43940 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 

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): 

AD 2015–15–08 Bombardier, Inc.: 

Amendment 39–18217. Docket No. 

FAA–2015–0088; Directorate Identifier 

2014–NM–179–AD. 

(a) Effective Date 

This AD becomes effective August 28, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

BD–100–1A10 (Challenger 300) airplanes, 

equipped with a spoiler electronic control 

unit (SECU) having part number (P/N) 

C47330–006, C47330–007, or C47330–008; 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by testing of the 

spoiler electronic control unit (SECU) 

software for an upgrade, which revealed a 

timing error between the command and 

monitor channels. We are issuing this AD to 

prevent a timing error in the SECU software, 

which, in combination with failure of the roll 

disconnect switch, could result in complete 

loss of spoiler functionality and consequent 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of the Maintenance or 

Inspection Program 

Within 600 flight hours since the most 

recent operational test of the aileron 

disconnect system for spoiler functionality as 

of the effective date of this AD, or within 400 

flight hours after the effective date of this AD, 

whichever occurs first: Revise the 

maintenance or inspection program, as 

applicable, to incorporate repetitive 

operational tests of the aileron disconnect 

system for spoiler functionality, and all 

applicable corrective actions, using a method 

approved by the Manager, New York ACO, 

ANE–170, FAA. 

Note 1 to paragraph (g) of this AD: 

Guidance on operational tests of the aileron 

disconnect system can be found in the 

Bombardier Inc., BD–100–1A10 Time Limits/ 

Maintenance Checks (TLMC) Manual. 

(h) Modification of the SECU 

Within 1,600 flight hours or 48 months 

after the effective date of this AD, whichever 

occurs first: Modify and re-identify the 

SECU, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 100–27–16, dated October 

31, 2013. Doing the actions required by this 

paragraph terminates the actions required by 

paragraph (g) of this AD. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an SECU, P/N C47330– 

006, C47330–007, or C47330–008, on any 

airplane. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–24, dated 

August 5, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2015–0088–0002. 

(l) 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 this AD specifies otherwise. 

(i) Bombardier Service Bulletin 100–27–16, 

dated October 31, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) 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. 

(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 July 15, 

2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–17937 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–2014–1052; Directorate 

Identifier 2014–NM–140–AD; Amendment 

39–18210; AD 2015–15–01] 

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) 2004–13– 

02, which applied to certain The Boeing 

Company Model 747–100, –200B, and 

–200F series airplanes. AD 2004–13–02 

required repetitive inspections to find 

discrepancies in the upper and lower 

skins of the fuselage lap joints, and 

repair if necessary. This new AD adds 

post-repair inspections for cracking and 

corrosion, and repair if necessary; 

structural modification at the lap joints; 

and post-modification inspections for 

cracking and corrosion, and repair if 

necessary. This AD was prompted by an 

evaluation by the design approval 

holder (DAH) that indicates the 

longitudinal lap joints are subject to 

widespread fatigue damage (WFD). The 

actions mandated by this AD are 

necessary to reach the limit of validity 

(LOV). We are issuing this AD to detect 

and correct fatigue cracking in the upper 

and lower skins of the fuselage lap 

joints, which could result in sudden 

fracture and failure of a lap joint and 

rapid in-flight decompression of the 

airplane fuselage. 


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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 43941 

DATES: This AD is effective August 28, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 28, 2015. 

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 http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

1052. 

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–2014– 

1052; 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: Bill.Ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2004–13–02, 

Amendment 39–13682 (69 FR 35237, 

June 24, 2004). AD 2004–13–02 applied 

to certain The Boeing Company Model 

747–100, –200B, and –200F series 

airplanes. The NPRM published in the 

Federal Register on January 23, 2015 

(80 FR 3506). The NPRM was prompted 

by an evaluation by the DAH that 

indicates the longitudinal lap joints are 

subject to WFD. A structural 

modification at the lap joint, and postmodification repetitive inspections of 

the skin, existing internal doubler, or 

splice strap for cracks, and corrective 

actions if necessary, are necessary to 

reach the limit of validity (LOV). The 

NPRM proposed to continue to require 

repetitive inspections to find 

discrepancies in the upper and lower 

skins of the fuselage lap joints, and 

repair if necessary; and to add postrepair inspections for cracking and 

corrosion, and repair if necessary; 

structural modification at the lap joints; 

and post-modification inspections for 

cracking and corrosion, and repair if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking in 

the upper and lower skins of the 

fuselage lap joints, which could result 

in sudden fracture and failure of a lap 

joint and rapid in-flight decompression 

of the airplane fuselage. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 3506, 

January 23, 2015) and the FAA’s 

response to each comment. 

Support for the NPRM (80 FR 3506, 

January 23, 2015) 

Boeing stated that it concurs with the 

content of the proposed rule (80 FR 

3506, January 23, 2015). 

Request To Increase Inspection 

Frequency for Certain Airplanes 

An anonymous commenter expressed 

an opinion that there may be more 

reason to check airplanes that are 

frequently pressurized to a greater than 

2.0 per-square-inch (psi) range than 

those that are not pressurized to that 

extent. The commenter also asked if 

there should be a weighted system that 

requires inspections sooner if an 

airplane has proportionally more flight 

cycles in the greater-than-, rather than 

the less-than, 2.0-psi differentials. 

We do not agree with the commenter’s 

request for different inspection intervals 

based on pressurization ranges. The 

proposed inspection intervals were 

based on airplanes flying in a normal 

condition, which included full 

pressurization. In the past, if an operator 

had documentation substantiating flight 

cycles of less than 2.0 psi, some of the 

inspection requirements could be 

reduced. This reduced inspection 

requirement was relieving in nature and 

occurred roughly 10 years ago. We have 

since determined that fleet findings did 

not support this relief and have 

disallowed reduced inspection 

requirements in future ADs. We have 

not provided this relief in this AD. We 

have not changed this final rule in this 

regard. 

Request To Increase WFD Rule 

Applicability 

An anonymous commenter requested 

a reason why the WFD regulation 

applies only to Boeing and not to any 

other airplane manufacturer. The 

commenter stated that it seems like this 

type of WFD would be present in more 

than just Boeing airplanes, and yet the 

regulation and requirement for 

inspection seems to single out Boeing. 

The commenter suggested that it would 

make sense to consolidate and apply 

these requirements equally over all the 

types of airplanes. 

We do not agree with the commenter’s 

request. On May 24, 2012, we made 

effective Amendment 26–6 of 14 CFR 

26.21, ‘‘Limit of Validity,’’ of the 

Federal Aviation Regulations (14 CFR 

26.21). This regulation required all 

design approval holders (DAHs) to 

develop an LOV for affected airplanes, 

which affected several manufacturers 

and models (not exclusively Boeing). 

The LOV is established by means of 

engineering data that support the 

structural maintenance program that 

corresponds to the period of time, stated 

as a number of total accumulated flight 

cycles or flight hours or both, during 

which it is demonstrated that WFD will 

not occur in the airplane. 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 

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 3506, 

January 23, 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 3506, 

January 23, 2015). 

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 Boeing Alert Service 

Bulletin 747–53A2463, Revision 2, 

dated June 16, 2014. The service 

information describes procedures for 

inspections and repairs of cracks and 

corrosion in the skin at lap joints in the 

fuselage. This service information is 

reasonably available because the 


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43942 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section of this AD. 

Costs of Compliance 

We estimate that this AD affects 2 

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 [actions retained from AD 

2004-13-02, Amendment 39-13682 (69 

FR 35237, June 24, 2004)].

5,628 work-hours × $85 per hour = 

$478,380 per inspection cycle.

$0 $478,380 per inspection cycle.$956,760 per inspection cycle. 

Modification [new action] ............................. Up to 3,764 work-hours × $85 per hour = 

$319,940.

$0 Up to $319,940 ........ Up to $639,880. 

Post-modification/post-repair inspections 

[new action].

Up to 3,764 work-hours × $85 per hour = 

$319,940 per inspection cycle.

$0 Up to $319,940 per 

inspection cycle.

Up to $639,880 per 

inspection cycle. 

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 

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 

■ 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) 

2004–13–02, Amendment 39–13682 (69 

FR 35237, June 24, 2004), and adding 

the following new AD: 

2015–15–01 The Boeing Company: 

Amendment 39–18210; Docket No. 

FAA–2014–1052; Directorate Identifier 

2014–NM–140–AD. 

(a) Effective Date 

This AD is effective August 28, 2015. 

(b) Affected ADs 

This AD replaces AD 2004–13–02, 

Amendment 39–13682 (69 FR 35237, June 

24, 2004). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, –200B, and –200F series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

747–53A2463, Revision 2, dated June 16, 

2014. 

(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) that 

indicates the longitudinal lap joints are 

subject to widespread fatigue damage (WFD). 

We are issuing this AD to detect and correct 

fatigue cracking in the upper and lower skins 

of the fuselage lap joints, which could result 

in sudden fracture and failure of a lap joint 

and rapid in-flight decompression of the 

airplane fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections for Corrosion, and Corrective 

Actions 

For airplanes identified as Groups 2 

through 14 in Boeing Alert Service Bulletin 

747–53A2463, Revision 2, dated June 16, 

2014: Except as provided by paragraph (l)(3) 

of this AD, at the applicable time specified 

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

Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, do an 

external low frequency eddy current 

inspection for corrosion at the upper row of 

fasteners in the lap joint, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, except as 

provided by paragraph (l)(1) of this AD. Do 

all applicable corrective actions before 

further flight. Repeat the inspection at the 

upper row of fasteners in the lap joint 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, except as 

provided by paragraph (l)(3) of this AD. 

Accomplishment of a structural modification 

in accordance with Part 5 of Boeing Alert 

Service Bulletin 747–53A2463, Revision 2, 

dated June 16, 2014, except as provided by 

paragraph (l)(1) of this AD, terminates the 

inspection requirements of this paragraph in 

the area of the modification only. The actions 

required by paragraph (j) of this AD are still 

applicable in the area of the modification. 

(h) Inspections for Cracking, and Corrective 

Actions 

For airplanes identified as Groups 2 

through 14 in Boeing Alert Service Bulletin 


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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 43943 

747–53A2463, Revision 2, dated June 16, 

2014: Except as provided by paragraph (l)(3) 

of this AD, at the applicable time specified 

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

Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, do an 

internal medium frequency eddy current 

inspection for skin cracks at the lower row 

of fasteners in the lap joint, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, except as 

provided by paragraph (l)(1) of this AD. Do 

all applicable corrective actions before 

further flight. Repeat the inspection at the 

lower row of fasteners in the lap joint 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, except as 

provided by paragraph (l)(3) of this AD. 

Accomplishment of a structural modification 

in accordance with Part 5 of Boeing Alert 

Service Bulletin 747–53A2463, Revision 2, 

dated June 16, 2014, except as provided by 

paragraph (l)(1) of this AD, terminates the 

inspection requirements of this paragraph in 

the area of the modification only. The actions 

required by paragraph (j) of this AD are still 

applicable in the area of the modification. 

(i) Structural Modification 

For airplanes identified as Groups 2 

through 14 in Boeing Alert Service Bulletin 

747–53A2463, Revision 2, dated June 16, 

2014: At the applicable time specified in 

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

Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, except as 

provided by paragraph (l)(2) of this AD, do 

a structural modification at the lap joints, 

and all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2463, Revision 2, dated June 16, 

2014, except as provided by paragraph (l)(1) 

of this AD. Do all applicable corrective 

actions before further flight. Accomplishment 

of the structural modification required by 

this paragraph terminates the inspections 

required by paragraphs (g), (h), and (k) of this 

AD in the area of the modification only. The 

actions required by paragraph (j) of this AD 

are still applicable in the area of the 

modification. 

(j) Post-Modification Inspections and 

Corrective Actions 

For airplanes on which the actions 

required by paragraph (i) of this AD have 

been done: At the applicable time specified 

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

Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, except as 

provided by paragraph (l)(2) of this AD, do 

an internal high frequency eddy current 

(HFEC) inspection for cracks of the skin or 

existing internal doublers, and an open-hole 

HFEC inspection for splice strap cracks, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2463, Revision 2, dated June 16, 

2014. If any cracking is found, before further 

flight, repair using a method approved in 

accordance with the procedures specified in 

paragraph (n) of this AD. Repeat the 

inspections of the skin, internal doublers, 

and splice straps thereafter at the applicable 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2463, Revision 2, dated 

June 16, 2014. 

(k) Post-Repair Inspections and Corrective 

Actions 

For airplanes with any new or existing 

external doubler repair accomplished at a lap 

joint and the repair doubler length is 40 

inches or longer: At the applicable time 

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

Boeing Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, except as 

provided by paragraph (l)(2) of this AD, do 

an internal HFEC inspection for cracking or 

corrosion of the repairs, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2463, Revision 2, 

dated June 16, 2014, except as provided by 

paragraph (l)(1) of this AD. Do all applicable 

corrective actions before further flight. 

Repeat the inspection of external doubler 

repairs accomplished at lap joints thereafter 

at the applicable intervals specified in 

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

Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014. 

Accomplishment of a structural modification 

in accordance with Part 5 of Boeing Alert 

Service Bulletin 747–53A2463, Revision 2, 

dated June 16, 2014, except as provided by 

paragraph (l)(1) of this AD, terminates the 

inspection requirements of this paragraph in 

the area of the modification only. The actions 

required by paragraph (j) of this AD are still 

applicable in the area of the modification. 

(l) Exceptions 

(1) If, during any action required by this 

AD, Boeing Alert Service Bulletin 747– 

53A2463, Revision 2, dated June 16, 2014, 

specifies to contact Boeing for an inspection 

or modification procedure, or repair 

instructions: Before further flight, do the 

inspection, or modification, or repair using a 

method approved in accordance with the 

procedures specified in paragraph (n) of this 

AD. 

(2) Where Paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2463, 

Revision 2, dated June 16, 2014, specifies a 

compliance time ‘‘after the Revision 2 date of 

this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(3) For the compliance threshold and 

repetitive interval calculations for 

inspections required by paragraphs (g) and 

(h) of this AD, the provisions specified in 

paragraphs (l)(3)(i) and (l)(3)(ii) of this AD 

apply regarding differential pressure. 

(i) For inspections done before the effective 

date of this AD: Flight cycles in which the 

cabin differential pressure was at 2.0 poundsper-square-inch (psi) or less need not be 

counted in the flight-cycle determination, 

provided that flight cycles with momentary 

spikes in cabin differential pressure above 

2.0 psi were included as full pressure flight 

cycles. For this provision to apply, all cabin 

pressure records must have been maintained 

for each airplane. No fleet-averaging of cabin 

pressure is allowed. 

(ii) For inspections done on or after the 

effective date of this AD: All flight cycles 

must be counted, regardless of differential 

pressure. 

(m) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraph (m)(1) or 

(m)(2) of this AD. 

(1) Boeing Alert Service Bulletin 747– 

53A2463, dated March 7, 2002, including 

Appendices A, B, and C, dated March 7, 

2002, which was incorporated by reference in 

AD 2004–13–02, Amendment 39–13682 (69 

FR 35237, June 24, 2004). 

(2) Boeing Alert Service Bulletin 747– 

53A2463, Revision 1, dated April 16, 2009, 

which is not incorporated by reference in this 

AD. 

(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)(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 for AD 2004–13–02, 

Amendment 39–13682 (69 FR 35237, June 

24, 2004), are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

and (h) of this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

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

email: Bill.Ashforth@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 


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43944 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Rules and Regulations 

1Revisions to Auxiliary Installations, 

Replacement Facilities, and Siting and 

Maintenance Regulations, Order No. 790–A, 79 FR 

70056 (Nov. 25, 2014), FERC Stats. & Regs. ¶ 31,361 

(2014) (cross-referenced at 149 FERC ¶ 61,144 

(2014)). 

2Order No. 790, 78 FR 72794–801 (Dec. 4, 2013), 

FERC Stats. & Regs. ¶ 31,351 (2013) (crossreferenced at 145 FERC ¶ 61,154 (2013)). 

3 18 CFR 2.55 (2014). 

(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– 

53A2463, Revision 2, dated June 16, 2014. 

(ii) Reserved. 

(3) For Boeing 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 July 10, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–17978 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Parts 2 and 157 

[Docket No. RM12–11–003; Order No. 790– 

B] 

Revisions to Auxiliary Installations, 

Replacement Facilities, and Siting and 

Maintenance Regulations 

AGENCY: Federal Energy Regulatory 

Commission. 

ACTION: Final rule, order on 

clarification. 

SUMMARY: The Federal Energy 

Regulatory Commission (Commission) is 

amending its regulations to: Provide 

pre-granted authority under a new 

paragraph to abandon or replace 

auxiliary facilities, subject to certain 

conditions; permit auxiliary facilities 

that cannot meet the conditions for the 

pre-granted abandonment authority in 

the new paragraph to be abandoned 

under the blanket certificate regulations, 

subject to those regulations’ 

requirements; and permit replacement 

facilities constructed under the 

regulations to be abandoned under the 

blanket certificate regulations, subject to 

those regulations’ requirements. 

DATES: This rule will become effective 

October 7, 2015. 

FOR FURTHER INFORMATION CONTACT: 

Katherine Liberty, Office of the General 

Counsel, Federal Energy Regulatory 

Commission, 888 First Street NE., 

Washington, DC 20426, (202) 502– 

6491, katherine.liberty@ferc.gov. 

Gordon Wagner, Office of the General 

Counsel, Federal Energy Regulatory 

Commission, 888 First Street NE., 

Washington, DC 20426, (202) 502– 

8947, gordon.wagner@ferc.gov. 

Howard Wheeler, Office of Energy 

Projects, Federal Energy Regulatory 

Commission, 888 First Street NE., 

Washington, DC 20426, (202) 502– 

8688, howard.wheeler@ferc.gov. 

Shannon Jones, Office of Energy 

Projects, Federal Energy Regulatory 

Commission, 888 First Street NE., 

Washington, DC 20426, (202) 502– 

6410, shannon.jones@ferc.gov. 

SUPPLEMENTARY INFORMATION: 

ORDER NO. 790–B 

Table of Contents 

Paragraph 

Nos. 

I. Discussion ............................. 4 

A. Section 2.55(a) Auxiliary Facilities ................ 9 

B. Section 2.55(b) Replacements .................... 14 

II. Information Collection 

Statement .............................. 18 

III. Environmental Analysis .... 23 

IV. Regulatory Flexibility Act 24 

V. Document Availability ....... 26 

VI. Effective Date and Congressional Notification ......... 29 

Order No. 790–B 

Final Rule 

Order on Rehearing and Clarification 

1. On November 20, 2014, the Federal 

Energy Regulatory Commission 

(Commission) issued Order No. 790–A,1

which affirmed, inter alia, the 

Commission’s clarification in Order No. 

790 2 that auxiliary facilities installed 

under section 2.55(a) of the 

Commission’s regulations 3 may only 

utilize rights-of-way, facility sites, and 

work spaces authorized for the 

construction and operation of interstate 

transmission facilities. 

2. On December 22, 2014, National 

Fuel Gas Supply Corporation and 

Empire Pipeline, Inc. (collectively, 

National Fuel) filed a request that the 

Commission revise its part 157, subpart 

F, blanket certificate regulations to 

provide a mechanism under those 

regulations for the abandonment of 

auxiliary facilities that were constructed 

under section 2.55(a) and replacement 

facilities that were constructed under 

section 2.55(b). National Fuel also 

requests clarification that in addition to 

authorizing new auxiliary installations, 

section 2.55(a) also authorizes the 

replacement of existing auxiliary 

facilities without the need for 

abandonment authority under section 

7(b) of the Natural Gas Act (NGA). 

3. As discussed below, this order 

responds to National Fuel’s requests by 

(1) adopting a new subsection 2.55(a)(3) 

to provide pre-granted authority to 

abandon or replace auxiliary facilities, 

subject to certain conditions; (2) 

amending part 157 to provide authority, 

subject to the blanket certificate 

regulations’ conditions, to abandon 

section 2.55(a) auxiliary facilities that 

cannot meet the conditions for the pregranted abandonment authority being 

added to section 2.55(a) and to abandon 

section 2.55(b) replacement facilities. 

I. Discussion 

4. In Order No. 790–A, the 

Commission explained that section 2.55 

facilities are installed under the 

certificate authority that authorized the 

interstate transmission pipeline 

facilities being augmented or replaced. 

The Commission further explained that 

because section 2.55 auxiliary and 

replacement facilities are certificated 

facilities, a company needs prior 

authorization under NGA section 7(b) to 

abandon such facilities. The 

Commission stated that in many 

instances companies should be able to 

rely on their part 157, subpart F, blanket 

certificate authority to abandon section 

2.55 facilities. In view of this statement, 

National Fuel believes it is the 

Commission’s intent that companies be 

able to rely on their part 157 blanket 

certificate authority to abandon facilities 

installed under section 2.55. 

5. National Fuel points out, however, 

that section 157.202(b)(3) of the blanket 

certificate regulations states that a 

‘‘facility’’ for purposes of the blanket 

program does not include a facility 

‘‘described under section 2.55,’’ and that 

section 157.216 states that blanket 

certificate abandonment authority is 

limited to facilities that ‘‘did or could 


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