSPORTATION New Jersey Avenue SE., Washington, DC 20590. Miscellaneous Comment Federal Aviation Administration FOR FURTHER INFORMATION CONTACT: Herman Mak, Aerospace Engineer, An individual commenter indicated 14 CFR Part 39 Engine Certification Office, FAA, Engine that the proposal showed the FAA’s & Propeller Directorate, 1200 District commitment to ‘‘staying on top of [Docket No. FAA–2016–9490; Directorate Identifier 2016–NE–26–AD; Amendment 39– Avenue, Burlington, MA 01803; phone: changes in the industry.’’ The 18914; AD 2017–11–15] 781–238–7147; fax: 781–238–7199; commenter noted, however, that email: herman.mak@faa.gov. although GE has updated the life RIN 2120–AA64 expectancy of this part, it may still be SUPPLEMENTARY INFORMATION: a long time before it needs to be Airworthiness Directives; General Discussion replaced. The commenter indicated, Electric Company Turbofan Engines therefore, that the FAA’s action may be We issued a notice of proposed AGENCY: Federal Aviation rulemaking (NPRM) to amend 14 CFR ‘‘over zealous’’ and lead to ‘‘large scale Administration (FAA), DOT. part 39 by adding an AD that would waste.’’ ACTION: Final rule. apply to certain GE CF6–80C2L1F We disagree. We are issuing this AD turbofan engines. The NPRM published to prevent failure of an engine rotating SUMMARY: We are adopting a new in the Federal Register on January 23, part, which could lead to failure of the airworthiness directive (AD) for General 2017 (82 FR 7734) (‘‘the NPRM’’). The part, uncontained release of the part, Electric Company (GE) CF6–80C2L1F NPRM was prompted by a reduction in damage to the engine, and damage to the turbofan engines. This AD was the life limit of the affected engines airplane. We did not change this AD. prompted by a reduction in the life limit which is the result of a revised of the affected engines which is the operating profile. The NPRM proposed Support for the NPRM result of a revised operating profile. to require replacement of the HPT spacer/impeller, P/N 1539M12P02, at a An individual commenter supported This AD requires replacement of the newer, lower life limit. We are issuing the NPRM. high-pressure turbine (HPT) spacer/ impeller, part number (P/N) this AD to prevent failure of the HPT Conclusion 1539M12P02, at a newer, lower life spacer/impeller, uncontained release of limit. We are issuing this AD to correct the HPT spacer/impeller, damage to the We reviewed the relevant data, the unsafe condition on these products. engine, and damage to the airplane. considered the comments received, and DATES: This AD is effective July 13, determined that air safety and the Comments 2017. public interest require adopting this AD We gave the public the opportunity to as proposed. ADDRESSES: See the FOR FURTHER participate in developing this AD. The INFORMATION CONTACT section. following presents the comments Costs of Compliance Examining the AD Docket received on the NPRM and the FAA’s We estimate that this AD affects 0 response to each comment. You may examine the AD docket on engines installed on airplanes of U.S. the Internet at http:// Request To Revise Compliance registry. www.regulations.gov by searching for GE Aviation requested that we We estimate the following costs to and locating Docket No. FAA–2016– indicate in the compliance section of comply with this AD: ESTIMATED COSTS Cost per Cost on U.S. Action Labor cost Parts cost product operators Replacement of HPT spacer/impel- 0 work-hours × $85 per hour = $0 $19,320 (pro-rated cost of part) ..... $19,320 $0 ler at reduced life. asabaliauskas on DSKBBXCHB2PROD with RULES Authority for This Rulemaking rules on aviation safety. Subtitle I, detail the scope of the Agency’s Title 49 of the United States Code section 106, describes the authority of authority. specifies the FAA’s authority to issue the FAA Administrator. Subtitle VII: Aviation Programs, describes in more VerDate Sep<11>2014 16:16 Jun 07, 2017 Jkt 241001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\08JNR1.SGM 08JNR1


Document Created: 2018-11-14 10:06:58
Document Modified: 2018-11-14 10:06:58
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule; request for comments.
DatesThis AD is effective June 23, 2017.
ContactWayne 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: [email protected]
FR Citation82 FR 26576 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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