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[Federal Register Volume 79, Number 131 (Wednesday, July 9, 2014)]
[Proposed Rules]
[Pages 38797-38799]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-16004]

[[Page 38797]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0430; Directorate Identifier 2014-NM-083-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 all 
The Boeing Company Model 767 airplanes. This proposed AD was prompted 
by a report of a rotary actuator for the trailing edge (TE) flap that 
had slipped relative to its mating reaction ring, which is attached to 
the flap support rib. This proposed AD would require repetitive 
inspections for corrosion of the fixed ring gear and reaction ring 
splines of the rotary actuator assembly for each support position, and 
related investigative and corrective actions if necessary. We are 
proposing this AD to detect and correct reaction ring gears and rotary 
actuator gears from becoming disengaged with flaps extended and causing 
an uncommanded roll due to flap blowback, overload, or flap departure 
from the airplane, which could compromise safe flight and landing of 
the airplane.

DATES: We must receive comments on this proposed AD by August 25, 2014.

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 proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. 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.

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-2014-
0430; 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: Allen Rauschendorfer, Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6487; fax: 425-917-6590; email: 
Allen.Rauschendorfer@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-2014-0430; 
Directorate Identifier 2014-NM-083-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 of a TE flap rotary actuator that had 
slipped relative to its mating reaction ring, which is attached to the 
flap support rib. This occurred on a Model 767-300ER airplane that was 
delivered in June 1997 and had accumulated approximately 79,000 total 
flight hours and 14,000 total flight cycles in service. Removal of the 
reaction ring and actuator revealed that the mating splines were 
severely corroded. The manufacturer determined that, if the corrosion 
were to affect the mating splines on either surface (actuator or ring) 
to the point where they could no longer effectively engage, the 
actuator would be prone to possible slippage. Due to the similarity of 
the design, the potential condition could develop at multiple flap 
supports. Should degradation reach the point where both actuators on a 
single flap were unable to react to the torsion created by air loads, 
an uncommanded flap retraction, or blowback could occur. The condition 
of uncommanded roll with flaps extended, due to flap blowback, 
overload, or flap departure from the airplane, could compromise safe 
flight and landing of the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 767-27A0229, dated March 
4, 2014. For information on the procedures and compliance times, see 
this service information at http://www.regulations.gov by searching for 
Docket No. FAA-2014-0430.

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 repetitive 
inspections for corrosion of the fixed ring gear and reaction ring 
splines of the rotary actuator assembly for each support position, and 
related investigative and corrective actions if necessary, specified in 
the service information described previously.
    The phrase ``related investigative actions'' is used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that (1) are related to the primary actions, 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 proposed AD. 
``Corrective actions'' are actions that correct or address any 
condition found. Corrective actions in an AD could include, for 
example, repairs.

Explanation of ``RC'' Steps in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee, 
to enhance the

[[Page 38798]]

AD system. One enhancement was a new process for annotating which steps 
in the service information are required for compliance (RC) with an AD. 
Differentiating these steps from other tasks in the service information 
is expected to improve an owner's/operator's understanding of crucial 
AD requirements and help provide consistent judgment in AD compliance. 
The actions specified in the service information described previously 
include steps that are labeled as RC (required for compliance) because 
these steps have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As noted in the specified service information, steps labeled as RC 
must be done to comply with the proposed AD. However, steps that are 
not labeled as RC are recommended. Those steps that are not labeled as 
RC may be deviated from, done as part of other actions, or done using 
accepted methods different from those identified in the service 
information without obtaining approval of an alternative method of 
compliance (AMOC), provided the steps labeled as RC can be done and the 
airplane can be put back in a serviceable condition. Any substitutions 
or changes to steps labeled as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 389 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
----------------------------------------------------------------------------------------------------------------
Inspection...................  60 work-hours x $85               $0   $5,100 per            $1,983,900 per
                                per hour = $5,100                      inspection cycle..    inspection cycle.
                                per inspection
                                cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                        Labor cost             Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Actuator repair...................  4 work-hours x $85 per                  $0   $340 per actuator.
                                     hour = $340 per actuator.
----------------------------------------------------------------------------------------------------------------

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-2014-0430; Directorate Identifier 
2014-NM-083-AD.

(a) Comments Due Date

    We must receive comments by August 25, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 767-200, -300, -
300F, and -400ER series airplanes, certificated in any category.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of a trailing edge (TE) flap 
rotary actuator that had slipped relative to its mating reaction 
ring, which is attached to the flap support rib. We are issuing this 
AD to detect and correct reaction ring gears and rotary actuator 
gears from becoming disengaged with flaps extended and causing an 
uncommanded roll due to flap blowback, overload, or flap departure 
from the airplane, which could compromise safe flight and landing of 
the airplane.

[[Page 38799]]

(f) Compliance

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

(g) Repetitive Inspections, Related Investigative Actions, and 
Corrective Actions

    Except as provided by paragraph (h) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 767-27A0229, dated March 4, 2014: Do a 
detailed inspection for corrosion of the rotary actuator assembly 
fixed ring gear and reaction ring splines for each support position; 
and do all applicable related investigative and corrective actions 
if necessary; in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 767-27A0229, dated March 4, 2014. Do 
all applicable related investigative and corrective actions before 
further flight. Repeat the inspection of the rotary actuator 
assembly fixed ring gear and reaction ring splines for each support 
position thereafter at the applicable intervals specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
767-27A0229, dated March 4, 2014.

(h) Exception to the Requirements of Paragraph (g) of This AD

    Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 767-27A0229, dated March 4, 2014, 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.''

(i) 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 (j) 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 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 must 
meet the certification basis of the airplane and the approval must 
specifically refer to this AD.
    (4) If the service information contains steps that are labeled 
as RC (Required for Compliance), those steps must be done to comply 
with this AD; any steps that are not labeled as RC are recommended. 
Those steps that are not labeled as RC may be deviated from, done as 
part of other actions, or done using accepted methods different from 
those identified in the specified service information without 
obtaining approval of an AMOC, provided the steps labeled as RC can 
be done and the airplane can be put back in a serviceable condition. 
Any substitutions or changes to steps labeled as RC require approval 
of an AMOC.

(j) Related Information

    (1) For more information about this AD, contact Allen 
Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; phone: 425-917-6487; fax: 425-917-6590; email: 
Allen.Rauschendorfer@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. 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 26, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-16004 Filed 7-8-14; 8:45 am]
BILLING CODE 4910-13-P
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