18456 Federal Register / Vol. 81, No. 62 / Thursday, March 31, 2016 / Rules and Regulations 

participants for the 12-month period 

February 1, 2014 to January 31, 2015; 

(5) For FY 2017, 60 percent based on 

a State’s FY 2009 SNAP-Ed 

expenditures, and 40 percent based on 

the State’s share of national SNAP 

participants for the 12-month period 

February 1, 2015 to January 31, 2016; 

and, 

(6) For FY 2018 and subsequent years, 

50 percent based on a State’s FY 2009 

SNAP-Ed expenditures, and 50 percent 

based on the State’s share of national 

SNAP participants for the previous 12- 

month period ending January 31; 

(F) If a participating State agency 

notifies FNS as required in (ix) above 

that it will not obligate or expend all of 

the funds allocated to it for a fiscal year 

under this section, FNS may reallocate 

the unobligated or unexpended funds to 

other participating State agencies that 

have approved SNAP-Ed Plans during 

the period for which the funding is 

available for new obligations by FNS. 

Reallocated funds received by a State 

will be considered part of its base FY 

2009 allocation for the purpose of 

determining the State’s allocation for 

the next fiscal year; funds surrendered 

by a State shall not be considered part 

of its base FY 2009 allocation for the 

next fiscal year for the purpose of 

determining the State’s allocation for 

the next fiscal year. 

(xi) Fiscal recordkeeping and 

reporting requirements. Each 

participating State agency must meet 

FNS fiscal recordkeeping and reporting 

requirements. Total SNAP-Ed 

expenditures and State, private, and 

other contributions to SNAP-Ed 

activities are reported through the 

financial reporting means and in the 

timeframe designated by FNS; 

(xii) Additional information may be 

required of the State agency, on an as 

needed basis, regarding the type of 

nutrition education and obesity 

prevention activities offered and the 

characteristics of the target population 

served, depending on the contents of the 

State’s SNAP-Ed Plan, to determine 

whether nutrition education goals are 

being met; 

(xiii) The State agency must submit a 

SNAP-Ed Annual Report to FNS by 

January 31 of each year. The report shall 

describe SNAP-Ed Plan project 

activities, outcomes, and budget for the 

prior year. 

(e) * * * 

(6) The SNAP-Ed Plan shall be signed 

by the head of the State agency and 

submitted prior to funding of nutrition 

education and obesity prevention 

activities when the State agency elects 

to request Federal grant funds to 

conduct these SNAP-Ed activities. The 

Plan shall be submitted for approval no 

later than August 15. Approved plans 

become effective the following FFY 

October 1 to September 30. 

* * * * * 

Dated: March 24, 2016. 

Audrey Rowe, 

Administrator, Food and Nutrition Service. 

[FR Doc. 2016–07179 Filed 3–30–16; 8:45 am] 

BILLING CODE 3410–30–P 

DEPARTMENT OF AGRICULTURE 

Rural Housing Service 

7 CFR Part 3555 

RIN 0575–AD00 

Single Family Housing Guaranteed 

Loan Program 

Correction 

Rule document 2016–07049, 

beginning on page 17361 in the issue of 

Tuesday, March 29, 2016, was 

inadvertently published and is 

withdrawn from that issue. 

[FR Doc. C1–2016–07049 Filed 3–29–16; 4:15 pm] 

BILLING CODE 1505–01–D 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3983; Directorate 

Identifier 2015–NM–141–AD; Amendment 

39–18448; AD 2016–07–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–300, 747SR, and 747SP series 

airplanes. This AD was prompted by an 

evaluation by the design approval 

holder (DAH) indicating that the upper 

chords of the upper deck floor beams 

are subject to widespread fatigue 

damage (WFD). This AD requires 

repetitive inspections for cracks at the 

floor panel attachment fastener holes; 

repetitive inspections for cracks in the 

upper and lower chords of the upper 

deck floor beams at permanent fastener 

locations; repetitive inspections for 

cracks in certain repaired and modified 

areas; and related investigative and 

corrective actions if necessary. This AD 

also requires repetitive replacement of 

the upper chords of the upper deck floor 

beams, including pre-replacement 

inspections and corrective action if 

necessary; and post-replacement 

repetitive inspections and repair if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking of the 

upper chords of the upper deck floor 

beams. Undetected cracking could result 

in large deflection or deformation of the 

upper deck floor beams, resulting in 

damage to wire bundles and control 

cables for the flight control system, and 

reduced controllability of the airplane. 

Multiple adjacent severed floor beams 

could result in rapid decompression of 

the airplane. 

DATES: This AD is effective May 5, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 5, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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 http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3983. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3983; 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 


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98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–300, 747SR, and 

747SP series airplanes. The NPRM 

published in the Federal Register on 

October 6, 2015 (80 FR 60303) (‘‘the 

NPRM’’). The NPRM was prompted by 

an evaluation by the DAH indicating 

that the upper chords of the upper deck 

floor beams are subject to WFD. The 

NPRM proposed to require repetitive 

inspections for cracks at the floor panel 

attachment fastener holes; repetitive 

inspections for cracks in the upper and 

lower chords of the upper deck floor 

beams at permanent fastener locations; 

repetitive inspections for cracks in 

certain repaired and modified areas; and 

related investigative and corrective 

actions if necessary. The NPRM also 

proposed to require repetitive 

replacement of the upper chords of the 

upper deck floor beams, including prereplacement inspections and corrective 

action if necessary; and postreplacement repetitive inspections and 

repair if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking of the upper chords of the 

upper deck floor beams. Undetected 

cracking could result in large deflection 

or deformation of the upper deck floor 

beams, resulting in damage to wire 

bundles and control cables for the flight 

control system, and reduced 

controllability of the airplane. Multiple 

adjacent severed floor beams could 

result in rapid decompression 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 and the FAA’s 

response to each comment. A member of 

the public supported the NPRM and an 

anonymous commenter had no 

objection to the NPRM. 

Request To Clarify Credit for Previous 

Actions 

Boeing requested that we clarify that 

credit for previous actions is limited to 

those actions that comply with the new 

proposed requirements of the NPRM. 

Boeing noted that paragraph (m) of the 

proposed AD should provide credit for 

using Boeing Alert Service Bulletin 

747–53A2452, dated April 3, 2003, 

provided the new requirements 

specified in Boeing Alert Service 

Bulletin 747–53A2452, Revision 1, 

dated July 16, 2012, are met. 

We agree that clarification is 

necessary. Paragraph (m) of this AD, 

‘‘Credit for Previous Actions,’’ provides 

credit for actions done before the 

effective date of this AD using Boeing 

Alert Service Bulletin 747–53A2452, 

dated April 3, 2003, for the 

corresponding actions required by 

paragraphs (g), (h), and (i) of this AD. 

Paragraphs (g), (h), and (i) of this AD 

refer to Boeing Alert Service Bulletin 

747–53A2452, Revision 1, dated July 16, 

2012, as the appropriate source of 

service information for accomplishing 

the actions required by those 

paragraphs. Boeing Alert Service 

Bulletin 747–53A2452, Revision 1, 

dated July 16, 2012, added certain 

inspection locations. Therefore, for the 

added inspection locations specified in 

Boeing Alert Service Bulletin 747– 

53A2452, Revision 1, dated July 16, 

2012, paragraph (m) of this AD does not 

provide credit because Boeing Alert 

Service Bulletin 747–53A2452, dated 

April 3, 2003, cannot be used for those 

locations. We have revised paragraph 

(m) of this AD to clarify that although 

credit is given for using Boeing Alert 

Service Bulletin 747–53A2452, dated 

April 3, 2003, actions required by 

paragraphs (g), (h), and (i) of this AD 

that are not identified in Boeing Alert 

Service Bulletin 747–53A2452, dated 

April 3, 2003, must still be done. 

Boeing also stated that credit should 

be given in the NPRM for Boeing Alert 

Service Bulletin 747–53A2452, Revision 

1, dated July 16, 2012; and Boeing Alert 

Service Bulletin 747–53A2852, dated 

June 22, 2012. 

We have not included Boeing Alert 

Service Bulletin 747–53A2452, Revision 

1, dated July 16, 2012; and Boeing Alert 

Service Bulletin 747–53A2852, dated 

June 22, 2012; in paragraph (m) of this 

AD because that service information is 

already cited in paragraphs (g) through 

(k) of this AD as the only appropriate 

source of service information for 

accomplishing the actions required by 

this AD. As allowed by the phrase, 

‘‘unless already done,’’ in paragraph (f) 

of this AD, if the requirements of this 

AD have already been accomplished, 

this AD does not require that those 

actions be repeated. 

Request To Give Credit for Previous 

Alternative Methods of Compliance 

(AMOCs) 

Boeing requested that previously 

approved AMOCs for AD 2005–20–29, 

Amendment 39–14326 (70 FR 59246, 

October 12, 2005), be approved for the 

corresponding provisions of the 

proposed AD, provided the previously 

approved AMOCs satisfy the inspection 

locations and compliance times 

specified by the proposed AD. Boeing 

noted that AMOCs would be needed for 

new inspection locations and 

compliance times specified in the 

proposed AD. 

We acknowledge that certain AMOCs 

for AD 2005–20–29, Amendment 39– 

14326 (70 FR 59246, October 12, 2005), 

might also address the actions and 

compliance times required by this AD. 

However, each individual AMOC would 

need to be evaluated to ensure the 

identified unsafe condition is 

addressed. Any person may request 

approval of an AMOC under the 

provisions of paragraph (o) of this AD. 

We have not changed this final rule in 

this regard. 

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 changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes 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 the following service 

information. 

• Boeing Alert Service Bulletin 747– 

53A2452, Revision 1, dated July 16, 

2012. This service information describes 

procedures for repetitive open hole or 

surface high frequency eddy current 

(HFEC) inspections, as applicable, for 

cracks at the floor panel attachment 

fastener holes in certain areas and 

stations; repetitive surface HFEC 

inspections for cracks in the upper and 

lower chords of the upper deck floor 

beams at permanent fastener locations 

in certain areas and stations; and related 

investigative and corrective actions. 

This service information also describes 

procedures, for airplanes on which 

certain repairs or modifications are 

done, for repetitive open hole or surface 

HFEC inspections, as applicable, for 

cracks in the repaired and modified 

areas; and repair. 

• Boeing Alert Service Bulletin 747– 

53A2852, dated June 22, 2012. This 


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service information describes 

procedures for repetitive replacement of 

the upper chords of the upper deck floor 

beams, including pre-replacement 

inspections and corrective action, and 

post-replacement repetitive inspections 

and repair. 

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 67 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

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

Inspections specified in Boeing Alert 

Service Bulletin 747-53A2452, Revision 1, dated July 16, 2012.

Up to 884 work-hours × 

$85 per hour = $75,140, 

per inspection cycle.

$0 $75,140, per inspection 

cycle.

$5,034,380, per inspection 

cycle. 

Replacement specified in Boeing Alert 

Service Bulletin 747-53A2852, dated 

June 22, 2012.

Up to 696 work-hours × 

$85 per hour = $59,160, 

per replacement.

1 $0 $59,160, per replacement $3,963,720, per replacement. 

Post-replacement inspections specified 

in Boeing Alert Service Bulletin 

747-53A2852, dated June 22, 2012.

Up to 586 work-hours × 

$85 per hour = $49,810, 

per inspection cycle.

$0 $49,810, per inspection 

cycle.

$3,337,270, per inspection 

cycle. 

1We currently have no specific cost estimates associated with the parts necessary for the replacement. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2016–07–03 The Boeing Company: 

Amendment 39–18448 ; Docket No. 

FAA–2015–3983; Directorate Identifier 

2015–NM–141–AD. 

(a) Effective Date 

This AD is effective May 5, 2016. 

(b) Affected ADs 

This AD affects AD 2005–20–29, 

Amendment 39–14326 (70 FR 59246, October 

12, 2005). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–300, 747SR, and 747SP series 

airplanes; certificated in any category; as 

identified in Boeing Alert Service Bulletin 

747–53A2852, dated June 22, 2012. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the upper chords of the upper deck floor 

beams are subject to widespread fatigue 

damage (WFD). We are issuing this AD to 

detect and correct fatigue cracking of the 

upper chords of the upper deck floor beams. 

Undetected cracking could result in large 

deflection or deformation of the upper deck 

floor beams, resulting in damage to wire 

bundles and control cables for the flight 

control system, and reduced controllability of 

the airplane. Multiple adjacent severed floor 

beams could result in rapid decompression of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections of the Upper 

Chords of the Upper Deck Floor Beams 

At the applicable times specified in Tables 

1 through 7 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 747– 

53A2452, Revision 1, dated July 16, 2012, 

except as required by paragraph (l)(1) of this 

AD: Do the inspections specified in 

paragraphs (g)(1) and (g)(2) of this AD, and 

do all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2452, Revision 1, 

dated July 16, 2012, except as required by 

paragraph (l)(2) of this AD. Repeat the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD thereafter at the applicable 


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times specified in Tables 1 through 7 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2452, 

Revision 1, dated July 16, 2012. Do all 

applicable related investigative and 

corrective actions before further flight. Doing 

the inspections required by paragraphs (g)(1) 

and (g)(2) of this AD terminates the 

inspections required by paragraphs (m) and 

(n) of AD 2005–20–29, Amendment 39– 

14326 (70 FR 59246, October 12, 2005). 

(1) Do an open hole or surface high 

frequency eddy current (HFEC) inspection, as 

applicable, for cracks at the fastener holes of 

the floor panel attachment in the applicable 

areas and stations identified in Boeing Alert 

Service Bulletin 747–53A2452, Revision 1, 

dated July 16, 2012. 

(2) Do a surface HFEC inspection for cracks 

in the upper and lower chords of the upper 

deck floor beams at permanent fastener 

locations in the applicable areas and stations 

identified in Boeing Alert Service Bulletin 

747–53A2452, Revision 1, dated July 16, 

2012. 

(h) Terminating Modification and Repair for 

the Inspection Specified in Paragraph (g)(1) 

of This AD 

A fastener hole modification or a fastener 

hole repair in Area 1 or Area 2 as described 

in Boeing Alert Service Bulletin 747– 

53A2452, Revision 1, dated July 16, 2012, 

terminates the inspection of the fastener 

holes of the floor panel attachment required 

by paragraph (g)(1) of this AD for the repaired 

or modified area only, provided the 

modification and repair, including related 

investigative and corrective actions, are done 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2452, Revision 1, dated July 16, 

2012, except as required by paragraph (l)(2) 

of this AD. 

(i) Post Modification/Repair Repetitive 

Inspections 

(1) For airplanes on which any fastener 

hole modification or any fastener hole repair 

was done as specified in Boeing Alert Service 

Bulletin 747–53A2452: Except as required by 

paragraph (i)(2) of this AD, at the applicable 

times specified in Tables 8 and 9 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2452, 

Revision 1, dated July 16, 2012, or within 

1,000 flight cycles after the effective date of 

this AD, whichever occurs later, do an open 

hole or surface HFEC inspection, as 

applicable, for cracks in the repaired and 

modified areas, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2452, Revision 1, 

dated July 16, 2012. If any cracking is found, 

before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (o) of this AD. Repeat 

the applicable inspections thereafter at the 

times specified in Tables 8 and 9 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2452, 

Revision 1, dated July 16, 2012. Doing an 

inspection required by this paragraph 

terminates the inspections required by 

paragraph (p) of AD 2005–20–29, 

Amendment 39–14326 (70 FR 59246, October 

12, 2005). 

(2) For any repair #10 or repair #13 done 

as specified in Boeing Alert Service Bulletin 

747–53A2452: Before further flight, do postrepair inspections using a method approved 

in accordance with the procedures specified 

in paragraph (o) of this AD. 

(j) Replacement of the Upper Chords of the 

Upper Deck Floor Beams (Includes PreReplacement Inspections) 

Replace the upper chords of the upper 

deck floor beams by doing the actions 

required by paragraphs (j)(1) and (j)(2) of this 

AD at the times specified in those 

paragraphs. Accomplishing the replacement 

required by this paragraph terminates the 

inspections required by paragraphs (g) and (i) 

of this AD. 

(1) Before the accumulation of 30,000 total 

flight cycles, or within 3,000 flight cycles 

after the effective date of this AD, whichever 

occurs later, do an open hole HFEC 

inspection for cracks at certain fastener 

locations in the floor beam webs and side of 

body frames, and do a detailed inspection for 

cracks of any removed part that will be reinstalled, and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2852, dated June 

22, 2012, except as required by paragraph 

(l)(2) of this AD. Do all applicable corrective 

actions before further flight. 

(2) Before further flight after accomplishing 

the inspections required by paragraph (j)(1) 

of this AD, install new upper chords of the 

upper deck floor beams and reinforcing 

straps or angles, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2852, dated June 

22, 2012, except as required by paragraph 

(l)(2) of this AD. 

(k) Post-Replacement Repetitive Inspections 

For airplanes on which any replacement 

required by paragraph (j) or (k)(2)(ii) of this 

AD is done: At the applicable times specified 

in Tables 2 through 4 in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2852, dated June 22, 2012, 

do HFEC inspections for cracks at the 

permanent fastener holes and the upper 

chords of the upper deck floor beams, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2452, Revision 1, dated July 16, 

2012. 

(1) If any cracking is found during any 

inspection required by the introductory text 

of paragraph (k) or paragraph (k)(2)(i) of this 

AD, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (o) of this 

AD. 

(2) If no cracking is found during any 

inspection required by the introductory text 

of paragraph (k) or paragraph (k)(2)(i) of this 

AD, do the actions required by paragraphs 

(k)(2)(i) and (k)(2)(ii) of this AD. 

(i) Repeat the inspections specified in 

paragraph (k) of this AD thereafter at the 

applicable times specified in Tables 8 and 9 

of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2452, 

Revision 1, dated July 16, 2012. 

(ii) Within 10,000 flight cycles after 

accomplishing the initial HFEC inspections 

required by the introductory text of 

paragraph (k) of this AD, replace the upper 

chords of the upper deck floor beams by 

doing the actions specified in paragraphs 

(j)(1) and (j)(2) of this AD. 

(l) Exceptions to Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2452, Revision 1, dated July 16, 

2012, specifies a compliance time ‘‘after the 

Revision 1 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2452, Revision 1, dated July 16, 

2012; or Boeing Alert Service Bulletin 747– 

53A2852, dated June 22, 2012; specifies to 

contact Boeing for appropriate action: Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (o) of this AD. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), and 

(i) of this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 747–53A2452, 

dated April 3, 2003. For the actions required 

by paragraphs (g), (h), and (i) of this AD that 

are not identified in Boeing Alert Service 

Bulletin 747–53A2452, dated April 3, 2003, 

those actions must still be done. Boeing Alert 

Service Bulletin 747–53A2452, dated April 3, 

2003, is incorporated by reference in AD 

2005–20–29, Amendment 39–14326 (70 FR 

59246, October 12, 2005). 

(n) Special Flight Permit 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(o) 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 (p) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 


jstallworth on DSK7TPTVN1PROD with RULES
18460 Federal Register / Vol. 81, No. 62 / Thursday, March 31, 2016 / Rules and Regulations 

(p) Related Information 

(1) For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: nathan.p.weigand@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (q)(3) and (q)(4) of this AD. 

(q) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2452, Revision 1, dated July 16, 2012. 

(ii) Boeing Alert Service Bulletin 747– 

53A2852, dated June 22, 2012. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on March 

20, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07024 Filed 3–30–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2208; Directorate 

Identifier 2015–NE–19–AD; Amendment 39– 

18447; AD 2016–07–02] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. (Type Certificate 

Previously Held by AlliedSignal Inc., 

Garrett Turbine Engine Company) 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Honeywell International Inc. 

(Honeywell) TFE731–4, –4R, –5AR, 

–5BR, and –5R turbofan engines. This 

AD was prompted by a report of certain 

interstage turbine transition (ITT) ducts 

failing to meet containment capability 

requirements. This AD requires 

replacing certain ITT ducts. We are 

issuing this AD to prevent failure of the 

ITT duct, which could lead to an 

uncontained part release, damage to the 

engine, and damage to the airplane. 

DATES: This AD is effective May 5, 2016 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 5, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Honeywell International Inc., 111 S 34th 

Street, Phoenix, AZ 85034–2802; phone: 

800–601–3099; Internet: https://

myaerospace.honeywell.com/wps/

portal/!ut/. You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 1200 District 

Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

2208. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2208; 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 

Document 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: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; phone: 562–627–5246; fax: 

562–627–5210; email: joseph.costa@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Honeywell TFE731–4, –4R, 

–5AR, –5BR, and –5R turbofan engines 

with ITT duct, part number (P/N) 

3075292–4, installed, with a serial 

number (S/N) listed in Table 2 of 

Honeywell Service Bulletin (SB) 

TFE731–72–3789, Revision 0, dated 

March 23, 2015. The NPRM published 

in the Federal Register on October 29, 

2015 (80 FR 66481). The NPRM was 

prompted by report of certain ITT ducts 

that were not properly heat treated and 

failed to meet containment capability 

requirements. The NPRM proposed to 

require replacing certain ITT ducts. We 

are issuing this AD to correct the unsafe 

condition on these products. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 66481, October 29, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

66481, October 29, 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 66481, 

October 29, 2015). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Honeywell SB TFE731– 

72–3789, Revision 0, dated March 23, 

2015. The SB describes procedures for 

removing affected ITT ducts. 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 47 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 2 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. We estimate that 

replacement parts will cost $15,000 per 

engine. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $712,990. 


jstallworth on DSK7TPTVN1PROD with RULES