80 FR 20178 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 72 (April 15, 2015)

Page Range		20178-20181
FR Document		2015-08464

We propose to supersede Airworthiness Directive (AD) 2013-23- 03, which applies to 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. AD 2013-23-03 currently requires doing a detailed inspection of certain attach fittings for a cylindrical defect and replacing if necessary. Since we issued AD 2013- 23-03, we received a report that a machining defect was also found on some of the actuator assemblies inspected during manufacture. This defect could lead to fatigue cracking and subsequent fracture. For certain airplanes, this proposed AD would mandate new inspections of the inboard actuator attach fittings for machining defects, and overhaul or replacement, if necessary. This proposed AD would also limit the compliance time for doing the replacement for certain other airplanes. We are proposing 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.

Federal Register, Volume 80 Issue 72 (Wednesday, April 15, 2015)

[Federal Register Volume 80, Number 72 (Wednesday, April 15, 2015)]
[Proposed Rules]
[Pages 20178-20181]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2015-08464]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0828; Directorate Identifier 2014-NM-146-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 supersede Airworthiness Directive (AD) 2013-23-
03, which applies to 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. AD 2013-23-03 currently
requires doing a detailed inspection of certain attach fittings for a
cylindrical defect and replacing if necessary. Since we issued AD 2013-
23-03, we received a report that a machining defect was also found on
some of the actuator assemblies inspected during manufacture. This
defect could lead to fatigue cracking and subsequent fracture. For
certain airplanes, this proposed AD would mandate new inspections of
the inboard actuator attach fittings for machining defects, and
overhaul or replacement, if necessary. This proposed AD would also
limit the compliance time for doing the replacement for certain other
airplanes. We are proposing 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: We must receive comments on this proposed AD by June 1, 2015.

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, Washington. 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-2015-
0828.

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-2015-
0828; 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: 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:

Comments Invited

We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0828;
Directorate Identifier 2014-NM-146-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

On October 31, 2013, we issued AD 2013-23-03, Amendment 39-17658
(78 FR 68345, November 14, 2013), 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. AD 2013-23-03
requires inspecting to determine the part number of the inboard
actuator attach fittings of the outboard flap. For affected attach
fittings, AD 2013-23-03 requires doing a detailed inspection of the
attach fittings for a cylindrical defect and replacing if necessary. As
an option to the detailed inspection, AD 2013-23-03 allows replacement
of affected attach fittings. AD 2013-23-03 resulted from 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 issued AD 2013-23-03
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.

Actions Since AD 2013-23-03, Amendment 39-17658 (78 FR 68345, November
14, 2013) Was Issued

The preamble to AD 2013-23-03, Amendment 39-17658 (78 FR 68345,
November 14, 2013), specified that we considered the requirements
``interim action.'' AD 2013-23-03 explained that we might consider
further rulemaking to require a minimum thickness inspection of inboard
actuator attach fittings that are conically machined. Since we issued
AD 2013-23-03, we received a report that a machining defect was also
found on some of the actuator assemblies inspected during manufacture
at the point where the tapered machining transitioned to the
hemispherical machining at the top of the inner surface. Revised
service information has been issued and, for certain airplanes, this
proposed AD would mandate new

[[Page 20179]]

inspections of the inboard actuator attach fittings for machining
defects, and overhaul or replacement, if necessary. This proposed AD
would also limit the compliance time for doing the replacement, for
certain other airplanes.

Related Service Information Under 1 CFR part 51

We reviewed Boeing Alert Service Bulletin 747-57A2343, Revision 1,
dated June 23, 2014. The service information describes procedures for
new inspections of the inboard actuator attach fittings for machining
defects, and overhaul or replacement, if necessary. This service
information is reasonably available; see ADDRESSES for ways to access
this service information.

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.

Related AD

This proposed AD is related to AD 2005-20-18, Amendment 39-14312
(70 FR 57740, October 4, 2005), for Model 747-100, -200B, -200F, -200C,
-100B, -300 series airplanes. AD 2005-20-18 required nspecting and
overhauling, replacing, or repairing (as applicable) the actuator
attach fittings on the inboard and outboard flaps of the wing. The
replacement was done in accordance with Boeing Service Bulletin 747-
57A2316.

Proposed AD Requirements

This proposed AD would retain all of the requirements of AD 2013-
23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013). For certain
airplanes, this proposed AD would mandate new inspections of the
inboard actuator attach fittings for machining defects, and overhaul or
replacement, if necessary. This proposed AD would also limit the
compliance time for doing the replacement for certain other airplanes.
This proposed AD would also require accomplishing the actions specified
in the service information described previously.

Costs of Compliance

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

Estimated costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained inspection for part 7 work-hours x $85 $0 $595 $109,480.
number in AD 2013-23-03, per hour = $595.
Amendment 39-17658 (78 FR 68345,
November 14, 2013).
New proposed inspections for 8 work-hours x $85 0 680 125,120.
machining defect. per hour = $680.
Replacement for airplanes without 6 work-hours x $85 13,720 14,230 14,230 per airplane.
any defect. per hour = $510.
----------------------------------------------------------------------------------------------------------------

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

We have 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 that the 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 removing Airworthiness Directive (AD)
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013), and
adding the following new AD:

The Boeing Company: Docket No. FAA-2015-0828; Directorate Identifier
2014-NM-146-AD.

(a) Comments Due Date

The FAA must receive comments on this AD action by June 1, 2015.

(b) Affected ADs

This AD replaces AD 2013-23-03, Amendment 39-17658 (78 FR 68345,
November 14, 2013).

[[Page 20180]]

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, Revision 1, dated June 23, 2014.

(d) Subject

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. A machining defect was also found on some
actuator assemblies inspected during manufacture at the point where
the tapered machining transitioned to the hemispherical machining at
the top of the inner surface. This defect could lead to fatigue
cracking and subsequent fracture. 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) Retained Part Number Inspection

This paragraph restates the requirements of paragraph (g) of AD
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013),
with revised service information. Within 90 days after November 29,
2013 (the effective date of AD 2013-23-03): 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; or Boeing Alert Service Bulletin 747-57A2343, Revision 1,
dated June 23, 2014. As of the effective date of this AD, only
Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June
23, 2014, may be used.

(h) Retained Actions for Certain Attach Fittings

This paragraph restates the requirements of paragraph (h) of AD
2013-23-03, Amendment 39-17658 (78 FR 68345, November 14, 2013),
with revised service information. 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; or Boeing Alert Service Bulletin
747-57A2343, Revision 1, dated June 23, 2014. As of the effective
date of this AD, only Boeing Alert Service Bulletin 747-57A2343,
Revision 1, dated June 23, 2014, may be used. For airplanes on which
the detailed inspection is done before the effective date of this
AD: 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; or Boeing Alert Service Bulletin 747-57A2343,
Revision 1, dated June 23, 2014. 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) New Actions For Certain Airplanes on Which Any Cylindrical Defect
Is Found

For airplanes on which the detailed inspection required by
paragraph (h)(1) of this AD is done on or after the effective date
of this AD: If any cylindrical defect is found during any inspection
required by paragraph (h)(1) of this AD, before further flight, do
the actions specified in paragraph (i)(1) or (i)(2) of this AD.
(1) Determine the minimum wall thickness of the actuator attach
fitting either by doing an ultrasonic inspection or by mechanically
measuring the thickness and do a detailed inspection of the inner
conical section to determine if the machining defect is present, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2343, Revision 1, dated June 23, 2014.
(i) 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, Revision 1, dated June 23, 2014.
(ii) If the minimum thickness of the wall is 0.140 inch or
greater and the machining defect is present, before further flight,
do the actions specified in paragraph (i)(1)(ii)(A) or (i)(1)(ii)(B)
of this AD.
(A) Overhaul the inboard actuator attach fitting of the outboard
flap, in accordance with Part 5 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June
23, 2014.
(B) 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, Revision 1, dated June
23, 2014.
(iii) If the minimum thickness of the wall is 0.130 inch or
greater and less than 0.140 inch and the machining defect is not
present, within 48 months or 3,000 flight cycles after the effective
date of this AD, whichever occurs first, 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, Revision 1, dated June 23, 2014.
(iv) If the minimum thickness of the wall is 0.130 inch or
greater and less than 0.140 inch and the machining defect is
present, 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, Revision 1, dated June 23, 2014.
(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, Revision 1, dated June
23, 2014.

(j) New Actions for Airplanes on Which No Cylindrical Defects Are Found

If no cylindrical defect is found during any inspection required
by paragraph (h)(1) of this AD, within 24 months after the effective
date of this AD, do the actions specified in paragraph (j)(1) or
(j)(2) of this AD.
(1) Determine the minimum wall thickness of the actuator attach
fitting either by doing an ultrasonic inspection or by mechanically
measuring the thickness and do a detailed inspection of the inner
conical section to determine if the machining defect is present, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-57A2343, Revision 1, dated June 23, 2014.
(i) 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, Revision 1, dated June 23, 2014.
(ii) If the minimum thickness of the wall is 0.140 inch or
greater and the machining defect is present, before further flight,
do the actions specified in paragraph (j)(1)(ii)(A) or (j)(1)(ii)(B)
of this AD.
(A) Overhaul the inboard actuator attach fitting of the outboard
flap, in accordance with Part 5 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June
23, 2014.
(B) 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, Revision 1, dated June
23, 2014.

[[Page 20181]]

(iii) If the minimum thickness of the wall is 0.130 inch or
greater and less than 0.140 inch and the machining defect is not
present, within 48 months or 3,000 flight cycles after the effective
date of this AD, whichever occurs first, 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, Revision 1, dated June 23, 2014.
(iv) If the minimum thickness of the wall is 0.130 inch or
greater and less than 0.140 inch and the machining defect is
present, 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, Revision 1, dated June 23, 2014.
(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, Revision 1, dated June
23, 2014.

(k) New Inspection or Replacement for Certain Fittings That Were
Previously Inspected

For airplanes with any inboard actuator attach fitting having P/
N 65B08564-7 installed and the fitting was inspected in accordance
with Part 3 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-57A2343, dated September 12, 2013: Within 24
months after the effective date of this AD, do the actions specified
in paragraph (k)(1) or (k)(2) of this AD.
(1) Do a detailed inspection of the inner conical section for
machining defects only, in accordance with Part 3 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2343, Revision 1, dated June 23, 2014.
(i) If any machining defect is found and the minimum thickness
of the wall is 0.140 inch or greater: Before further flight, do the
actions specified in paragraph (k)(1)(i)(A) or (k)(1)(i)(B) of this
AD.
(A) Overhaul the inboard actuator attach fitting of the outboard
flap, in accordance with Part 5 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 747-57A2343, Revision 1, dated June
23, 2014.
(B) 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, Revision 1, dated June
23, 2014.
(ii) If any machining defect is found and the minimum thickness
of the wall is 0.130 inch or greater and less than 0.140 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, Revision 1, dated June 23, 2014.
(iii) If no machining defect is found and the minimum thickness
of the wall is 0.130 inch or greater and less than 0.140 inch:
Within 48 months or 3,000 flight cycles after the effective date of
this AD, whichever occurs first, 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, Revision 1, dated June 23, 2014.
(iv) If a machining defect is or is not found and 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, Revision 1, dated June
23, 2014.
(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, Revision 1, dated June
23, 2014.

(l) Part Installation Limitation

As of the effective date of this AD, no actuator attach fitting
having P/N 65B08564-7 that meets the requirements of CONDITION 5 or
CONDITION 6 defined in Boeing Alert Service Bulletin 747-57A2343,
dated September 12, 2013, may be installed on any airplane unless
the inspection specified in paragraph (k)(1) of this AD is done and
the applicable actions in paragraphs (k)(1)(i), (k)(1)(ii),
(k)(1)(iii), and (k)(1)(iv) are done within the applicable times
specified in paragraphs (k)(1)(i), (k)(1)(ii), (k)(1)(iii), and
(k)(1)(iv) of this AD.

(m) 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 (n)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair 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 any service information contains steps that are
identified as RC (Required for Compliance), those steps must be done
to comply with this AD; any steps that are not identified as RC are
recommended. Those steps that are not identified 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 steps identified as RC can be done
and the airplane can be put back in a serviceable condition. Any
substitutions or changes to steps identified as RC require approval
of an AMOC.
(5) AMOCs approved for AD 2013-23-03, Amendment 39-17658 (78 FR
68345, November 14, 2013) are approved as AMOCs for the
corresponding provisions of this AD.

(n) Related Information

(1) 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.
(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, Washington. For information on the availability
of this material at the FAA, call 425-227-1221.

Issued in Renton, Washington, on April 6, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-08464 Filed 4-14-15; 8:45 am]
BILLING CODE 4910-13-P

Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 20179

inspections of the inboard actuator FAA’s Determination Proposed AD Requirements
attach fittings for machining defects, This proposed AD would retain all of
and overhaul or replacement, if We are proposing this AD because we
evaluated all the relevant information the requirements of AD 2013–23–03,
necessary. This proposed AD would Amendment 39–17658 (78 FR 68345,
also limit the compliance time for doing and determined the unsafe condition
described previously is likely to exist or November 14, 2013). For certain
the replacement, for certain other airplanes, this proposed AD would
airplanes. develop in other products of the same
type design. mandate new inspections of the inboard
Related Service Information Under 1 actuator attach fittings for machining
Related AD defects, and overhaul or replacement, if
CFR part 51
necessary. This proposed AD would
This proposed AD is related to AD also limit the compliance time for doing
We reviewed Boeing Alert Service
2005–20–18, Amendment 39–14312 (70 the replacement for certain other
Bulletin 747–57A2343, Revision 1,
FR 57740, October 4, 2005), for Model airplanes. This proposed AD would also
dated June 23, 2014. The service
747–100, –200B, –200F, –200C, –100B, require accomplishing the actions
information describes procedures for
–300 series airplanes. AD 2005–20–18 specified in the service information
new inspections of the inboard actuator
required nspecting and overhauling, described previously.
attach fittings for machining defects,
replacing, or repairing (as applicable)
and overhaul or replacement, if the actuator attach fittings on the Costs of Compliance
necessary. This service information is inboard and outboard flaps of the wing. We estimate that this proposed AD
reasonably available; see ADDRESSES for The replacement was done in affects 184 airplanes of U.S. registry.
ways to access this service information. accordance with Boeing Service Bulletin We estimate the following costs to
747–57A2316. comply with this proposed AD:

ESTIMATED COSTS
Cost per
Action Labor cost Parts cost Cost on U.S. operators
product

Retained inspection for part number in AD 7 work-hours × $85 per hour = $0 $595 $109,480.
2013–23–03, Amendment 39–17658 (78 FR $595.
68345, November 14, 2013).
New proposed inspections for machining de- 8 work-hours × $85 per hour = 0 680 125,120.
fect. $680.
Replacement for airplanes without any defect .. 6 work-hours × $85 per hour = 13,720 14,230 14,230 per airplane.
$510.

We have received no definitive data Regulatory Findings The Proposed Amendment
that would enable us to provide a cost
We have determined that this Accordingly, under the authority
estimate for the on-condition actions proposed AD would not have federalism
specified in this AD. delegated to me by the Administrator,
implications under Executive Order the FAA proposes to amend 14 CFR part
Authority for This Rulemaking 13132. This proposed AD would not 39 as follows:
have a substantial direct effect on the
Title 49 of the United States Code States, on the relationship between the PART 39—AIRWORTHINESS
specifies the FAA’s authority to issue national Government and the States, or DIRECTIVES
rules on aviation safety. Subtitle I, on the distribution of power and
Section 106, describes the authority of responsibilities among the various ■ 1. The authority citation for part 39
the FAA Administrator. Subtitle VII, levels of government. continues to read as follows:
Aviation Programs, describes in more For the reasons discussed above, I
Authority: 49 U.S.C. 106(g), 40113, 44701.
detail the scope of the Agency’s certify that the proposed regulation:
authority. (1) Is not a ‘‘significant regulatory § 39.13 [Amended]
We are issuing this rulemaking under action’’ under Executive Order 12866,
■ 2. The FAA amends § 39.13 by
the authority described in Subtitle VII, (2) Is not a ‘‘significant rule’’ under
removing Airworthiness Directive (AD)
Part A, Subpart III, Section 44701, the DOT Regulatory Policies and
2013–23–03, Amendment 39–17658 (78
‘‘General requirements.’’ Under that Procedures (44 FR 11034, February 26,
FR 68345, November 14, 2013), and
section, Congress charges the FAA with 1979),
adding the following new AD:
promoting safe flight of civil aircraft in (3) Will not affect intrastate aviation
in Alaska, and The Boeing Company: Docket No. FAA–
air commerce by prescribing regulations 2015–0828; Directorate Identifier 2014–
for practices, methods, and procedures (4) Will not have a significant
NM–146–AD.
economic impact, positive or negative,
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the Administrator finds necessary for
safety in air commerce. This regulation on a substantial number of small entities (a) Comments Due Date
is within the scope of that authority under the criteria of the Regulatory The FAA must receive comments on this
Flexibility Act. AD action by June 1, 2015.
because it addresses an unsafe condition
that is likely to exist or develop on List of Subjects in 14 CFR Part 39 (b) Affected ADs
products identified in this rulemaking Air transportation, Aircraft, Aviation This AD replaces AD 2013–23–03,
action. safety, Incorporation by reference, Amendment 39–17658 (78 FR 68345,
Safety. November 14, 2013).

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Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules 20181

(iii) If the minimum thickness of the wall the effective date of this AD, whichever approval of an AMOC provided the steps
is 0.130 inch or greater and less than 0.140 occurs first, replace the inboard actuator identified as RC can be done and the airplane
inch and the machining defect is not present, attach fitting of the outboard flap, in can be put back in a serviceable condition.
within 48 months or 3,000 flight cycles after accordance with Part 4 of the Any substitutions or changes to steps
the effective date of this AD, whichever Accomplishment Instructions of Boeing Alert identified as RC require approval of an
occurs first, replace the inboard actuator Service Bulletin 747–57A2343, Revision 1, AMOC.
attach fitting of the outboard flap, in dated June 23, 2014. (5) AMOCs approved for AD 2013–23–03,
accordance with Part 4 of the (iv) If a machining defect is or is not found Amendment 39–17658 (78 FR 68345,
Accomplishment Instructions of Boeing Alert and the minimum thickness of the wall is November 14, 2013) are approved as AMOCs
Service Bulletin 747–57A2343, Revision 1, less than 0.130 inch: Before further flight, for the corresponding provisions of this AD.
dated June 23, 2014. replace the inboard actuator attach fitting of
(iv) If the minimum thickness of the wall the outboard flap, in accordance with Part 4 (n) Related Information
is 0.130 inch or greater and less than 0.140 of the Accomplishment Instructions of (1) For more information about this AD,
inch and the machining defect is present, Boeing Alert Service Bulletin 747–57A2343, contact Nathan Weigand, Aerospace
before further flight, replace the inboard Revision 1, dated June 23, 2014. Engineer, Airframe Branch, ANM–120S,
actuator attach fitting of the outboard flap, in (2) Replace the inboard actuator attach FAA, Seattle Aircraft Certification Office,
accordance with Part 4 of the fitting of the outboard flap, in accordance 1601 Lind Avenue SW., Renton, WA 98057–
Accomplishment Instructions of Boeing Alert with Part 4 of the Accomplishment 3356; phone: 425–917–6428; fax: 425–917–
Service Bulletin 747–57A2343, Revision 1, Instructions of Boeing Alert Service Bulletin 6590; email: nathan.p.weigand@faa.gov.
dated June 23, 2014. 747–57A2343, Revision 1, dated June 23, (2) For service information identified in
(2) Replace the inboard actuator attach 2014. this AD, contact Boeing Commercial
fitting of the outboard flap, in accordance Airplanes, Attention: Data & Services
with Part 4 of the Accomplishment (l) Part Installation Limitation Management, P. O. Box 3707, MC 2H–65,
Instructions of Boeing Alert Service Bulletin As of the effective date of this AD, no Seattle, WA 98124–2207; telephone 206–
747–57A2343, Revision 1, dated June 23, actuator attach fitting having P/N 65B08564– 544–5000, extension 1; fax 206–766–5680;
2014. 7 that meets the requirements of CONDITION Internet https://www.myboeingfleet.com. You
5 or CONDITION 6 defined in Boeing Alert may view this referenced service information
(k) New Inspection or Replacement for
Service Bulletin 747–57A2343, dated at the FAA, Transport Airplane Directorate,
Certain Fittings That Were Previously
September 12, 2013, may be installed on any 1601 Lind Avenue SW., Renton, Washington.
Inspected
airplane unless the inspection specified in For information on the availability of this
For airplanes with any inboard actuator paragraph (k)(1) of this AD is done and the material at the FAA, call 425–227–1221.
attach fitting having P/N 65B08564–7 applicable actions in paragraphs (k)(1)(i),
installed and the fitting was inspected in Issued in Renton, Washington, on April 6,
(k)(1)(ii), (k)(1)(iii), and (k)(1)(iv) are done
accordance with Part 3 of the 2015.
within the applicable times specified in
Accomplishment Instructions of Boeing Alert paragraphs (k)(1)(i), (k)(1)(ii), (k)(1)(iii), and John P. Piccola, Jr.,
Service Bulletin 747–57A2343, dated (k)(1)(iv) of this AD. Acting Manager, Transport Airplane
September 12, 2013: Within 24 months after Directorate, Aircraft Certification Service.
the effective date of this AD, do the actions (m) Alternative Methods of Compliance
[FR Doc. 2015–08464 Filed 4–14–15; 8:45 am]
specified in paragraph (k)(1) or (k)(2) of this (AMOCs)
BILLING CODE 4910–13–P
AD. (1) The Manager, Seattle Aircraft
(1) Do a detailed inspection of the inner Certification Office (ACO), FAA, has the
conical section for machining defects only, in authority to approve AMOCs for this AD, if
accordance with Part 3 of the requested using the procedures found in 14 DEPARTMENT OF TRANSPORTATION
Accomplishment Instructions of Boeing Alert CFR 39.19. In accordance with 14 CFR 39.19,
Service Bulletin 747–57A2343, Revision 1, send your request to your principal inspector Federal Aviation Administration
dated June 23, 2014. or local Flight Standards District Office, as
(i) If any machining defect is found and the appropriate. If sending information directly 14 CFR Part 39
minimum thickness of the wall is 0.140 inch to the manager of the ACO, send it to the
[Docket No. FAA–2015–0827; Directorate
or greater: Before further flight, do the actions attention of the person identified in
Identifier 2014–NM–008–AD]
specified in paragraph (k)(1)(i)(A) or paragraph (n)(1) of this AD. Information may
(k)(1)(i)(B) of this AD. be emailed to: 9-ANM-Seattle-ACO-AMOC- RIN 2120–AA64
(A) Overhaul the inboard actuator attach Requests@faa.gov.
fitting of the outboard flap, in accordance (2) Before using any approved AMOC, Airworthiness Directives; Bombardier,
with Part 5 of the Accomplishment notify your appropriate principal inspector, Inc. Airplanes
Instructions of Boeing Alert Service Bulletin or lacking a principal inspector, the manager
747–57A2343, Revision 1, dated June 23, of the local flight standards district office/ AGENCY: Federal Aviation
2014. certificate holding district office. Administration (FAA), DOT.
(B) Replace the inboard actuator attach (3) An AMOC that provides an acceptable
ACTION: Notice of proposed rulemaking
fitting of the outboard flap, in accordance level of safety may be used for any repair
with Part 4 of the Accomplishment required by this AD if it is approved by the (NPRM).
Instructions of Boeing Alert Service Bulletin Boeing Commercial Airplanes Organization
747–57A2343, Revision 1, dated June 23, Designation Authorization (ODA) that has SUMMARY: We propose to supersede
2014. been authorized by the Manager, Seattle Airworthiness Directive (AD) 2011–07–
(ii) If any machining defect is found and ACO, to make those findings. For a repair 10, for certain Bombardier, Inc. Model
the minimum thickness of the wall is 0.130 method to be approved, the repair must meet BD–100–1A10 (Challenger 300)
inch or greater and less than 0.140 inch: the certification basis of the airplane, and the airplanes. AD 2011–07–10 currently
Before further flight, replace the inboard approval must specifically refer to this AD. requires revising the Airworthiness
mstockstill on DSK4VPTVN1PROD with PROPOSALS

actuator attach fitting of the outboard flap, in (4) If any service information contains Limitations section of the Instructions
accordance with Part 4 of the steps that are identified as RC (Required for for Continued Airworthiness; doing
Accomplishment Instructions of Boeing Alert Compliance), those steps must be done to
detailed visual inspections; removing
Service Bulletin 747–57A2343, Revision 1, comply with this AD; any steps that are not
dated June 23, 2014. identified as RC are recommended. Those discrepant material; cleaning the
(iii) If no machining defect is found and steps that are not identified as RC may be surfaces of the valves, the plug of the
the minimum thickness of the wall is 0.130 deviated from using accepted methods in sensing port, and the cabin pressure-
inch or greater and less than 0.140 inch: accordance with the operator’s maintenance sensing port plug; securing the
Within 48 months or 3,000 flight cycles after or inspection program without obtaining insulation; installing a new safety valve,

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Document Created: 2015-12-18 11:13:51
Document Modified: 2015-12-18 11:13:51

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by June 1, 2015.
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: [email protected]
FR Citation		80 FR 20178
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

80 FR 20178 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 80, Issue 72 (April 15, 2015)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration