43974 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Proposed Rules 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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): 

The Boeing Company: Docket No. FAA– 

2015–2959; Directorate Identifier 2015– 

NM–008–AD. 

(a) Comments Due Date 

We must receive comments by September 

8, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 787–8 airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin B787–81205–SB290015–00, 

Issue 002, dated November 25, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic Power. 

(e) Unsafe Condition 

This AD was prompted by reports 

indicating that the ram air turbine (RAT) 

assembly may fail to operate if deployed at 

low airspeeds. We are issuing this AD to 

prevent failure of the RAT assembly to 

operate at low air speeds. The volume fuse 

on the RAT assembly may be activated inflight before the RAT is deployed. This may 

lead to improper pump hydraulic pressure 

offloading when the RAT is needed. Failure 

of the RAT to operate in an all engine out 

event would result in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

Within 36 months after the effective date 

of this AD, replace the RAT pump and 

control module assembly or the RAT 

assembly, including an installation test and 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin B787–81205– 

SB290015–00, Issue 002, dated November 25, 

2014. Do all applicable corrective actions 

before further flight. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Alert Service 

Bulletin B787–81205–SB290015–00, Issue 

001, dated September 4, 2014, which is not 

incorporated by reference in this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j)(1) 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 

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) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

(1) For more information about this AD, 

contact Sean J. Schauer, Aerospace Engineer, 

Systems and Equipment Branch, ANM 130S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6479; fax: 425– 

917–6590; email: sean.schauer@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

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

Internet https://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on July 16, 

2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18151 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2961; Directorate 

Identifier 2014–NM–145–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2012–15– 

13, which applies to certain The Boeing 

Company Model 747–100B SUD, 747– 

300, 747–400, and 747–400D series 

airplanes; and Model 747–200B series 

airplanes having a stretched upper deck. 

AD 2012–15–13 currently requires 

inspections for cracking and 

discrepancies of certain fasteners; 

modification of the frame-to-tension-tie 

joints; repetitive post-modification 

inspections; related investigative and 

corrective actions if necessary; and 

repetitive inspections for cracking in the 

tension tie channels, and repair if 

necessary. For certain airplanes, AD 

2012–15–13 also requires an inspection 

to determine if the angle is installed 

correctly, and re-installation if 

necessary; and an inspection at the 

fastener locations where the tension tie 

previously attached to the frame prior to 

certain modifications, and repair if 

necessary. Since we issued AD 2012– 

15–13, an evaluation indicated that the 

upper deck is subject to widespread 

fatigue damage (WFD). This proposed 

AD would add a new inspection for 

cracking in the tension tie channels and 

post-modification inspections of the 

modified tension ties for cracking, and 

repair if necessary. We are proposing 

this AD to prevent fatigue cracking of 

the tension ties, shear webs, and frames 

of the upper deck, which could result in 

rapid decompression and reduced 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by September 8, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 


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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Proposed Rules 43975 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2961. 

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– 

2961; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917– 

6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–2961; Directorate Identifier 

2014–NM–145–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On July 23, 2012, we issued AD 2012– 

15–13, Amendment 39–17142 (77 FR 

47267, August 8, 2012), for certain The 

Boeing Company Model 747–100B SUD, 

747–300, 747–400, and 747–400D series 

airplanes; and Model 747–200B series 

airplanes having a stretched upper deck. 

AD 2012–15–13 requires repetitive open 

hole high frequency eddy current 

(HFEC) inspections for cracking in the 

forward and aft tension tie channels, 

and repair if necessary. For certain 

airplanes, AD 2012–15–13 also requires 

a one-time angle inspection to 

determine if the angle is installed 

correctly, and re-installation if 

necessary; and a one-time open hole 

HFEC inspection at the fastener 

locations where the tension tie 

previously attached to the frame prior to 

certain modifications, and repair if 

necessary. AD 2012–15–13 resulted 

from reports of cracked and severed 

tension ties, broken fasteners, and 

cracks in the frame, shear web, and 

shear ties adjacent to tension ties for the 

upper deck. We issued AD 2012–15–13 

to detect and correct cracking of the 

tension ties, shear webs, and frames of 

the upper deck, which could result in 

rapid decompression and reduced 

structural integrity of the airplane. 

Widespread Fatigue Damage 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as widespread fatigue 

damage (WFD). As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD rule (75 FR 69746, 

November 15, 2010) became effective on 

January 14, 2011. The WFD rule 

requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

design approval holders (DAHs) 

establish a limit of validity (LOV) of the 

engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

Actions Since AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, 

August 8, 2012), Was Issued 

The preamble to AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, 

August 8, 2012), specified that we 

considered the requirements of that AD 


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‘‘interim action.’’ AD 2012–15–13 

explained that we might consider 

further rulemaking if final action is later 

identified. Since we issued AD 2012– 

15–13, an evaluation by the DAH 

indicated that the upper deck is subject 

to WFD. We have determined that it is 

necessary to mandate a new inspection 

for cracking in the tension tie channels, 

repetitive post-modification inspections 

of the modified tension ties for cracking, 

and repair if necessary. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2559, Revision 2, 

dated May 13, 2014. The service 

information describes procedures for 

modifying the tension tie and frame at 

certain center sections. 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 of this NPRM. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all of 

the requirements of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, 

August 8, 2012). For certain airplanes, 

this proposed AD would mandate a new 

inspection for cracking in the forward 

and aft tension tie channels, repetitive 

post-modification inspections of the 

modified tension ties for cracking, and 

repair if necessary. Refer to Boeing Alert 

Service Bulletin 747–53A2559, Revision 

2, dated May 13, 2014, for details on the 

procedures and compliance times. 

Explanation of Compliance Time 

The compliance time for the 

modification specified in this proposed 

AD for addressing WFD was established 

to ensure that discrepant structure is 

modified before WFD develops in 

airplanes. Standard inspection 

techniques cannot be relied on to detect 

WFD before it becomes a hazard to 

flight. We will not grant any extensions 

of the compliance time to complete any 

AD-mandated service bulletin related to 

WFD without extensive new data that 

would substantiate and clearly warrant 

such an extension. 

Costs of Compliance 

We estimate that this proposed AD 

affects 120 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

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

operators 

Retained modification in AD 2012–15– 

13, Amendment 39–17142 (77 FR 

47267, August 8, 2012) (67 airplanes).

Between 257 and 263 work-hours = 

between $21,845 and $22,355.

Between $341,334 

and $345,490.

Between $363,179 

and $367,845.

Between 

$24,332,993 and 

$24,645,615. 

Retained post-modification inspections 

in AD 2012–15–13, Amendment 39– 

17142 (77 FR 47267, August 8, 

2012) (67 airplanes).

6 work-hours × $85 per hour = $510 

per inspection cycle.

$0 .......................... $510 per inspection cycle.$34,170 per inspection cycle. 

New proposed inspection ..................... 10 work-hours × $85 per hour = $850 $0 .......................... $850 ...................... $102,000. 

New proposed post-modification eddy 

current inspections.

216 work-hours × $85 per hour = 

$18,360 per inspection cycle.

$0 .......................... $18,360 per inspection cycle.$2,203,200 per inspection cycle. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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 

removing Airworthiness Directive (AD) 

2012–15–13, Amendment 39–17142 (77 

FR 47267, August 8, 2012), and adding 

the following new AD: 


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The Boeing Company: Docket No. FAA– 

2015–2961; Directorate Identifier 2014– 

NM–145–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by September 8, 2015. 

(b) Affected ADs 

This AD replaces AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100B SUD, 747–300, 747–400, 

and 747–400D series airplanes; and Model 

747–200B series airplanes having a stretched 

upper deck; certificated in any category; 

excluding airplanes that have been converted 

to a large cargo freighter configuration. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracked and severed tension ties, broken 

fasteners, and cracks in the frame, shear web, 

and shear ties adjacent to tension ties for the 

upper deck. This AD was also prompted by 

an evaluation by the design approval holder 

(DAH), which indicated that the upper deck 

is subject to widespread fatigue damage 

(WFD). We are issuing this AD to prevent 

fatigue cracking of the tension ties, shear 

webs, and frames of the upper deck, which 

could result in rapid decompression and 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Stage 1 Inspections, 

With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012), with no changes. For all airplanes: 

Do detailed inspections for cracking or 

discrepancies of the fasteners in the tension 

ties, shear webs, and frames at body stations 

(STA) 1120 through 1220, and related 

investigative and corrective actions as 

applicable, by doing all actions specified in 

and in accordance with ‘‘Stage 1 Inspection’’ 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2507, 

dated April 21, 2005, except as provided by 

paragraph (k) of this AD; or Boeing Alert 

Service Bulletin 747–53A2507, Revision 1, 

dated January 14, 2010. As of September 12, 

2012 (the effective date of AD 2012–15–13), 

only Boeing Alert Service Bulletin 747– 

53A2507, Revision 1, dated January 14, 2010, 

may be used to do the actions required by 

this paragraph. Do the Stage 1 inspections at 

the applicable times specified in paragraphs 

(h) and (i) of this AD, except as provided by 

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

Accomplishment of the initial Stage 2 

inspection required by paragraph (j) of this 

AD terminates the requirements of this 

paragraph. Any applicable related 

investigative and corrective actions must be 

done before further flight. Doing the 

modification required by paragraph (p) of 

this AD terminates the repetitive inspection 

requirements of this paragraph. 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2507, 

dated April 21, 2005, specifies a compliance 

time relative to ‘‘the original issue date on 

this service bulletin,’’ this AD requires 

compliance before the specified compliance 

time after April 26, 2006 (the effective date 

of AD 2006–06–11, Amendment 39–14520 

(71 FR 14367, March 22, 2006)). 

(2) For any airplane that reaches the 

applicable compliance time for the initial 

Stage 2 inspection (as specified in Table 1, 

Compliance Recommendations, under 

paragraph 1.E., of Boeing Alert Service 

Bulletin 747–53A2507, dated April 21, 2005) 

before reaching the applicable compliance 

time for the initial Stage 1 inspection: 

Accomplishment of the initial Stage 2 

inspection terminates the Stage 1 

inspections. 

(h) Retained Compliance Time for Initial 

Stage 1 Inspection, With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012), with no changes. Do the initial 

Stage 1 inspection at the earlier of the times 

specified in paragraphs (h)(1) and (h)(2) of 

this AD. 

(1) Inspect at the earlier of the times 

specified in paragraphs (h)(1)(i) and (h)(1)(ii) 

of this AD. 

(i) At the applicable time specified in 

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

Alert Service Bulletin 747–53A2507, dated 

April 21, 2005. 

(ii) Before the accumulation of 10,000 total 

flight cycles, or within 250 flight cycles after 

November 28, 2007 (the effective date of AD 

2007–23–18, Amendment 39–15266 (72 FR 

65655, November 23, 2007)), whichever 

occurs later. 

(2) Inspect at the later of the times 

specified in paragraphs (h)(2)(i) and (h)(2)(ii) 

of this AD. 

(i) Before the accumulation of 12,000 total 

flight cycles. 

(ii) Within 50 flight cycles or 20 days, 

whichever occurs first, after November 28, 

2007 (the effective date of AD 2007–23–18, 

Amendment 39–15266 (72 FR 65655, 

November 23, 2007)). 

(i) Retained Compliance Times for Repetitive 

Stage 1 Inspections, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2012–15–13, Amendment 

39–17142 (77 FR 47267, August 8, 2012), 

with no changes. Repeat the Stage 1 

inspection specified in paragraph (g) of this 

AD at the time specified in paragraph (i)(1) 

or (i)(2) of this AD, as applicable. Repeat the 

inspection thereafter at intervals not to 

exceed 250 flight cycles, until the initial 

Stage 2 inspection required by paragraph (j) 

of this AD has been done. 

(1) For airplanes on which the initial Stage 

1 inspection has not been accomplished as of 

November 28, 2007 (the effective date of AD 

2007–23–18, Amendment 39–15266 (72 FR 

65655, November 23, 2007)): Do the next 

inspection before the accumulation of 10,000 

total flight cycles, or within 250 flight cycles 

after the initial Stage 1 inspection done in 

accordance with paragraph (g) of this AD, 

whichever occurs later. 

(2) For airplanes on which the initial Stage 

1 inspection has been accomplished as of 

November 28, 2007 (the effective date of AD 

2007–23–18, Amendment 39–15266 (72 FR 

65655, November 23, 2007)): Do the next 

inspection at the applicable time specified in 

paragraph (i)(2)(i) or (i)(2)(ii) of this AD. 

(i) For airplanes that have accumulated 

fewer than 12,000 total flight cycles as of 

November 28, 2007 (the effective date of AD 

2007–23–18, Amendment 39–15266 (72 FR 

65655, November 23, 2007)): Do the next 

inspection before the accumulation of 10,000 

total flight cycles, or within 250 flight cycles 

after November 28, 2007, whichever occurs 

later. 

(ii) For airplanes that have accumulated 

12,000 total flight cycles or more as of 

November 28, 2007 (the effective date of AD 

2007–23–18, Amendment 39–15266 (72 FR 

65655, November 23, 2007)): Do the next 

inspection at the later of the times specified 

in paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of 

this AD. 

(A) Within 250 flight cycles after 

accomplishment of the initial Stage 1 

inspection. 

(B) Within 50 flight cycles or 20 days, 

whichever occurs first, after November 28, 

2007 (the effective date of AD 2007–23–18, 

Amendment 39–15266 (72 FR 65655, 

November 23, 2007)). 

(j) Retained Repetitive Stage 2 Inspections, 

With No Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2012–15–13, Amendment 

39–17142 (77 FR 47267, August 8, 2012), 

with no changes. For all airplanes: Do 

detailed and high frequency eddy current 

inspections for cracking or discrepancies of 

the fasteners in the tension ties, shear webs, 

and frames at body stations 1120 through 

1220, and related investigative and corrective 

actions as applicable, by doing all actions 

specified in and in accordance with ‘‘Stage 

2 Inspection’’ of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2507, dated April 21, 2005, or 

Boeing Alert Service Bulletin 747–53A2507, 

Revision 1, dated January 14, 2010; except as 

provided by paragraph (k) of this AD. Do the 

initial inspections at the earlier of the times 

specified in paragraphs (j)(1) and (j)(2) of this 

AD. Repeat the Stage 2 inspection thereafter 

at the applicable times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2507, dated April 21, 2005, 

or Boeing Alert Service Bulletin 747– 

53A2507, Revision 1, dated January 14, 2010. 

As of September 12, 2012 (the effective date 

of AD 2012–15–13), only Boeing Alert 

Service Bulletin 747–53A2507, Revision 1, 

dated January 14, 2010, may be used. Any 

applicable related investigative and 

corrective actions must be done before 

further flight. Accomplishment of the initial 

Stage 2 inspection ends the repetitive Stage 

1 inspections. Doing the modification 

required by paragraph (p) of this AD 


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terminates the repetitive inspection 

requirements of this paragraph. 

(1) Before the accumulation of 16,000 total 

flight cycles, or within 1,000 flight cycles 

after November 28, 2007 (the effective date of 

AD 2007–23–18, Amendment 39–15266 (72 

FR 65655, November 23, 2007)), whichever 

occurs later. 

(2) Before the accumulation of 10,000 total 

flight cycles, or within 1,000 flight cycles 

after September 12, 2012 (the effective date 

of AD 2012–15–13, Amendment 39–17142 

(77 FR 47267, August 8, 2012)), whichever 

occurs later. 

(k) Retained Exception to Corrective Action 

Instructions, With No Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012), with no changes. If any discrepancy, 

including but not limited to any crack, 

broken fastener, loose fastener, or missing 

fastener is found during any inspection 

required by paragraph (g), (h), (i), or (j) of this 

AD, and Boeing Alert Service Bulletin 747– 

53A2507, dated April 21, 2005, or Boeing 

Alert Service Bulletin 747–53A2507, 

Revision 1, dated January 14, 2010, specifies 

to contact Boeing for appropriate action: 

Before further flight, repair the discrepancy 

using a method approved in accordance with 

the procedures specified in paragraph (t) of 

this AD. 

(l) Retained Stage 2 Inspection: Work at STA 

1140, With No Changes 

This paragraph restates the requirements of 

paragraph (l) of AD 2012–15–13, Amendment 

39–17142 (77 FR 47267, August 8, 2012), 

with no changes. For all airplanes: Except as 

provided by paragraph (o) of this AD, at the 

time specified in paragraph 1.E, 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2507, Revision 1, dated 

January 14, 2010, do an open hole high 

frequency eddy current (HFEC) inspection for 

cracking in the forward and aft tension tie 

channels at 12 fastener locations inboard of 

the aluminum straps at STA 1140, and before 

further flight do all applicable repairs. Do all 

actions in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2507, Revision 1, 

dated January 14, 2010. Repeat the 

inspections thereafter at the time specified in 

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

Alert Service Bulletin 747–53A2507, 

Revision 1, dated January 14, 2010. Doing the 

modification required by paragraph (p) of 

this AD terminates the inspection 

requirements in this paragraph. 

(m) Retained One-Time Inspection for 

Incorrectly Installed Angles, With No 

Changes 

This paragraph restates the requirements of 

paragraph (m) of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012), with no changes. For Group 1, 

Configuration 1, airplanes as identified in 

Boeing Alert Service Bulletin 747–53A2507, 

Revision 1, dated January 14, 2010: Except as 

provided by paragraph (o) of this AD, at the 

time specified in paragraph 1.E, 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2507, Revision 1, dated 

January 14, 2010, do a detailed inspection to 

determine if the angle is installed correctly, 

and before further flight re-install all angles 

that were installed incorrectly. Do all actions 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2507, Revision 1, dated January 14, 

2010. 

(n) Retained One-time Inspection for Cracks 

in Frames at Previous Tension Tie Locations, 

With No Changes 

This paragraph restates the requirements of 

paragraph (n) of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012), with no changes. For Group 1, 

Configuration 2, airplanes; and Groups 2 and 

3 airplanes; as identified in Boeing Alert 

Service Bulletin 747–53A2507, Revision 1, 

dated January 14, 2010: Except as provided 

by paragraph (o) of this AD, at the time 

specified in paragraph 1.E, ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2507, 

Revision 1, dated January 14, 2010, do an 

open hole HFEC inspection for cracks at the 

fastener locations (STAs 1120, 1160, 1200, 

and 1220) where the tension tie previously 

attached to the frame prior to modification to 

the Boeing Special Freighter or Boeing 

Converted Freighter configuration, and before 

further flight do all applicable repairs. Do all 

actions in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2507, Revision 1, 

dated January 14, 2010. Doing the 

modification required by paragraph (p) of 

this AD terminates the one-time inspection 

requirements in this paragraph. 

(o) Retained Exception to Boeing Alert 

Service Bulletin 747–53A2507, Revision 1, 

Dated January 14, 2010, With No Changes 

This paragraph restates the requirements of 

paragraph (o) of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012), with no changes. Where paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2507, Revision 1, dated 

January 14, 2010, specifies a compliance time 

relative to ‘‘the Revision 1 date of this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time after 

September 12, 2012 (the effective date of AD 

2012–15–13). 

(p) Retained Modification and PostModification Repetitive Inspections, With 

Revised Service Information 

This paragraph restates the requirements of 

paragraph (p) of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012), with revised service information. 

Except as provided by paragraphs (p)(1) and 

(p)(2) of this AD: At the applicable times 

specified in paragraph 1.E, ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2559, 

Revision 1, dated August 4, 2011, modify the 

frame-to-tension-tie joints at STAs 1120 

through 1220; do all related investigative and 

applicable corrective actions; do the 

repetitive post-modification detailed 

inspections for cracking of the tension tie and 

frame structure and all applicable corrective 

actions; and do the additional modification. 

Do all actions in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2559, Revision 1, 

dated August 4, 2011, or Boeing Alert Service 

Bulletin 747–53A2559, Revision 2, dated 

May 13, 2014. Modifying the frame-totension-tie joints at STAs 1120 through 1220 

terminates the repetitive inspection 

requirements of paragraphs (g) and (j) of this 

AD, the inspection requirements of paragraph 

(l) of this AD, and the one-time inspection 

requirement of paragraph (n) of this AD. As 

of the effective date of this AD, only Boeing 

Alert Service Bulletin 747–53A2559, 

Revision 2, dated May 13, 2014, may be used 

to accomplish the actions specified in this 

paragraph. 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2559, 

Revision 1, dated August 4, 2011, specifies a 

compliance time relative to ‘‘the original 

issue date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after September 12, 2012 

(the effective date of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012)). 

(2) Where Boeing Service Bulletin 747– 

53A2559, Revision 1, dated August 4, 2011, 

or Boeing Alert Service Bulletin 747– 

53A2559, Revision 2, dated May 13, 2014, 

specifies to contact Boeing for repair 

instructions or additional modification 

requirements: Before further flight, repair the 

cracking or do the additional actions using a 

method approved in accordance with the 

procedures specified in paragraph (t) of this 

AD. 

(q) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the credit provided 

by paragraph (q) of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, August 

8, 2012), with no changes. This paragraph 

provides credit for the corresponding actions 

required by paragraph (p) of this AD, if those 

actions were done before September 12, 2012 

(the effective date of AD 2012–15–13), using 

Boeing Alert Service Bulletin 747–53A2559, 

dated January 8, 2009. 

(r) New Repetitive Post-Modification Eddy 

Current Inspections 

Do an eddy current inspection of all areas 

of the modified tension ties for cracking, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2559, Revision 2, 

dated May 13, 2014. Do the inspection at the 

time specified in Table 2 of paragraph 1.E, 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2559, Revision 2, dated 

May 13, 2014, except where paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2559, Revision 2, dated May 13, 

2014, specifies a compliance time relative to 

‘‘the Revision 2 date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. If any crack is found, before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (t) of this AD. If no 

crack is found, repeat the inspection 

thereafter at the intervals specified in 

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

Service Bulletin 747–53A2559, Revision 2, 

dated May 13, 2014. 


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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Proposed Rules 43979 

(s) New One-Time Surface HFEC Inspections 

Do a surface HFEC inspection of the 

tension tie center section, for cracking in the 

forward and aft tension tie channels between 

STA 1120 through 1220, in accordance with 

Part 4 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2559, 

Revision 2, dated May 13, 2014. Do the 

inspection at the applicable time specified in 

Table 1 or Table 3 of paragraph 1.E, 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2559, Revision 2, dated 

May 13, 2014, except where paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2559, Revision 2, dated 

May 13, 2014, specifies a compliance time 

relative to ‘‘the Revision 2 date of this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. If any crack is 

found, before further flight, repair the crack 

using a method approved in accordance with 

the procedures specified in paragraph (t) of 

this AD. 

(t) 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 (u)(1) 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 

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) AMOCs approved previously for AD 

2012–15–13, Amendment 39–17142 (77 FR 

47267, August 8, 2012), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(u) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; fax 

206–766–5683; Internet https:// 

www.myboeingfleet.com. You may view this 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on July 16, 

2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18152 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Parts 157, 260, and 284 

[Docket No. RM96–1–038] 

Standards for Business Practices of 

Interstate Natural Gas Pipelines 

AGENCY: Federal Energy Regulatory 

Commission. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Federal Energy 

Regulatory Commission (Commission) is 

proposing to amend its regulations to 

incorporate by reference, with certain 

enumerated exceptions, the latest 

version (Version 3.0) of business 

practice standards adopted by the 

Wholesale Gas Quadrant of the North 

American Energy Standards Board 

(NAESB) applicable to natural gas 

pipelines. These revisions, in part, 

revise the codes used to identify receipt 

and delivery locations in the Index of 

Customers. In addition, for consistency 

with the revisions to the Index of 

Customers, the Commission is 

proposing certain conforming changes 

to the Commission’s regulations on 

exhibits and on system flow diagrams. 

DATES: Comments are due August 24, 

2015. 

ADDRESSES: Comments, identified by 

docket number, may be filed in the 

following ways: 

• Electronic Filing through http://

www.ferc.gov. Documents created 

electronically using word processing 

software should be filed in native 

applications or print-to-PDF format and 

not in a scanned format. 

• Mail/Hand Delivery: Those unable 

to file electronically may mail or handdeliver comments to: Federal Energy 

Regulatory Commission, Secretary of the 

Commission, 888 First Street NE., 

Washington, DC 20426. 

Instructions: For detailed instructions 

on submitting comments and additional 

information on the rulemaking process, 

see the Comment Procedures section of 

this document. 

FOR FURTHER INFORMATION CONTACT: 

Stanley Wolf (technical issues), Office of 

Energy Policy and Innovation, Federal 

Energy Regulatory Commission, 888 

First Street NE., Washington, DC 20426, 

Telephone: (202) 502–6841, Email: 

stanley.wolf@ferc.gov. 

Oscar F. Santillana (technical issues), 

Office of Energy Market Regulation, 

Federal Energy Regulatory Commission, 

888 First Street NE., Washington, DC 

20426, Telephone: (202) 502–6392, 

Email: oscar.santillana@ferc.gov. 

Gary D. Cohen (legal issues), Office of 

the General Counsel, Federal Energy 

Regulatory Commission, 888 First Street 

NE., Washington, DC 20426, Telephone: 

(202) 502–8321, Email: gary.cohen@

ferc.gov. 

SUPPLEMENTARY INFORMATION: 

Table of Contents 

Paragraph Nos. 

I. Background ................................................................................................................................................................................ 2 

II. Discussion ................................................................................................................................................................................ 8 

A. Modifications to Standards to Support the Commission’s Show Cause Order in Docket No. RP14–442–000 .......... 12 

B. Location Codes .................................................................................................................................................................. 15 

C. Request in Order No. 587–V for NAESB to Evaluate the Use of the Terms ‘‘Operating Capacity’’ and ‘‘Design Capacity’’ ................................................................................................................................................................................ 18 

D. Standards Previously Not Incorporated by Reference .................................................................................................... 20 

1. Contracts Standards and eTariff Related Standards ................................................................................................ 20 

2. Record Retention Standards ...................................................................................................................................... 21 

3. WGQ Interpretations .................................................................................................................................................. 22 

E. Proposed Implementation Procedures ............................................................................................................................. 23 

III. Notice of Use of Voluntary Consensus Standards ................................................................................................................ 28 


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