
[Federal Register Volume 78, Number 220 (Thursday, November 14, 2013)]
[Rules and Regulations]
[Pages 68345-68347]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-27015]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0871; Directorate Identifier 2013-NM-187-AD; 
Amendment 39-17658; AD 2013-23-03]
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 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR 
series airplanes. This AD requires inspecting to determine the part 
number of the inboard actuator attach fittings of the outboard flap. 
For affected attach fittings, this AD requires doing a detailed 
inspection of the attach fittings for a cylindrical defect and 
replacing if necessary. As an option to the detailed inspection, this 
AD allows replacement of affected attach fittings. This AD was prompted 
by a report of the fracture of an inboard actuator attach fitting of 
the outboard flap. An inspection of the attach fitting revealed that it 
was incorrectly machined with a cylindrical profile instead of a 
conical profile, resulting in reduced wall thickness. We are issuing 
this AD to detect and correct defective inboard actuator attach 
fittings which, combined with loss of the outboard actuator load path, 
could result in uncontrolled retraction of the outboard flap, damage to 
flight control systems, and consequent reduced controllability of the 
airplane.

DATES: This AD is effective November 29, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of November 29, 
2013.
    We must receive comments on this AD by December 30, 2013.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    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 review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. 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; 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: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax: 
425-917-6590; email: nathan.p.weigand@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We received a report a report of the fracture of a No. 7 inboard 
actuator attach fitting of the outboard flap. It was determined that 
the fracture occurred in the internal conical machined area. 
Investigation revealed that a portion of the interior surface was 
machined with a cylindrical profile instead of a conical profile. This 
resulted in reduced wall thickness and subsequent fracture; the 
thickness of the fitting was approximately half the designed wall 
thickness. We also received reports of other attach fittings with a 
cylindrical defect with reduced wall thickness. This condition combined 
with loss of the outboard actuator load path, if not corrected, could 
result in uncontrolled retraction of the outboard flap and subsequent 
damage to flight control systems at the rear spar, and consequent 
reduced controllability of the airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-57A2343, dated 
September 12, 2013. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov.

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 inspecting to determine the part number of the 
inboard actuator attach fittings of the outboard flap. For affected 
attach fittings, this AD requires doing a detailed inspection of the 
attach fittings for a cylindrical defect and replacing if necessary. As 
an option to the detailed inspection, this AD allows replacement of the 
affected attach fittings.
    The FAA worked in conjunction with industry, under the 
Airworthiness Directives Implementation Aviation Rulemaking Committee, 
to enhance the

[[Page 68346]]

AD system. One enhancement was a new process for annotating which steps 
in the service information are required for compliance 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 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.

Interim Action

    We consider this AD interim action. The manufacturer is currently 
developing a modification that will address the unsafe condition 
identified in this AD. Once this modification is developed, approved, 
and available, we might consider additional rulemaking.
    We are also considering further rulemaking to require a minimum 
thickness inspection of inboard actuator attach fittings that are 
conically machined. However, the planned compliance time for the 
minimum thickness inspection would allow enough time to provide notice 
and opportunity for prior public comment on the merits of that 
inspection. This AD only addresses the unsafe condition associated with 
inboard actuator attach fittings of the outboard flap that have a 
cylindrical defect.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
defective actuator attach fittings, combined with loss of the outboard 
actuator load path, could result in uncontrolled retraction of the 
outboard flap, damage to flight control systems, and consequent reduced 
controllability of the airplane. Therefore, we find that notice and 
opportunity for prior public comment are impracticable 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-2013-0871 and 
Directorate Identifier 2013-NM-187-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

    We estimate that this AD affects 184 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection for part number..........  7 work-hour x $85 per                $0             $595         $109,480
                                       hour = $595.
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    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition actions specified in this AD.

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,
    (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:

[[Page 68347]]

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):

2013-23-03 The Boeing Company: Amendment 39-17658; Docket No. FAA-
2013-0871; Directorate Identifier 2013-NM-187-AD.

(a) Effective Date

    This AD is effective November 29, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-
400D, 747-400F, and 747SR series airplanes, certificated in any 
category, as identified in Boeing Alert Service Bulletin 747-
57A2343, dated September 12, 2013.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report of the fracture of an inboard 
actuator attach fitting of the outboard flap. An inspection of the 
attach fitting revealed that it was incorrectly machined with a 
cylindrical profile instead of a conical profile, resulting in 
reduced wall thickness. We are issuing this AD to detect and correct 
defective inboard actuator attach fittings which, combined with loss 
of the outboard actuator load path, could result in uncontrolled 
retraction of the outboard flap, damage to flight control systems, 
and consequent reduced controllability of the airplane.

(f) Compliance

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

(g) Part Number Inspection

    Within 90 days after the effective date of this AD: Inspect to 
determine the part number of the inboard actuator attach fittings of 
the outboard flaps, in accordance with Part 1 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2343, dated 
September 12, 2013.

(h) Actions for Certain Attach Fittings

    If, during the inspection required by paragraph (g) of this AD, 
any inboard actuator attach fitting having part number (P/N) 
65B08564-7 is found, before further flight, do the actions specified 
in paragraph (h)(1) or (h)(2) of this AD.
    (1) Do a detailed inspection of the inboard actuator attach 
fitting for a cylindrical defect, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2343, dated September 12, 2013. If any cylindrical defect is 
found, before further flight, do the actions specified in paragraph 
(h)(1)(i) or (h)(1)(ii) of this AD.
    (i) Do a minimum thickness inspection of the inboard actuator 
attach fitting to determine minimum wall thickness of the actuator 
fitting assembly, in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2343, dated 
September 12, 2013. If the minimum thickness of the wall is less 
than 0.130 inch: Before further flight, replace the inboard actuator 
attach fitting of the outboard flap, in accordance with Part 4 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 747 
57A2343, dated September 12, 2013.
    (ii) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, dated September 12, 
2013.
    (2) Replace the inboard actuator attach fitting of the outboard 
flap, in accordance with Part 4 of the Accomplishment Instructions 
of Boeing Alert Service Bulletin 747-57A2343, dated September 12, 
2013.

(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

    For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6428; fax: 425-917-6590; email: 
nathan.p.weigand@faa.gov.

(k) 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 747-57A2343, dated September 
12, 2013.
    (ii) Reserved.
    (3) 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.
    (4) You may review copies of the referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, Washington. 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 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 31, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-27015 Filed 11-13-13; 8:45 am]
BILLING CODE 4910-13-P


