80_FR_80489 80 FR 80242 - Airworthiness Directives; The Boeing Company Airplanes

80 FR 80242 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 247 (December 24, 2015)

Page Range80242-80247
FR Document2015-30881

We are superseding 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 required a detailed inspection of certain attach fittings for a cylindrical defect, and replacement if necessary. For certain airplanes, this new AD requires new inspections of the inboard actuator attach fittings for machining defects, and overhaul or replacement if necessary. This new AD also limits the compliance time for doing the replacement for certain other airplanes. This AD was prompted by 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. 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.

Federal Register, Volume 80 Issue 247 (Thursday, December 24, 2015)
[Federal Register Volume 80, Number 247 (Thursday, December 24, 2015)]
[Rules and Regulations]
[Pages 80242-80247]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-30881]


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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; 
Amendment 39-18341; AD 2015-25-03]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding 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 required a detailed 
inspection of certain attach fittings for a cylindrical defect, and 
replacement if necessary. For certain airplanes, this new AD requires 
new inspections of the inboard actuator attach fittings for machining 
defects, and overhaul or replacement if necessary. This new AD also 
limits the compliance time for doing the replacement for certain other 
airplanes. This AD was prompted by 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. 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 January 28, 2016.
    The Director of the Federal Register approved the incorporation by 
reference

[[Page 80243]]

of a certain publication listed in this AD as of January 28, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 29, 2013 (78 FR 68345, November 14, 2013).

ADDRESSES: 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. It is also available on the Internet at https://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.govby 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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

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: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2013-23-03, Amendment 39-17658 (78 FR 68345, 
November 14, 2013). AD 2013-23-03 applied 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. The 
NPRM published in the Federal Register on April 15, 2015 (80 FR 20178). 
The NPRM was prompted by a report that a machining defect was also 
found on some of the actuator assemblies inspected during manufacture. 
The NPRM proposed to continue to require doing a detailed inspection of 
certain attach fittings for a cylindrical defect and replacing if 
necessary. This defect could lead to fatigue cracking and subsequent 
fracture. For certain airplanes, the NPRM proposed to mandate new 
inspections of the inboard actuator attach fittings for machining 
defects, and overhaul or replacement, if necessary. The NPRM also 
proposed to limit the compliance time for doing the replacement for 
certain other airplanes. 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (80 
FR 20178, April 15, 2015) and the FAA's response to each comment.

Request to Add Terminating Action

    Boeing asked that we revise the NPRM (80 FR 20178, April 15, 2015) 
to specify that no additional action is required for a wall thickness 
of 0.140 inch or greater with no machining defect present, as also 
provided in Table 1 of Boeing Alert Service Bulletin 747-57A2443, 
Revision 1, dated June 23, 2014.
    We agree with the commenter that no additional action is required 
for a wall thickness of 0.140 inch or greater with no machining defect 
present. However, we do not agree with the request to revise the AD 
because if this condition exists, no action is required by this AD. 
Only actions that are required to address the identified unsafe 
condition are specified in this AD. We have made no change to the AD in 
this regard.

Request to Revise Certain Requirements

    Paragraph (k) of the proposed AD (80 FR 20178, April 15, 2015) 
would have affected certain inboard actuator attach fittings that were 
inspected using Boeing Alert Service Bulletin 747-57A2443, dated 
September 12, 2013. United Airlines (UAL) requested that we remove this 
inspection criterion. UAL noted that there was no requirement to 
identify the actuators; therefore, operators would not be likely to 
positively identify them. UAL added that actuators are not likely to be 
tracked in position, and could have been moved between airplanes as a 
result of maintenance. UAL also stated that, in general, it would be 
better if the AD as a whole was worded not to depend on a record of 
previous inspection accomplishment, but rather on parts identification.
    We acknowledge the commenter's concerns. We realize that paragraph 
(k) of this AD is predicated on the fact that operators kept records 
from the inspection specified in Boeing Alert Service Bulletin 747-
57A2443, dated September 12, 2013. The intent of this AD is to either 
replace inboard actuator attach fittings having part number (P/N) 
65B08564-7, or to inspect P/N 65B08564-7 for cylindrical defects, 
machining defects, and wall thickness, and accomplish applicable 
corrective actions. For that reason we have changed the introductory 
text of paragraph (k) of this AD so that it applies to airplanes on 
which doing the detailed inspection required by paragraph (h)(1) of 
this AD was done before the effective date of this AD and a cylindrical 
defect was found but a replacement was not done. We have also revised 
paragraph (k)(1) of this AD to require an ultrasonic inspection to 
determine the minimum thickness or mechanically determine the minimum 
thickness and to allow a records review for the inspections. This 
change ensures all inspections are done on airplanes with P/N 65B08564-
7 that did not replace P/N 65B08564-7 after complying with AD 2013-23-
03, Amendment 39-17658 (78 FR 68345, November 14, 2013).
    To address airplanes on which inboard actuator attach fittings were 
replaced after complying with paragraph (h)(1) of AD 2013-23-03, 
Amendment 39-17658 (78 FR 68345, November 14, 2013), we have added new 
paragraph (m) to this AD, which specifies that for airplanes on which 
the detailed inspection required by paragraph (h)(1) of this AD is done 
before the effective date of this AD and the inboard actuator attach 
fitting has been replaced since that inspection, the inspection to 
determine the part number specified in paragraph (g) of this AD must be 
done within 90 days after the effective date of this AD, and the 
applicable actions specified in paragraphs (h), (i), and (j) of this AD 
must be done within the applicable times specified in paragraphs (h), 
(i), and (j) of this AD. We have also added a records review as an 
option if records are available that can conclusively determine the 
part number. We

[[Page 80244]]

redesignated subsequent paragraphs accordingly.

Request to Add Inspection

    UAL stated that the actions specified in paragraph (l) of the 
proposed AD (80 FR 20178, April 15, 2015) would also depend on the 
record of findings from inspections made in accordance with AD 2013-23-
03, Amendment 39-17658 (78 FR 68345, November 14, 2013). UAL added that 
there was no AD requirement to record these findings. UAL noted that 
operators conducted the inspections and took actions that were 
required. UAL stated that it would be better to call out a new 
inspection in the AD to determine which condition the actuator is in, 
and then take action as appropriate.
    We acknowledge the commenter's concerns. We have revised paragraph 
(l) of this AD to specify that no actuator attach fitting having P/N 
65B08564-7 may be installed on any airplane unless the inspection 
specified in paragraph (h)(1) of this AD is done prior to installation 
and the applicable actions specified in paragraphs (i) and (j) of this 
AD are done within the applicable times specified in paragraphs (i) and 
(j) of this AD. We have also added a records review as an option if 
records are available that can conclusively determine if the actions 
have been done.

Change to Paragraph (h)(2) of the Proposed AD ((80 FR 20178, April 15, 
2015)

    We have revised paragraph (h)(2) of this AD by referring to Boeing 
Alert Service Bulletin 747-57A2443, Revision 1, dated June 23, 2014, as 
an appropriate source of service information for accomplishing the 
required actions.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 20178, April 15, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 20178, April 15, 2015).
    We also determined that this change will not increase the economic 
burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-57A2443, dated 
September 12, 2013; and Boeing Alert Service Bulletin 747-57A2443, 
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 because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

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
              Action                    Labor cost         Parts cost        product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Retained inspection for part       7 work-hours x $85                $0            $595  $109,480
 number in AD 2013[dash]23-03,      per hour = $595.
 Amendment 39[dash]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 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:

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.

[[Page 80245]]

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:
2015-25-03 The Boeing Company: Amendment 39-18341; Docket No. FAA-
2015-0828; Directorate Identifier 2014-NM-146-AD.

(a) Effective Date

    This AD is effective January 28, 2016.

(b) Affected ADs

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

(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-
57A2443, 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 With Revised Service Information

    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 747-57A2443, dated September 12, 
2013; or Boeing Alert Service Bulletin 747-57A2443, Revision 1, 
dated June 23, 2014. As of the effective date of this AD, only 
Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014, may be used.

(h) Retained Actions for Certain Attach Fittings With Revised Service 
Information

    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-
57A2443, dated September 12, 2013; or Boeing Alert Service Bulletin 
747-57A2443, Revision 1, dated June 23, 2014. As of the effective 
date of this AD, only Boeing Alert Service Bulletin 747-57A2443, 
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 747-57A2443, dated 
September 12, 2013; or Boeing Alert Service Bulletin 747-57A2443, 
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 747-57A2443, 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 747-57A2443, 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 747-57A2443, dated September 12, 
2013; or Boeing Alert Service Bulletin 747-57A2443, Revision 1, 
dated June 23, 2014. As of the effective date of this AD, only 
Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014, may be used.

(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 747-57A2443, 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-
57A2443, 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 747-57A2443, 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 747-57A2443, 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 747-57A2443, 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-
57A2443, 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 747-57A2443, 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 747-57A2443, Revision 1, dated June 23, 2014.

[[Page 80246]]

    (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 
57A2443, 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 747-57A2443, 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 747-57A2443, 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 747-57A2443, 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-
57A2443, 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 747-57A2443, Revision 1, dated June 
23, 2014.

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

    For airplanes on which the detailed inspection required by 
paragraph (h)(1) of this AD is done before the effective date of 
this AD, except as required by paragraph (m) of this AD: If any 
cylindrical defect is found during any inspection required by 
paragraph (h)(1) of this AD and the replacement of the inboard 
actuator attach fitting of the outboard flap was not done as 
specified in Part 4 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-57A2443, 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 and do an ultrasonic inspection to determine the 
minimum thickness or mechanically determine the minimum thickness, 
in accordance with Part 3 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated June 
23, 2014. A review of airplane maintenance records, if available, is 
acceptable to determine the wall thickness and to determine if there 
are machining defects, provided wall thickness and machining defects 
can be positively determined from the records review.
    (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 747-57A2443, 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 747-57A2443, 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-
57A2443, 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-
57A2443, 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 747-57A2443, 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 747-57A2443, Revision 1, dated June 
23, 2014.

(l) Parts Installation Limitation

    As of the effective date of this AD, no actuator attach fitting 
having P/N 65B08564-7 may be installed on any airplane unless the 
inspection specified in paragraph (h)(1) of this AD is done prior to 
installation and the applicable actions specified in paragraphs (i) 
and (j) of this AD are done within the applicable times specified in 
paragraphs (i) and (j) of this AD. A review of airplane maintenance 
records, if available, is acceptable to determine if the inspection 
and applicable actions have been done, provided the inspection and 
actions can be positively determined from the records review.

(m) Action for Parts Installed After AD 2013-23-03, Amendment 39-17658 
(78 FR 68345, November 14, 2013) Was Accomplished

    For airplanes on which the detailed inspection required by 
paragraph (h)(1) of this AD is done before the effective date of 
this AD and the inboard actuator attach fitting was replaced since 
that 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 and, for inboard actuator attach 
fittings having P/N 65B08564-7, do the applicable actions specified 
in paragraphs (h), (i), and (j) of this AD within the applicable 
times specified in paragraphs (h), (i), and (j) of this AD. A review 
of airplane maintenance records, if available, is acceptable to 
determine the part number, provided the part number can be 
positively determined from the records review.

(n) 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 (o) 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 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 an airworthy 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.

(o) Related Information

    For more information about this AD, contact Nathan Weigand, 
Aerospace

[[Page 80247]]

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].

(p) 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.
    (3) The following service information was approved for IBR on 
January 28, 2016.
    (i) Boeing Alert Service Bulletin 747-57A2443, Revision 1, dated 
June 23, 2014.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
November 29, 2013 (78 FR 68345, November 14, 2013).
    (i) Boeing Alert Service Bulletin 747-57A2443, dated September 
12, 2013.
    (ii) Reserved.
    (5) 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.
    (6) 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.
    (7) 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 November 24, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,Aircraft Certification Service.
[FR Doc. 2015-30881 Filed 12-23-15; 8:45 am]
 BILLING CODE 4910-13-P



                                            80242            Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations

                                            modification Number 55128S18242; or P/N                  district office. The AMOC approval letter             National Archives and Records
                                            F2511373420000, post-modification Number                 must specifically reference this AD.                  Administration (NARA). For information on
                                            55128S18242) of the cockpit instrument                      (2) Contacting the Manufacturer: For any           the availability of this material at NARA, call
                                            panel does not constitute terminating action             requirement in this AD to obtain corrective           202–741–6030, or go to: http://
                                            for the repetitive inspections required by               actions from a manufacturer, the action must          www.archives.gov/federal-register/cfr/ibr-
                                            paragraph (g) of this AD.                                be accomplished using a method approved               locations.html.
                                              (ii) If, during the inspection required by             by the Manager, International Branch, ANM–
                                                                                                     116, Transport Airplane Directorate, FAA; or            Issued in Renton, Washington, on
                                            paragraph (h)(2) of this AD, any cracking is                                                                   December 9, 2015.
                                            found in bracket No. 7 of the cockpit                    the EASA; or Airbus’s EASA DOA. If
                                                                                                     approved by the DOA, the approval must                Michael Kaszycki,
                                            instrument panel: Although Airbus Service
                                            Bulletin A330–25–3538, Revision 02, dated                include the DOA-authorized signature.                 Acting Manager, Transport Airplane
                                            April 24, 2014; and Airbus Service Bulletin                 (3) Required for Compliance (RC): Except           Directorate, Aircraft Certification Service.
                                            A340–25–4351, Revision 01, dated January                 as required by paragraph (h)(2)(ii) of this AD,       [FR Doc. 2015–31714 Filed 12–23–15; 8:45 am]
                                            31, 2014; specify to contact Airbus for repair           if Airbus Service Bulletin A330–25–3538,
                                                                                                                                                           BILLING CODE 4910–13–P
                                            instructions, and specify that action as ‘‘RC’’          Revision 02, dated April 24, 2014; or Airbus
                                            (Required for Compliance), repair the                    Service Bulletin A340–25–4351, Revision 01,
                                                                                                     dated January 31, 2014; contain procedures
                                            cracking before further flight using a repair                                                                  DEPARTMENT OF TRANSPORTATION
                                                                                                     or tests that are identified as RC, those
                                            method approved by the Manager,
                                                                                                     procedures and tests must be done to comply
                                            International Branch, ANM–116, Transport                                                                       Federal Aviation Administration
                                                                                                     with this AD; any procedures and tests that
                                            Airplane Directorate, FAA; or the European
                                                                                                     are not identified as RC are recommended.
                                            Aviation Safety Agency (EASA); or Airbus’s
                                                                                                     Those procedures and tests that are not               14 CFR Part 39
                                            EASA Design Organization Approval (DOA).
                                                                                                     identified as RC may be deviated from, using
                                            (i) Optional Terminating Modification for                accepted methods in accordance with the               [Docket No. FAA–2015–0828; Directorate
                                            Paragraph (g) of This AD                                 operators maintenance or inspection program           Identifier 2014–NM–146–AD; Amendment
                                                                                                     without obtaining approval of an AMOC,                39–18341; AD 2015–25–03]
                                               Modifying an airplane by replacing bracket
                                                                                                     provided the procedures and tests identified
                                            No. 6 of the cockpit instrument panel with                                                                     RIN 2120–AA64
                                                                                                     as RC can be done and the airplane can be
                                            a new, reinforced bracket, in accordance with
                                                                                                     put back in an airworthy condition. Any
                                            the Accomplishment Instructions of Airbus                                                                      Airworthiness Directives; The Boeing
                                                                                                     substitutions or changes to procedures or
                                            Service Bulletin A330–25–3548, dated
                                            October 31, 2013; or Airbus Service Bulletin
                                                                                                     tests identified as RC require approval of an         Company Airplanes
                                                                                                     AMOC.
                                            A340–25–4354, dated October 31, 2013; as                                                                       AGENCY:  Federal Aviation
                                            applicable; terminates the repetitive                    (l) Related Information                               Administration (FAA), DOT.
                                            inspections required by paragraph (g) of this               (1) Refer to Mandatory Continuing
                                            AD.                                                                                                            ACTION: Final rule.
                                                                                                     Airworthiness Information (MCAI) EASA
                                            (j) Credit for Previous Actions                          Airworthiness Directive 2014–0127, dated              SUMMARY:    We are superseding
                                                                                                     May 15, 2014, for related information. This
                                               This paragraph provides credit for actions                                                                  Airworthiness Directive (AD) 2013–23–
                                                                                                     MCAI may be found in the AD docket on the
                                            required by paragraphs (g) and (h) of this AD,           Internet at http://www.regulations.gov/               03, which applies to certain The Boeing
                                            if those actions were performed before the               #!documentDetail;D=FAA-2015-0083-0002.                Company Model 747–100, 747–100B,
                                            effective date of this AD using the service                 (2) Service information identified in this         747–100B SUD, 747–200B, 747–200C,
                                            information identified in paragraph (j)(1),              AD that is not incorporated by reference is           747–200F, 747–300, 747–400, 747–
                                            (j)(2), or (j)(3) of this AD, which is not               available at the addresses specified in               400D, 747–400F, and 747SR series
                                            incorporated by reference in this AD.                    paragraphs (m)(3) and (m)(4) of this AD.
                                               (1) Airbus Service Bulletin A330–25–3538,                                                                   airplanes. AD 2013–23–03 required a
                                            dated September 10, 2013.                                (m) Material Incorporated by Reference                detailed inspection of certain attach
                                               (2) Airbus Service Bulletin A330–25–3538,                (1) The Director of the Federal Register           fittings for a cylindrical defect, and
                                            Revision 01, dated April 24, 2014.                       approved the incorporation by reference               replacement if necessary. For certain
                                               (3) Airbus Service Bulletin A340–25–4351,             (IBR) of the service information listed in this       airplanes, this new AD requires new
                                            dated September 10, 2014.                                paragraph under 5 U.S.C. 552(a) and 1 CFR             inspections of the inboard actuator
                                            (k) Other FAA AD Provisions                              part 51.                                              attach fittings for machining defects,
                                                                                                        (2) You must use this service information          and overhaul or replacement if
                                               The following provisions also apply to this           as applicable to do the actions required by
                                            AD:                                                                                                            necessary. This new AD also limits the
                                                                                                     this AD, unless this AD specifies otherwise.          compliance time for doing the
                                               (1) Alternative Methods of Compliance                    (i) Airbus Service Bulletin A330–25–3538,
                                            (AMOCs): The Manager, International                      Revision 02, dated April 24, 2014.                    replacement for certain other airplanes.
                                            Branch, ANM–116, Transport Airplane                         (ii) Airbus Service Bulletin A330–25–3548,         This AD was prompted by a report that
                                            Directorate, FAA, has the authority to                   dated October 31, 2013.                               a machining defect was also found on
                                            approve AMOCs for this AD, if requested                     (iii) Airbus Service Bulletin A340–25–             some of the actuator assemblies
                                            using the procedures found in 14 CFR 39.19.              4351, Revision 01, dated January 31, 2014.            inspected during manufacture. This
                                            In accordance with 14 CFR 39.19, send your                  (iv) Airbus Service Bulletin A340–25–              defect could lead to fatigue cracking and
                                            request to your principal inspector or local             4354, dated October 31, 2013.                         subsequent fracture. We are issuing this
                                            Flight Standards District Office, as                        (3) For service information identified in
                                            appropriate. If sending information directly                                                                   AD to detect and correct defective
                                                                                                     this AD, contact Airbus SAS, Airworthiness
                                            to the International Branch, send it to ATTN:            Office—EAL, 1 Rond Point Maurice Bellonte,            inboard actuator attach fittings which,
                                            Vladimir Ulyanov, Aerospace Engineer,                    31707 Blagnac Cedex, France; telephone +33            combined with loss of the outboard
                                            International Branch, ANM–116, Transport                 5 61 93 36 96; fax +33 5 61 93 45 80; email           actuator load path, could result in
                                            Airplane Directorate, FAA, 1601 Lind                     airworthiness.A330-A340@airbus.com;                   uncontrolled retraction of the outboard
                                            Avenue SW., Renton, WA 98057–3356;                       Internet http://www.airbus.com.                       flap, damage to flight control systems,
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                                            telephone 425–227–1138; fax 425–227–1149.                   (4) You may view this service information          and consequent reduced controllability
                                            Information may be emailed to: 9-ANM-116-                at the FAA, Transport Airplane Directorate,           of the airplane.
                                            AMOC-REQUESTS@faa.gov. Before using                      1601 Lind Avenue SW., Renton, WA. For
                                            any approved AMOC, notify your appropriate               information on the availability of this               DATES: This AD is effective January 28,
                                            principal inspector, or lacking a principal              material at the FAA, call 425–227–1221.               2016.
                                            inspector, the manager of the local flight                  (5) You may view this service information             The Director of the Federal Register
                                            standards district office/certificate holding            that is incorporated by reference at the              approved the incorporation by reference


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                                                             Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations                                        80243

                                            of a certain publication listed in this AD               20178). The NPRM was prompted by a                    positively identify them. UAL added
                                            as of January 28, 2016.                                  report that a machining defect was also               that actuators are not likely to be
                                              The Director of the Federal Register                   found on some of the actuator                         tracked in position, and could have
                                            approved the incorporation by reference                  assemblies inspected during                           been moved between airplanes as a
                                            of a certain other publication listed in                 manufacture. The NPRM proposed to                     result of maintenance. UAL also stated
                                            this AD as of November 29, 2013 (78 FR                   continue to require doing a detailed                  that, in general, it would be better if the
                                            68345, November 14, 2013).                               inspection of certain attach fittings for a           AD as a whole was worded not to
                                            ADDRESSES: For service information                       cylindrical defect and replacing if                   depend on a record of previous
                                            identified in this AD, contact Boeing                    necessary. This defect could lead to                  inspection accomplishment, but rather
                                            Commercial Airplanes, Attention: Data                    fatigue cracking and subsequent                       on parts identification.
                                            & Services Management, P.O. Box 3707,                    fracture. For certain airplanes, the                     We acknowledge the commenter’s
                                            MC 2H–65, Seattle, WA 98124–2207;                        NPRM proposed to mandate new                          concerns. We realize that paragraph (k)
                                            telephone 206–544–5000, extension 1;                     inspections of the inboard actuator                   of this AD is predicated on the fact that
                                            fax 206–766–5680; Internet https://                      attach fittings for machining defects,                operators kept records from the
                                            www.myboeingfleet.com. You may view                      and overhaul or replacement, if                       inspection specified in Boeing Alert
                                            this referenced service information at                   necessary. The NPRM also proposed to                  Service Bulletin 747–57A2443, dated
                                            the FAA, Transport Airplane                              limit the compliance time for doing the               September 12, 2013. The intent of this
                                            Directorate, 1601 Lind Avenue SW.,                       replacement for certain other airplanes.              AD is to either replace inboard actuator
                                            Renton, WA. For information on the                       We are issuing this AD to detect and                  attach fittings having part number (P/N)
                                            availability of this material at the FAA,                correct defective inboard actuator attach             65B08564–7, or to inspect P/N
                                            call 425–227–1221. It is also available                  fittings which, combined with loss of                 65B08564–7 for cylindrical defects,
                                            on the Internet at https://                              the outboard actuator load path, could                machining defects, and wall thickness,
                                            www.regulations.gov by searching for                     result in uncontrolled retraction of the              and accomplish applicable corrective
                                            and locating Docket No. FAA–2015–                        outboard flap, damage to flight control               actions. For that reason we have
                                            0828.                                                    systems, and consequent reduced                       changed the introductory text of
                                                                                                     controllability of the airplane.                      paragraph (k) of this AD so that it
                                            Examining the AD Docket                                                                                        applies to airplanes on which doing the
                                                                                                     Comments                                              detailed inspection required by
                                              You may examine the AD docket on
                                            the Internet at http://                                    We gave the public the opportunity to               paragraph (h)(1) of this AD was done
                                            www.regulations.govby searching for                      participate in developing this AD. The                before the effective date of this AD and
                                            and locating Docket No. FAA–2015–                        following presents the comments                       a cylindrical defect was found but a
                                            0828; or in person at the Docket                         received on the NPRM (80 FR 20178,                    replacement was not done. We have also
                                            Management Facility between 9 a.m.                       April 15, 2015) and the FAA’s response                revised paragraph (k)(1) of this AD to
                                            and 5 p.m., Monday through Friday,                       to each comment.                                      require an ultrasonic inspection to
                                            except Federal holidays. The AD docket                                                                         determine the minimum thickness or
                                                                                                     Request to Add Terminating Action                     mechanically determine the minimum
                                            contains this AD, the regulatory
                                                                                                       Boeing asked that we revise the                     thickness and to allow a records review
                                            evaluation, any comments received, and
                                                                                                     NPRM (80 FR 20178, April 15, 2015) to                 for the inspections. This change ensures
                                            other information. The address for the
                                                                                                     specify that no additional action is                  all inspections are done on airplanes
                                            Docket Office (phone: 800–647–5527) is
                                                                                                     required for a wall thickness of 0.140                with P/N 65B08564–7 that did not
                                            Docket Management Facility, U.S.
                                                                                                     inch or greater with no machining                     replace P/N 65B08564–7 after
                                            Department of Transportation, Docket
                                                                                                     defect present, as also provided in Table             complying with AD 2013–23–03,
                                            Operations, M–30, West Building
                                                                                                     1 of Boeing Alert Service Bulletin 747–               Amendment 39–17658 (78 FR 68345,
                                            Ground Floor, Room W12–140, 1200
                                                                                                     57A2443, Revision 1, dated June 23,                   November 14, 2013).
                                            New Jersey Avenue SE., Washington,                                                                                To address airplanes on which
                                                                                                     2014.
                                            DC 20590.                                                  We agree with the commenter that no                 inboard actuator attach fittings were
                                            FOR FURTHER INFORMATION CONTACT:                         additional action is required for a wall              replaced after complying with
                                            Nathan Weigand, Aerospace Engineer,                      thickness of 0.140 inch or greater with               paragraph (h)(1) of AD 2013–23–03,
                                            Airframe Branch, ANM–120S, FAA,                          no machining defect present. However,                 Amendment 39–17658 (78 FR 68345,
                                            Seattle Aircraft Certification Office,                   we do not agree with the request to                   November 14, 2013), we have added
                                            1601 Lind Avenue SW., Renton, WA                         revise the AD because if this condition               new paragraph (m) to this AD, which
                                            98057–3356; phone: 425–917–6428; fax:                    exists, no action is required by this AD.             specifies that for airplanes on which the
                                            425–917–6590; email:                                     Only actions that are required to address             detailed inspection required by
                                            nathan.p.weigand@faa.gov.                                the identified unsafe condition are                   paragraph (h)(1) of this AD is done
                                            SUPPLEMENTARY INFORMATION:                               specified in this AD. We have made no                 before the effective date of this AD and
                                                                                                     change to the AD in this regard.                      the inboard actuator attach fitting has
                                            Discussion
                                                                                                                                                           been replaced since that inspection, the
                                              We issued a notice of proposed                         Request to Revise Certain Requirements                inspection to determine the part number
                                            rulemaking (NPRM) to amend 14 CFR                           Paragraph (k) of the proposed AD (80               specified in paragraph (g) of this AD
                                            part 39 to supersede AD 2013–23–03,                      FR 20178, April 15, 2015) would have                  must be done within 90 days after the
                                            Amendment 39–17658 (78 FR 68345,                         affected certain inboard actuator attach              effective date of this AD, and the
                                            November 14, 2013). AD 2013–23–03                        fittings that were inspected using                    applicable actions specified in
                                            applied to certain The Boeing Company                    Boeing Alert Service Bulletin 747–                    paragraphs (h), (i), and (j) of this AD
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                                            Model 747–100, 747–100B, 747–100B                        57A2443, dated September 12, 2013.                    must be done within the applicable
                                            SUD, 747–200B, 747–200C, 747–200F,                       United Airlines (UAL) requested that we               times specified in paragraphs (h), (i),
                                            747–300, 747–400, 747–400D, 747–                         remove this inspection criterion. UAL                 and (j) of this AD. We have also added
                                            400F, and 747SR series airplanes. The                    noted that there was no requirement to                a records review as an option if records
                                            NPRM published in the Federal                            identify the actuators; therefore,                    are available that can conclusively
                                            Register on April 15, 2015 (80 FR                        operators would not be likely to                      determine the part number. We


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                                            80244            Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations

                                            redesignated subsequent paragraphs                       AD. We have also added a records                      proposed in the NPRM (80 FR 20178,
                                            accordingly.                                             review as an option if records are                    April 15, 2015).
                                                                                                     available that can conclusively                         We also determined that this change
                                            Request to Add Inspection
                                                                                                     determine if the actions have been done.              will not increase the economic burden
                                               UAL stated that the actions specified                                                                       on any operator or increase the scope of
                                            in paragraph (l) of the proposed AD (80                  Change to Paragraph (h)(2) of the
                                                                                                                                                           this AD.
                                            FR 20178, April 15, 2015) would also                     Proposed AD ((80 FR 20178, April 15,
                                            depend on the record of findings from                    2015)                                                 Related Service Information Under 1
                                            inspections made in accordance with                                                                            CFR Part 51
                                                                                                        We have revised paragraph (h)(2) of
                                            AD 2013–23–03, Amendment 39–17658                        this AD by referring to Boeing Alert                     We reviewed Boeing Alert Service
                                            (78 FR 68345, November 14, 2013). UAL                    Service Bulletin 747–57A2443, Revision                Bulletin 747–57A2443, dated September
                                            added that there was no AD requirement                   1, dated June 23, 2014, as an appropriate             12, 2013; and Boeing Alert Service
                                            to record these findings. UAL noted that                 source of service information for                     Bulletin 747–57A2443, Revision 1,
                                            operators conducted the inspections and                  accomplishing the required actions.                   dated June 23, 2014. The service
                                            took actions that were required. UAL                                                                           information describes procedures for
                                            stated that it would be better to call out               Conclusion                                            new inspections of the inboard actuator
                                            a new inspection in the AD to determine                                                                        attach fittings for machining defects,
                                                                                                       We reviewed the relevant data,
                                            which condition the actuator is in, and                                                                        and overhaul or replacement, if
                                                                                                     considered the comments received, and
                                            then take action as appropriate.                                                                               necessary. This service information is
                                                                                                     determined that air safety and the
                                               We acknowledge the commenter’s                                                                              reasonably available because the
                                                                                                     public interest require adopting this AD
                                            concerns. We have revised paragraph (l)                                                                        interested parties have access to it
                                                                                                     with the change described previously
                                            of this AD to specify that no actuator                                                                         through their normal course of business
                                                                                                     and minor editorial changes. We have
                                            attach fitting having P/N 65B08564–7                                                                           or by the means identified in the
                                                                                                     determined that these minor changes:
                                            may be installed on any airplane unless                                                                        ADDRESSES section.
                                            the inspection specified in paragraph                      • Are consistent with the intent that
                                            (h)(1) of this AD is done prior to                       was proposed in the NPRM (80 FR                       Costs of Compliance
                                            installation and the applicable actions                  20178, April 15, 2015) for correcting the               We estimate that this AD affects 184
                                            specified in paragraphs (i) and (j) of this              unsafe condition; and                                 airplanes of U.S. registry.
                                            AD are done within the applicable times                    • Do not add any additional burden                    We estimate the following costs to
                                            specified in paragraphs (i) and (j) of this              upon the public than was already                      comply with this AD:
                                                                                                                  ESTIMATED COSTS
                                                                                                                                                                             Cost per       Cost on U.S.
                                                                  Action                                               Labor cost                          Parts cost        product         operators

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



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



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                                                             Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations                                            80245

                                            § 39.13   [Amended]                                      June 23, 2014. As of the effective date of this       an ultrasonic inspection or by mechanically
                                            ■ 2. The FAA amends § 39.13 by                           AD, only Boeing Alert Service Bulletin 747–           measuring the thickness and do a detailed
                                            removing Airworthiness Directive (AD)                    57A2443, Revision 1, dated June 23, 2014,             inspection of the inner conical section to
                                                                                                     may be used.                                          determine if the machining defect is present,
                                            2013–23–03, Amendment 39–17658 (78                                                                             in accordance with Part 3 of the
                                            FR 68345, November 14, 2013), and                        (h) Retained Actions for Certain Attach
                                                                                                                                                           Accomplishment Instructions of Boeing Alert
                                            adding the following new AD:                             Fittings With Revised Service Information             Service Bulletin 747–57A2443, Revision 1,
                                            2015–25–03 The Boeing Company:                              This paragraph restates the requirements of        dated June 23, 2014.
                                                Amendment 39–18341; Docket No.                       paragraph (h) of AD 2013–23–03,                          (i) If the minimum thickness of the wall is
                                                FAA–2015–0828; Directorate Identifier                Amendment 39–17658 (78 FR 68345,                      less than 0.130 inch: Before further flight,
                                                2014–NM–146–AD.                                      November 14, 2013), with revised service              replace the inboard actuator attach fitting of
                                                                                                     information. If, during the inspection                the outboard flap, in accordance with Part 4
                                            (a) Effective Date
                                                                                                     required by paragraph (g) of this AD, any             of the Accomplishment Instructions of
                                              This AD is effective January 28, 2016.                 inboard actuator attach fitting having part           Boeing Alert Service Bulletin 747–57A2443,
                                            (b) Affected ADs                                         number (P/N) 65B08564–7 is found, before              Revision 1, dated June 23, 2014.
                                                                                                     further flight, do the actions specified in              (ii) If the minimum thickness of the wall
                                              This AD replaces AD 2013–23–03,                        paragraph (h)(1) or (h)(2) of this AD.                is 0.140 inch or greater and the machining
                                            Amendment 39–17658 (78 FR 68345,                            (1) Do a detailed inspection of the inboard        defect is present, before further flight, do the
                                            November 14, 2013).                                      actuator attach fitting for a cylindrical defect,     actions specified in paragraph (i)(1)(ii)(A) or
                                            (c) Applicability                                        in accordance with Part 2 of the                      (i)(1)(ii)(B) of this AD.
                                                                                                     Accomplishment Instructions of Boeing Alert              (A) Overhaul the inboard actuator attach
                                               This AD applies to The Boeing Company                 Service Bulletin 747–57A2443, dated
                                            Model 747–100, 747–100B, 747–100B SUD,                                                                         fitting of the outboard flap, in accordance
                                                                                                     September 12, 2013; or Boeing Alert Service           with Part 5 of the Accomplishment
                                            747–200B, 747–200C, 747–200F, 747–300,                   Bulletin 747–57A2443, Revision 1, dated
                                            747–400, 747–400D, 747–400F, and 747SR                                                                         Instructions of Boeing Alert Service Bulletin
                                                                                                     June 23, 2014. As of the effective date of this       747–57A2443, Revision 1, dated June 23,
                                            series airplanes, certificated in any category,          AD, only Boeing Alert Service Bulletin 747–
                                            as identified in Boeing Alert Service Bulletin                                                                 2014.
                                                                                                     57A2443, Revision 1, dated June 23, 2014,                (B) Replace the inboard actuator attach
                                            747–57A2443, Revision 1, dated June 23,                  may be used. For airplanes on which the
                                            2014.                                                                                                          fitting of the outboard flap, in accordance
                                                                                                     detailed inspection is done before the
                                                                                                                                                           with Part 4 of the Accomplishment
                                            (d) Subject                                              effective date of this AD: If any cylindrical
                                                                                                                                                           Instructions of Boeing Alert Service Bulletin
                                                                                                     defect is found, before further flight, do the
                                              Air Transport Association (ATA) of                                                                           747–57A2443, Revision 1, dated June 23,
                                                                                                     actions specified in paragraph (h)(1)(i) or
                                            America Code 57, Wings.                                                                                        2014.
                                                                                                     (h)(1)(ii) of this AD.
                                                                                                                                                              (iii) If the minimum thickness of the wall
                                            (e) Unsafe Condition                                        (i) Do a minimum thickness inspection of
                                                                                                                                                           is 0.130 inch or greater and less than 0.140
                                                                                                     the inboard actuator attach fitting to
                                               This AD was prompted by a report of the                                                                     inch and the machining defect is not present,
                                                                                                     determine minimum wall thickness of the
                                            fracture of an inboard actuator attach fitting           actuator fitting assembly, in accordance with         within 48 months or 3,000 flight cycles after
                                            of the outboard flap. An inspection of the               Part 3 of the Accomplishment Instructions of          the effective date of this AD, whichever
                                            attach fitting revealed that it was incorrectly          Boeing Alert Service Bulletin 747–57A2443,            occurs first, replace the inboard actuator
                                            machined with a cylindrical profile instead              dated September 12, 2013; or Boeing Alert             attach fitting of the outboard flap, in
                                            of a conical profile, resulting in reduced wall          Service Bulletin 747–57A2443, Revision 1,             accordance with Part 4 of the
                                            thickness. A machining defect was also                   dated June 23, 2014. If the minimum                   Accomplishment Instructions of Boeing Alert
                                            found on some actuator assemblies inspected              thickness of the wall is less than 0.130 inch:        Service Bulletin 747–57A2443, Revision 1,
                                            during manufacture at the point where the                Before further flight, replace the inboard            dated June 23, 2014.
                                            tapered machining transitioned to the                    actuator attach fitting of the outboard flap, in         (iv) If the minimum thickness of the wall
                                            hemispherical machining at the top of the                accordance with Part 4 of the                         is 0.130 inch or greater and less than 0.140
                                            inner surface. This defect could lead to                 Accomplishment Instructions of Boeing Alert           inch and the machining defect is present,
                                            fatigue cracking and subsequent fracture. We             Service Bulletin 747–57A2443, dated                   before further flight, replace the inboard
                                            are issuing this AD to detect and correct                September 12, 2013.                                   actuator attach fitting of the outboard flap, in
                                            defective inboard actuator attach fittings                  (ii) Replace the inboard actuator attach           accordance with Part 4 of the
                                            which, combined with loss of the outboard                fitting of the outboard flap, in accordance           Accomplishment Instructions of Boeing Alert
                                            actuator load path, could result in                      with Part 4 of the Accomplishment                     Service Bulletin 747–57A2443, Revision 1,
                                            uncontrolled retraction of the outboard flap,            Instructions of Boeing Alert Service Bulletin         dated June 23, 2014.
                                            damage to flight control systems, and                    747–57A2443, dated September 12, 2013.                   (2) Replace the inboard actuator attach
                                            consequent reduced controllability of the                   (2) Replace the inboard actuator attach            fitting of the outboard flap, in accordance
                                            airplane.                                                fitting of the outboard flap, in accordance           with Part 4 of the Accomplishment
                                                                                                     with Part 4 of the Accomplishment                     Instructions of Boeing Alert Service Bulletin
                                            (f) Compliance                                                                                                 747–57A2443, Revision 1, dated June 23,
                                                                                                     Instructions of Boeing Alert Service Bulletin
                                               Comply with this AD within the                        747–57A2443, dated September 12, 2013; or             2014.
                                            compliance times specified, unless already               Boeing Alert Service Bulletin 747–57A2443,            (j) New Actions for Airplanes on Which No
                                            done.                                                    Revision 1, dated June 23, 2014. As of the            Cylindrical Defects Are Found
                                            (g) Retained Part Number Inspection With                 effective date of this AD, only Boeing Alert
                                                                                                     Service Bulletin 747–57A2443, Revision 1,                If no cylindrical defect is found during any
                                            Revised Service Information                                                                                    inspection required by paragraph (h)(1) of
                                                                                                     dated June 23, 2014, may be used.
                                               This paragraph restates the requirements of                                                                 this AD, within 24 months after the effective
                                            paragraph (g) of AD 2013–23–03,                          (i) New Actions for Certain Airplanes on              date of this AD, do the actions specified in
                                            Amendment 39–17658 (78 FR 68345,                         Which Any Cylindrical Defect Is Found                 paragraph (j)(1) or (j)(2) of this AD.
                                            November 14, 2013), with revised service                    For airplanes on which the detailed                   (1) Determine the minimum wall thickness
                                            information. Within 90 days after November               inspection required by paragraph (h)(1) of            of the actuator attach fitting either by doing
                                            29, 2013 (the effective date of AD 2013–23–              this AD is done on or after the effective date        an ultrasonic inspection or by mechanically
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                                            03): Inspect to determine the part number of             of this AD: If any cylindrical defect is found        measuring the thickness and do a detailed
                                            the inboard actuator attach fittings of the              during any inspection required by paragraph           inspection of the inner conical section to
                                            outboard flaps, in accordance with Part 1 of             (h)(1) of this AD, before further flight, do the      determine if the machining defect is present,
                                            the Accomplishment Instructions of Boeing                actions specified in paragraph (i)(1) or (i)(2)       in accordance with Part 3 of the
                                            Alert Service Bulletin 747–57A2443, dated                of this AD.                                           Accomplishment Instructions of Boeing Alert
                                            September 12, 2013; or Boeing Alert Service                 (1) Determine the minimum wall thickness           Service Bulletin 747–57A2443, Revision 1,
                                            Bulletin 747–57A2443, Revision 1, dated                  of the actuator attach fitting either by doing        dated June 23, 2014.



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                                            80246            Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations

                                               (i) If the minimum thickness of the wall is           dated June 23, 2014. A review of airplane             (m) Action for Parts Installed After AD
                                            less than 0.130 inch: Before further flight,             maintenance records, if available, is                 2013–23–03, Amendment 39–17658 (78 FR
                                            replace the inboard actuator attach fitting of           acceptable to determine the wall thickness            68345, November 14, 2013) Was
                                            the outboard flap, in accordance with Part 4             and to determine if there are machining               Accomplished
                                            of the Accomplishment Instructions of                    defects, provided wall thickness and                     For airplanes on which the detailed
                                            Boeing Alert Service Bulletin 747 57A2443,               machining defects can be positively                   inspection required by paragraph (h)(1) of
                                            Revision 1, dated June 23, 2014.                         determined from the records review.                   this AD is done before the effective date of
                                               (ii) If the minimum thickness of the wall                (i) If any machining defect is found and the       this AD and the inboard actuator attach
                                            is 0.140 inch or greater and the machining               minimum thickness of the wall is 0.140 inch           fitting was replaced since that inspection:
                                            defect is present, before further flight, do the         or greater: Before further flight, do the actions     Within 90 days after the effective date of this
                                            actions specified in paragraph (j)(1)(ii)(A) or                                                                AD, inspect to determine the part number of
                                                                                                     specified in paragraph (k)(1)(i)(A) or
                                            (j)(1)(ii)(B) of this AD.                                                                                      the inboard actuator attach fittings of the
                                                                                                     (k)(1)(i)(B) of this AD.
                                               (A) Overhaul the inboard actuator attach                                                                    outboard flaps and, for inboard actuator
                                                                                                        (A) Overhaul the inboard actuator attach
                                            fitting of the outboard flap, in accordance                                                                    attach fittings having P/N 65B08564–7, do
                                                                                                     fitting of the outboard flap, in accordance
                                            with Part 5 of the Accomplishment                                                                              the applicable actions specified in
                                            Instructions of Boeing Alert Service Bulletin            with Part 5 of the Accomplishment
                                                                                                     Instructions of Boeing Alert Service Bulletin         paragraphs (h), (i), and (j) of this AD within
                                            747–57A2443, Revision 1, dated June 23,                                                                        the applicable times specified in paragraphs
                                            2014.                                                    747–57A2443, Revision 1, dated June 23,
                                                                                                     2014.                                                 (h), (i), and (j) of this AD. A review of
                                               (B) Replace the inboard actuator attach                                                                     airplane maintenance records, if available, is
                                            fitting of the outboard flap, in accordance                 (B) Replace the inboard actuator attach
                                                                                                                                                           acceptable to determine the part number,
                                            with Part 4 of the Accomplishment                        fitting of the outboard flap, in accordance
                                                                                                                                                           provided the part number can be positively
                                            Instructions of Boeing Alert Service Bulletin            with Part 4 of the Accomplishment
                                                                                                                                                           determined from the records review.
                                            747–57A2443, Revision 1, dated June 23,                  Instructions of Boeing Alert Service Bulletin
                                            2014.                                                    747–57A2443, Revision 1, dated June 23,               (n) Alternative Methods of Compliance
                                               (iii) If the minimum thickness of the wall            2014.                                                 (AMOCs)
                                            is 0.130 inch or greater and less than 0.140                (ii) If any machining defect is found and             (1) The Manager, Seattle Aircraft
                                            inch and the machining defect is not present,            the minimum thickness of the wall is 0.130            Certification Office (ACO), FAA, has the
                                            within 48 months or 3,000 flight cycles after            inch or greater and less than 0.140 inch:             authority to approve AMOCs for this AD, if
                                            the effective date of this AD, whichever                 Before further flight, replace the inboard            requested using the procedures found in 14
                                            occurs first, replace the inboard actuator               actuator attach fitting of the outboard flap, in      CFR 39.19. In accordance with 14 CFR 39.19,
                                            attach fitting of the outboard flap, in                  accordance with Part 4 of the                         send your request to your principal inspector
                                            accordance with Part 4 of the                            Accomplishment Instructions of Boeing Alert           or local Flight Standards District Office, as
                                            Accomplishment Instructions of Boeing Alert              Service Bulletin 747–57A2443, Revision 1,             appropriate. If sending information directly
                                            Service Bulletin 747–57A2443, Revision 1,                dated June 23, 2014.                                  to the manager of the ACO, send it to the
                                            dated June 23, 2014.                                        (iii) If no machining defect is found and          attention of the person identified in
                                               (iv) If the minimum thickness of the wall             the minimum thickness of the wall is 0.130            paragraph (o) of this AD. Information may be
                                            is 0.130 inch or greater and less than 0.140             inch or greater and less than 0.140 inch:             emailed to: 9-ANM-Seattle-ACO-AMOC-
                                            inch and the machining defect is present,                Within 48 months or 3,000 flight cycles after         Requests@faa.gov.
                                            before further flight, replace the inboard               the effective date of this AD, whichever                 (2) Before using any approved AMOC,
                                            actuator attach fitting of the outboard flap, in         occurs first, replace the inboard actuator            notify your appropriate principal inspector,
                                            accordance with Part 4 of the                            attach fitting of the outboard flap, in               or lacking a principal inspector, the manager
                                            Accomplishment Instructions of Boeing Alert              accordance with Part 4 of the                         of the local flight standards district office/
                                            Service Bulletin 747–57A2443, Revision 1,                Accomplishment Instructions of Boeing Alert           certificate holding district office.
                                            dated June 23, 2014                                      Service Bulletin 747–57A2443, Revision 1,                (3) An AMOC that provides an acceptable
                                               (2) Replace the inboard actuator attach               dated June 23, 2014.                                  level of safety may be used for any repair
                                            fitting of the outboard flap, in accordance                 (iv) If a machining defect is or is not found      required by this AD if it is approved by the
                                            with Part 4 of the Accomplishment                        and the minimum thickness of the wall is              Boeing Commercial Airplanes Organization
                                            Instructions of Boeing Alert Service Bulletin            less than 0.130 inch: Before further flight,          Designation Authorization (ODA) that has
                                            747–57A2443, Revision 1, dated June 23,                                                                        been authorized by the Manager, Seattle
                                                                                                     replace the inboard actuator attach fitting of
                                            2014.                                                                                                          ACO, to make those findings. For a repair
                                                                                                     the outboard flap, in accordance with Part 4
                                                                                                                                                           method to be approved, the repair must meet
                                            (k) New Inspection or Replacement for                    of the Accomplishment Instructions of
                                                                                                                                                           the certification basis of the airplane, and the
                                            Certain Fittings That Were Previously                    Boeing Alert Service Bulletin 747–57A2443,
                                                                                                                                                           approval must specifically refer to this AD.
                                            Inspected                                                Revision 1, dated June 23, 2014.
                                                                                                                                                              (4) If any service information contains
                                               For airplanes on which the detailed                      (2) Replace the inboard actuator attach            steps that are identified as RC (Required for
                                            inspection required by paragraph (h)(1) of               fitting of the outboard flap, in accordance           Compliance), those steps must be done to
                                            this AD is done before the effective date of             with Part 4 of the Accomplishment                     comply with this AD; any steps that are not
                                            this AD, except as required by paragraph (m)             Instructions of Boeing Alert Service Bulletin         identified as RC are recommended. Those
                                            of this AD: If any cylindrical defect is found           747–57A2443, Revision 1, dated June 23,               steps that are not identified as RC may be
                                            during any inspection required by paragraph              2014.                                                 deviated from using accepted methods in
                                            (h)(1) of this AD and the replacement of the             (l) Parts Installation Limitation                     accordance with the operator’s maintenance
                                            inboard actuator attach fitting of the outboard                                                                or inspection program without obtaining
                                            flap was not done as specified in Part 4 of                As of the effective date of this AD, no             approval of an AMOC provided the steps
                                            the Accomplishment Instructions of Boeing                actuator attach fitting having P/N 65B08564–          identified as RC can be done and the airplane
                                            Alert Service Bulletin 747–57A2443, within               7 may be installed on any airplane unless the         can be put back in an airworthy condition.
                                            24 months after the effective date of this AD,           inspection specified in paragraph (h)(1) of           Any substitutions or changes to steps
                                            do the actions specified in paragraph (k)(1)             this AD is done prior to installation and the         identified as RC require approval of an
                                            or (k)(2) of this AD.                                    applicable actions specified in paragraphs (i)        AMOC.
                                               (1) Do a detailed inspection of the inner             and (j) of this AD are done within the                   (5) AMOCs approved for AD 2013–23–03,
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                                            conical section for machining defects and do             applicable times specified in paragraphs (i)          Amendment 39–17658 (78 FR 68345,
                                            an ultrasonic inspection to determine the                and (j) of this AD. A review of airplane              November 14, 2013) are approved as AMOCs
                                            minimum thickness or mechanically                        maintenance records, if available, is                 for the corresponding provisions of this AD.
                                            determine the minimum thickness, in                      acceptable to determine if the inspection and
                                            accordance with Part 3 of the                            applicable actions have been done, provided           (o) Related Information
                                            Accomplishment Instructions of Boeing Alert              the inspection and actions can be positively            For more information about this AD,
                                            Service Bulletin 747–57A2443, Revision 1,                determined from the records review.                   contact Nathan Weigand, Aerospace



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                                                             Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations                                                 80247

                                            Engineer, Airframe Branch, ANM–120S,                     maintained under this regulation must                 association, partnership, corporation, or
                                            FAA, Seattle Aircraft Certification Office,              be maintained in a form and manner                    trust—(i) owning or holding
                                            1601 Lind Avenue SW., Renton, WA 98057–                  which permits prompt, accurate and                    membership in, or admitted to
                                            3356; phone: 425–917–6428; fax: 425–917–                 reliable location, access, and retrieval of
                                            6590; email: nathan.p.weigand@faa.gov.                                                                         membership representation on, the
                                                                                                     any particular record, data, or                       registered entity 3 or derivatives
                                            (p) Material Incorporated by Reference                   information; clarify that all records,                transaction execution facility; or (ii)
                                               (1) The Director of the Federal Register              except records of oral and written                    having trading privileges on the
                                            approved the incorporation by reference                  communications leading to the                         registered entity or derivatives
                                            (IBR) of the service information listed in this          execution of a commodity interest                     transaction execution facility.4
                                            paragraph under 5 U.S.C. 552(a) and 1 CFR                transaction and related cash or forward
                                            part 51.                                                 transactions, must be kept in a form and                 Regulation 1.35(a) requires FCMs,
                                               (2) You must use this service information             manner that allows for identification of              RFEDs, IBs, and members of a DCM or
                                            as applicable to do the actions required by                                                                    of a SEF to keep records of written
                                                                                                     a particular transaction; exclude
                                            this AD, unless the AD specifies otherwise.                                                                    communications that lead to the
                                               (3) The following service information was
                                                                                                     members of designated contract markets
                                                                                                     (‘‘DCMs’’) and of swap execution                      execution of a commodity interest
                                            approved for IBR on January 28, 2016.
                                               (i) Boeing Alert Service Bulletin 747–                facilities (‘‘SEFs’’) that are not registered         transaction and related cash or forward
                                            57A2443, Revision 1, dated June 23, 2014.                or required to register with the                      transactions. Additionally, Regulation
                                               (ii) Reserved.                                        Commission (‘‘Unregistered Members’’)                 1.35(a) includes a requirement to keep
                                               (4) The following service information was             from the requirements to keep written                 records of certain oral communications,
                                            approved for IBR on November 29, 2013 (78                communications that lead to the                       which applies to each FCM, RFED, large
                                            FR 68345, November 14, 2013).                            execution of a commodity interest                     IB (defined as an IB that has generated
                                               (i) Boeing Alert Service Bulletin 747–                transaction and related cash or forward               over $5 million in aggregate gross
                                            57A2443, dated September 12, 2013.
                                                                                                     transactions, keep text messages, and                 revenues over the preceding three years
                                               (ii) Reserved.
                                               (5) For service information identified in
                                                                                                     keep records in a particular form and                 from its activities as an IB), and member
                                            this AD, contact Boeing Commercial                       manner; and exclude commodity                         of a DCM or of a SEF that is registered
                                            Airplanes, Attention: Data & Services                    trading advisors (‘‘CTAs’’) from the oral             or required to register with the
                                            Management, P. O. Box 3707, MC 2H–65,                    recordkeeping requirement (‘‘Final                    Commission as a floor broker (‘‘FB’’)
                                            Seattle, WA 98124–2207; telephone 206–                   Rule’’).                                              (only with regard to acting as an agent
                                            544–5000, extension 1; fax 206–766–5680;                 DATES: Effective December 24, 2015.                   for a non-affiliated client) or as a CTA.5
                                            Internet https://www.myboeingfleet.com.
                                               (6) You may view this service information             FOR FURTHER INFORMATION CONTACT:                      Unlike the written recordkeeping
                                            at the FAA, Transport Airplane Directorate,              Katherine Driscoll, Associate Chief                   requirement that applies to both
                                            1601 Lind Avenue SW., Renton, WA. For                    Counsel, (202) 418–5544, kdriscoll@                   commodity interest transactions and
                                            information on the availability of this                  cftc.gov; August A. Imholtz III, Special              related cash or forward transactions, the
                                            material at the FAA, call 425–227–1221.                  Counsel, (202) 418–5140, aimholtz@                    oral recordkeeping requirement is
                                               (7) You may view this service information             cftc.gov; or Lauren Bennett, Special                  limited to commodity interest
                                            that is incorporated by reference at the                 Counsel, (202) 418–5290, lbennett@                    transactions.6 The scope of records
                                            National Archives and Records                            cftc.gov, Division of Swap Dealer and
                                            Administration (NARA). For information on                                                                      covered by Regulation 1.35(a) includes
                                                                                                     Intermediary Oversight, Commodity                     communications by telephone,
                                            the availability of this material at NARA, call
                                            202–741–6030, or go to http://                           Futures Trading Commission, 1155 21st                 voicemail, facsimile, instant messaging,
                                            www.archives.gov/federal-register/cfr/ibr-               Street NW., Washington, DC 20581.                     chat rooms, electronic mail, mobile
                                            locations.html.                                          SUPPLEMENTARY INFORMATION:                            device, or other digital or electronic
                                              Issued in Renton, Washington, on                       I. Background                                         media.7 These communications include
                                            November 24, 2015.                                                                                             text messages. Regulation 1.35(a) also
                                                                                                        The Commission amended Regulation                  mandates that all records be kept in a
                                            Jeffrey E. Duven,
                                                                                                     1.35(a) in December 2012 as part of a                 form and manner identifiable and
                                            Manager, Transport Airplane                              series of rulemakings intended to
                                            Directorate,Aircraft Certification Service.                                                                    searchable by transaction.
                                                                                                     integrate certain existing Commission
                                            [FR Doc. 2015–30881 Filed 12–23–15; 8:45 am]             rules more fully with the framework                      3 The term ‘‘registered entity’’ is defined in CEA
                                            BILLING CODE 4910–13–P                                   created by the Dodd-Frank Wall Street                 section 1a(40) to include both DCMs and SEFs. See
                                                                                                     Reform and Consumer Protection Act                    CEA sections 1a(40)(A) (DCMs) and (D) (SEFs).
                                                                                                     for swap dealers and major swap                          4 7 U.S.C. 1a(34).

                                            COMMODITY FUTURES TRADING                                participants (the ‘‘2012 Amendment’’).1                  5 As stated in the 2012 Amendment, the oral

                                            COMMISSION                                                  Regulation 1.35(a) requires each                   recordkeeping requirement in Regulation 1.35(a)
                                                                                                                                                           does not apply to: (i) Oral communications that lead
                                                                                                     futures commission merchant (‘‘FCM’’),                solely to the execution of a related cash or forward
                                            17 CFR Part 1                                            retail foreign exchange dealer (‘‘RFED’’),            transaction; (ii) oral communications provided or
                                            RIN 3038–AE23                                            introducing broker (‘‘IB’’), and member               received by a floor broker that do not lead to the
                                                                                                     of a DCM or of a SEF to keep full,                    purchase or sale for any person other than the floor
                                            Records of Commodity Interest and                                                                              broker of any commodity for future delivery,
                                                                                                     complete, and systematic records of all               security futures product, swap, or commodity
                                            Related Cash or Forward Transactions                     transactions relating to its business of              option authorized under section 4c of the
                                                                                                     dealing in commodity interest and                     Commodity Exchange Act; (iii) an introducing
                                            AGENCY:  Commodity Futures Trading                                                                             broker that has generated over the preceding three
                                                                                                     related cash or forward transactions.2
                                            Commission.                                                                                                    years $5 million or less in aggregate gross revenues
                                                                                                     The Commodity Exchange Act (‘‘CEA’’)                  from its activities as an introducing broker; (iv) a
                                            ACTION: Final rule.
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                                                                                                     defines ‘‘member’’ as an individual,                  floor trader; (v) a commodity pool operator; (vi) a
                                            SUMMARY:  The Commodity Futures                                                                                swap dealer; (vii) a major swap participant; or (viii)
                                                                                                       1 See Adaptation of Regulations to Incorporate      a member of a DCM or SEF that is not registered
                                            Trading Commission (the                                                                                        or required to be registered with the Commission
                                                                                                     Swaps—Records of Transactions, 77 FR 75523
                                            ‘‘Commission’’ or ‘‘CFTC’’) is amending                  (December 21, 2012) (‘‘2012 Amendment Adopting        in any capacity. 17 CFR 1.35(a)(1).
                                            Commission Regulation 1.35(a) to:                        Release’’).                                              6 17 CFR 1.35(a)(1).

                                            Provide that all records required to be                    2 17 CFR 1.35(a)(1).                                   7 Id.




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Document Created: 2015-12-24 02:25:04
Document Modified: 2015-12-24 02:25:04
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.
DatesThis AD is effective January 28, 2016.
ContactNathan 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 Citation80 FR 80242 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

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