Federal Register / Vol. 80, No. 221 / Tuesday, November 17, 2015 / Proposed Rules 71751 

(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, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2015–17, dated 

July 16, 2015, 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 Docket No. FAA– 

2015–4814. 

(2) 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. 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. 

Issued in Renton, Washington, on 

November 5, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28885 Filed 11–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4813; Directorate 

Identifier 2013–NM–161–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 99–16–01, 

for certain Airbus Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). AD 99–16– 

01 currently requires repetitive 

inspections of certain bolt holes where 

parts of the main landing gear (MLG) are 

attached to the wing rear spar, and 

repair if necessary. Since we issued AD– 

99–16–01, we have determined that the 

risk of cracking in the rear spar is higher 

than initially determined. This 

proposed AD would add airplanes to the 

applicability, reduce the compliance 

times and repetitive intervals for the 

inspections, and change the inspection 

procedures. We are proposing this AD to 

detect and correct cracking of the rear 

spar of the wing, which could result in 

reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by January 4, 2016. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.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. 

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– 

4813; 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 Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–2125; 

fax: 425–227–1149. 

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–2015–4813; Directorate Identifier 

2013–NM–161–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 based on 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 21, 1999, we issued AD 99– 

16–01, Amendment 39–11236 (64 FR 

40743, July 28, 1999). AD 99–16–01 

requires actions intended to address an 

unsafe condition on Airbus Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes). 

Since we issued AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, 


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July 28, 1999), a fleet survey and 

updated fatigue and damage tolerance 

analyses have shown that the threshold 

for the initial inspections and the 

intervals for the repetitive inspections 

need to be reduced. 

The European Aviation Safety Agency 

(EASA), which is Technical Agent for 

the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0180, dated August 9, 

2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During full-scale fatigue testing, cracks 

were found on the rear spar from certain bolt 

holes at the attachment of the Main Landing 

gear (MLG) forward pick-up fitting and the 

MLG Rib 5 aft. 

This condition, if not detected and 

corrected, could reduce the structural 

integrity of the aeroplane. 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France issued * * * [an AD] (later 

revised) to require High Frequency Eddy 

Current (HFEC) or Ultrasonic (U/S) 

inspections of certain fastener holes where 

the MLG forward pick-up fitting and MLG 

Rib 5 aft are attached to the rear spar. 

Since DGAC France * * * [issued a 

revised AD, which corresponded to FAA AD 

99–16–01, Amendment 39–11236 (64 FR 

40743, July 28, 1999), which superseded 

FAA AD 95–20–02, Amendment 39–9380 (60 

FR 52618, October 10, 1995)] * * *, a fleet 

survey and updated Fatigue and Damage 

Tolerance analyses have been performed in 

order to substantiate the second A300–600 

Extended Service Goal (ESG2) exercise. The 

results of these analyses have shown that the 

threshold and interval must be reduced to 

allow timely detection of these cracks and 

accomplishment of an applicable corrective 

action. 

For the reasons described above, this 

[EASA] AD retains the requirements of [the 

revised DGAC France AD], which is 

superseded, but reduces the related 

compliance times. 

The new, reduced threshold for the 

initial inspection ranges between 8,900 

total flight cycles/20,000 total flight 

hours, and 34,600 total flight cycles/

77,800 total flight hours, depending on 

the modification. The grace periods (750 

or 1,500 landings) for airplanes that 

have exceeded the specified thresholds 

are unchanged from those provided in 

AD 99–16–01, Amendment 39–11236 

(64 FR 40743, July 28, 1999). The new, 

reduced intervals for the repetitive 

inspections range between 4,000 flight 

cycles/9,000 flight hours (whichever 

occurs first), and 8,900 flight cycles/

20,000 flight hours (whichever occurs 

first), depending on the modification. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4813. 

Clarification of Terminating Action for 

Certain Paragraphs 

We have determined that if the 

inspection in paragraph (g)(4)(ii)(B)(2) of 

the proposed AD was done it would 

terminate the repetitive inspections 

specified in paragraph (g)(2) of this 

proposed AD. We have revised 

paragraph (g)(3)(i) of this proposed AD 

to include accomplishment of the 

inspection in paragraph (g)(4)(ii)(B)(2) 

as a terminating action. We have also 

determined that if the inspection in 

paragraph (g)(4)(ii)(B)(1) of the proposed 

AD was done it would terminate the 

repetitive inspections specified in 

paragraph (g)(2) of this proposed AD. 

We have revised paragraph (g)(3)(ii) of 

this proposed AD to include 

accomplishment of the inspection in 

paragraph (g)(4)(ii)(B)(1) of this AD as a 

terminating action. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A300–57–6017, Revision 04, including 

Appendix 1, dated February 4, 2011. 

This service information describes 

procedures for repetitive inspections of 

certain bolt holes where parts of the 

MLG are attached to the wing rear spar, 

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 of this NPRM. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Changes to AD 99–16–01, Amendment 

39–11236 (64 FR 40743, July 28, 1999) 

This proposed AD would retain all 

the requirements of AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, 

July 28, 1999). Since AD 99–16–01 was 

issued, the AD format has been revised, 

and certain paragraphs have been 

rearranged. As a result, the 

corresponding paragraph identifiers 

have been redesignated in this proposed 

AD, as listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

99–16–01, Amendment 39–11236 

(64 FR 40743, July 

28, 1999) 

Corresponding 

requirement in this 

proposed AD 

paragraph (a) paragraph (g)(1) 

paragraph (b) paragraph (g)(2) 

paragraph (c) paragraph (g)(3) 

paragraph (d) paragraph (g)(4) 

paragraph (e) paragraph (g)(5) 

paragraph (f) paragraph (g)(6) 

Certain notes that appeared in AD 99– 

16–01, Amendment 39–11236 (64 FR 

40743, July 28, 1999), were either 

removed due to the revised AD format 

or converted to regulatory text in this 

proposed AD. 

• Notes 1, 6, and 7 of AD 99–16–01 

have been removed from this proposed 

AD. Due to the revised AD format, 

certain information in these notes is 

now included in the AD template. 

• The content of Note 2 of AD 99–16– 

01 is regulatory in nature; therefore, we 

have included that information in 

paragraph (k)(1) of this proposed AD. 

• The content of Note 3 of AD 99–16– 

01 has been redesignated as Note 1 to 

paragraph (g) in this proposed AD. 

• The content of Note 4 of AD 99–16– 

01 is regulatory in nature; therefore, we 

have included that information in 

paragraph (g)(2)(ii) of this proposed AD. 

• The content of Note 5 of AD 99–16– 

01 is regulatory in nature; therefore, we 

have included that information in 

paragraph (k)(3) of this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 71 airplanes of U.S. registry. 

The actions required by AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, 

July 28, 1999), and retained in this 

proposed AD, take about 226 workhours per product, at an average labor 

rate of $85 per work-hour. Required 

parts cost about $0 per product. Based 

on these figures, the estimated cost of 

the actions that are required by AD 99– 

16–01 is $19,210 per product, per 

inspection cycle. 

We also estimate that it would take 

about 226 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $1,363,910, or $19,210 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 


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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 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 this 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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) 

99–16–01, Amendment 39–11236 (64 

FR 40743, July 28, 1999), and adding the 

following new AD: 

Airbus: Docket No. FAA–2015–4813; 

Directorate Identifier 2013–NM–161–AD. 

(a) Comments Due Date 

We must receive comments by January 4, 

2016. 

(b) Affected ADs 

This AD replaces AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, July 28, 

1999). 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, and B4–622 airplanes; 

Model A300 B4–605R and B4–622R 

airplanes; Model A300 F4–605R airplanes; 

and Model A300 C4–605R Variant F 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by the results of a 

full-scale fatigue test when cracking was 

found on the rear spar of the wing, and the 

subsequent determination that the risk of 

such cracking is higher than initially 

determined. We are issuing this AD to detect 

and correct cracking of the rear spar of the 

wing, which could result in reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections and Corrective 

Actions 

This paragraph restates the requirements of 

paragraphs (a), (b), (c), (d), (e), and (f) of AD 

99–16–01, Amendment 39–11236 (64 FR 

40743, July 28, 1999), with revised service 

information and reduced thresholds and 

repetitive intervals, for Airbus Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R Variant 

F airplanes; manufacturer serial numbers 

(MSNs) 252 through 553 inclusive; except 

those airplanes on which Airbus 

Modification 07601 has been accomplished 

prior to delivery. 

(1) Perform a high frequency eddy current 

(HFEC) rototest inspection to detect cracks in 

certain bolt holes where the main landing 

gear (MLG) forward pick-up fitting and MLG 

rib 5 aft are attached to the rear spar, in 

accordance with Airbus Service Bulletin 

A300–57–6017, Revision 01, including 

Appendix 1, dated July 25, 1994; or Airbus 

Service Bulletin A300–57–6017, Revision 04, 

including Appendix 1, dated February 24, 

2011. As of the effective date of this AD, only 

Airbus Service Bulletin A300–57–6017, 

Revision 04, including Appendix 1, dated 

February 24, 2011, may be used for the 

actions required by this paragraph. 

(i) For airplanes that have accumulated 

17,300 total landings or less as of November 

9, 1995 (the effective date of AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, July 28, 

1999)): Inspect prior to the accumulation of 

17,300 total landings, or within 1,500 

landings after November 9, 1995, whichever 

occurs later. 

(ii) For airplanes that have accumulated 

17,301 or more total landings, but less than 

19,300 total landings as of November 9, 1995 

(the effective date of AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, July 28, 

1999)): Inspect within 1,500 landings after 

November 9, 1995. 

(iii) For airplanes that have accumulated 

19,300 or more total landings as of November 

9, 1995 (the effective date of AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, July 28, 

1999)): Inspect within 750 landings after 

November 9, 1995 (the effective date of AD 

99–16–01, Amendment 39–11236 (64 FR 

40743, July 28, 1999)): 

(2) If no crack is found during the 

inspection required by paragraph (g)(1) of 

this AD, repeat that inspection thereafter at 

the time specified in either paragraph (g)(2)(i) 

or (g)(2)(ii) of this AD, as applicable. 

(i) For airplanes on which Airbus 

Modification 07716 (as specified in Airbus 

Service Bulletin A300–57–6020) has not been 

accomplished, inspect at the time specified 

in paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this 

AD, as applicable. 

(A) For airplanes having MSNs 465 

through 553 inclusive: Repeat the inspection 

at intervals not to exceed 13,000 landings, 

until the inspection required by paragraph 

(g)(4)(ii)(A)(1) of this AD has been 

accomplished. 

(B) For airplanes having MSN 252 through 

464 inclusive: Repeat the inspection at 

intervals not to exceed 8,400 landings, until 

the inspection required by paragraph 

(g)(4)(ii)(A)(2) of this AD has been 

accomplished. 

(ii) For airplanes on which Airbus 

Modification 07716 has been accomplished, 

inspect at the time specified in either 

paragraph (g)(2)(ii)(A) or (g)(2)(ii)(B) of this 

AD, as applicable. 

(A) For airplanes having MSNs 465 

through 553 inclusive: Repeat the inspection 

at intervals not to exceed 11,800 landings, 

until the inspection required by paragraph 

(g)(4)(i)(B) of this AD has been accomplished. 

(B) For airplanes having MSNs 252 through 

464 inclusive: Repeat the inspection within 

10,700 landings following the initial 

inspection required by paragraph (g)(1) of 

this AD, and thereafter at intervals not to 

exceed 7,500 landings, until the inspection 

required by paragraph (g)(4)(ii)(B)(2) has been 

accomplished. 

(3) If any crack is found during the 

inspection required by either paragraph (g)(1) 

or (g)(2) of this AD, prior to further flight, 


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accomplish the requirements of either 

paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as 

applicable. 

(i) For airplanes on which Airbus 

Modification 07716 has not been 

accomplished: Oversize the bolt hole by 1⁄32

inch and repeat the HFEC inspection 

required by paragraph (g)(1) of this AD, in 

accordance with Airbus Service Bulletin 

300–57–6017, Revision 01, including 

Appendix 1, dated July 25, 1994. After 

accomplishing the oversizing and HFEC 

inspection, repeat the inspection, as required 

by paragraph (g)(2) of this AD, at the 

applicable schedule specified in that 

paragraph, until the inspection required by 

paragraph (g)(4)(ii)(B)(1) or (g)(4)(ii)(B)(2) of 

this AD has been accomplished. 

(A) If no cracking is detected, install the 

second oversize bolt in accordance with 

Airbus Service Bulletin 300–57–6017, 

Revision 01, including Appendix 1, dated 

July 25, 1994. 

(B) If any cracking is detected, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

FAA, Transport Airplane Directorate. 

(ii) For airplanes on which Airbus 

Modification 07716 has been accomplished: 

Repair in accordance with a method 

approved by the Manager, International 

Branch, ANM–116. After repair, repeat the 

inspections as required by paragraph (g)(2) of 

this AD at the applicable schedule specified 

in that paragraph, until the inspection 

required by paragraph (g)(4)(ii)(B)(1) or 

(g)(4)(ii)(B)(2) of this AD has been 

accomplished. 

(4) Perform an ultrasonic inspection to 

detect cracks in certain bolt holes where the 

MLG forward pick-up fitting and MLG rib 5 

aft are attached to the rear spar, in 

accordance with Airbus Service Bulletin 

A300–57–6017, Revision 03, dated November 

19, 1997; or Revision 04, including Appendix 

1, dated February 24, 2011; at the time 

specified in paragraph (g)(4)(i) or (g)(4)(ii) of 

this AD, as applicable. As of the effective 

date of this AD, only Airbus Service Bulletin 

A300–57–6017, Revision 04, including 

Appendix 1, dated February 24, 2011, may be 

used for the actions in this paragraph. 

(i) For airplanes not inspected prior to 

September 1, 1999 (the effective date of AD 

99–16–01, Amendment 39–11236 (64 FR 

40743, July 28, 1999)), as specified in Airbus 

Service Bulletin A300–57–6017, dated 

November 22, 1993; or Revision 01, 

including Appendix 1, dated July 25, 1994: 

Inspect at the time specified in paragraph 

(g)(4)(i)(A), (g)(4)(i)(B), or (g)(4)(i)(C) of this 

AD, as applicable. Accomplishment of this 

inspection terminates the requirements of 

paragraph (g)(1) of this AD. 

(A) For airplanes that have accumulated 

17,300 total landings or fewer as of the 

effective date of this AD: Inspect prior to the 

accumulation of 17,300 total landings, or 

within 1,500 landings after September 1, 

1999 (the effective date of AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, July 28, 

1999)), whichever occurs later. 

(B) For airplanes that have accumulated 

17,301 total landings or more but fewer than 

19,300 total landings as of September 1, 1999 

(the effective date of AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, July 28, 

1999)): Inspect within 1,500 landings after 

September 1, 1999 (the effective date of AD 

99–16–01). 

(C) For airplanes that have accumulated 

19,300 total landings or more as of September 

1, 1999 (the effective date of AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, July 28, 

1999)): Inspect within 750 landings after 

September 1, 1999 (the effective date of AD 

99–16–01). 

(ii) For airplanes on which an HFEC 

inspection was performed prior to September 

1, 1999 (the effective date of AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, July 28, 

1999)), in accordance with the requirements 

of paragraph (g)(1) of this AD, or in 

accordance with Airbus Service Bulletin 

A300–57–6017, dated November 22, 1993: 

Inspect at the time specified in paragraph 

(g)(4)(ii)(A) or (g)(4)(ii)(B) of this AD, as 

applicable. 

(A) If no cracking was detected during any 

HFEC inspection accomplished prior to 

September 1, 1999 (the effective date of AD 

99–16–01, Amendment 39–11236 (64 FR 

40743, July 28, 1999)), and if Airbus 

Modification 07716 has not been 

accomplished: Inspect at the time specified 

in paragraph (g)(4)(ii)(A)(1) or (g)(4)(ii)(A)(2) 

of this AD, as applicable. 

(1) For airplanes having MSNs 465 through 

553 inclusive: Inspect within 13,000 landings 

after the most recent HFEC inspection, and 

thereafter at intervals not to exceed 8,900 

landings. Accomplishment of this inspection 

constitutes terminating action for the 

repetitive inspection requirement of 

paragraph (g)(2)(i)(A) of this AD. 

(2) For airplanes having MSNs 252 through 

464 inclusive: Inspect within 8,400 landings 

after the most recent HFEC inspection, and 

thereafter at intervals not to exceed 5,500 

landings. Accomplishment of this inspection 

constitutes terminating action for the 

repetitive inspection requirement of 

paragraph (g)(2)(i)(B) of this AD. 

(B) If any cracking was detected during any 

HFEC inspection performed prior to the 

effective date of this AD, regardless of the 

method of repair, or if Airbus Modification 

07716 has been accomplished: Inspect at the 

time specified in paragraph (g)(4)(ii)(B)(1) or 

(g)(4)(ii)(B)(2) of this AD, as applicable. 

(1) For airplanes having MSNs 465 through 

553 inclusive: Inspect within 11,800 landings 

after the most recent HFEC inspection, and 

thereafter at intervals not to exceed 8,200 

landings. Accomplishment of this inspection 

constitutes terminating action for the 

repetitive inspection requirement of 

paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as 

applicable. 

(2) For airplanes having MSNs 252 through 

464 inclusive: Inspect within 10,700 landings 

after the initial inspection in accordance with 

paragraph (g)(1) of this AD, or within 7,500 

landings after the most recent HFEC 

inspection, whichever occurs later, and 

thereafter at intervals not to exceed 4,900 

landings. Accomplishment of this inspection 

constitutes terminating action for the 

repetitive inspection requirement of 

paragraph (g)(3)(i) or (g)(3)(ii) of this AD, as 

applicable. 

(5) If no cracking is detected during the 

ultrasonic inspection required by paragraph 

(g)(4)(i) of this AD, repeat that inspection 

thereafter at the time specified in paragraph 

(g)(5)(i) or (g)(5)(ii) of this AD, as applicable, 

until the initial ultrasonic inspection 

required by paragraph (h) of this AD is done. 

(i) For airplanes having MSNs 465 through 

553 inclusive: Repeat the inspection at 

intervals not to exceed 8,900 landings. 

(ii) For airplanes having MSNs 232 through 

464 inclusive: Repeat the inspection at 

intervals not to exceed 5,500 landings. 

(6) If any cracking is detected during any 

inspection performed in accordance with the 

requirements of paragraph (g)(4) or (g)(5) of 

this AD: Prior to further flight, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116; or 

the Direction Ge ́ne ́rale de l’Aviation Civile 

(or its delegated agent); or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

Note 1 to paragraph (g) of this AD: Airbus 

Service Bulletin A300–57–6017, Revision 01, 

including Appendix 1, dated July 25, 1994; 

and Airbus Service Bulletin A300–57–6017, 

Revision 04, including Appendix 1, dated 

February 24, 2011; also reference Airbus 

Service Bulletin A300–57–6020, dated 

November 22, 1993, as an additional source 

of service information for installation of 

oversize studs in the bolt holes. 

(h) New Repetitive Inspections 

At the applicable times specified in 

paragraph 1.B.(5), ‘‘Accomplishment 

Timescale,’’ of Airbus Service Bulletin A300– 

57–6017, Revision 04, including Appendix 1, 

dated February 24, 2011: Do ultrasonic 

inspections to detect cracks in the MLG 

attachment fitting holes on the wing rear 

spar, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6017, Revision 04, 

including Appendix 1, dated February 24, 

2011. Repeat the inspections thereafter at the 

applicable intervals specified in paragraph 

1.B.(5), ‘‘Accomplishment Timescale,’’ of 

Airbus Service Bulletin A300–57–6017, 

Revision 04, including Appendix 1, dated 

February 24, 2011. For airplanes modified as 

specified in Airbus Service Bulletin A300– 

57–6073, the initial inspection threshold is 

counted from the completion date of the 

modification. Clarification of compliance 

time terminology used in table 1, ‘‘Structural 

Inspection Program,’’ of Airbus Service 

Bulletin A300–57–6017, Revision 04, 

including Appendix 1, dated February 24, 

2011, is provided in paragraphs (h)(1) 

through (h)(4) of this AD. Accomplishment of 

the initial inspection terminates the 

repetitive inspections required by paragraph 

(g)(5) of this AD. 

(1) For pre-Airbus Modification 07716 or 

pre-Airbus Modification 11440 airplanes: 

(i) The term ‘‘flight cycles’’ in the 

‘‘Inspection Threshold’’ column is total flight 

cycles accumulated by the airplane. 

(ii) The term ‘‘flight hours’’ in the 

‘‘Inspection Threshold’’ column is total flight 

hours accumulated by the airplane. 

(2) For post-Airbus Modification 07716 

airplanes: 

(i) The term ‘‘flight cycles’’ in the 

‘‘Inspection Threshold’’ column is total flight 

cycles accumulated by the airplane. 


wgreen on DSK2VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 221 / Tuesday, November 17, 2015 / Proposed Rules 71755 

1Collection of Connected Entity Data from 

Regional Transmission Organizations and 

Independent System Operators, 152 FERC ¶ 61,219 

(2015). 

(ii) The term ‘‘flight hours’’ in the 

‘‘Inspection Threshold’’ column is total flight 

hours accumulated by the airplane. 

(3) For post-Airbus Modification 11440 

(Airbus Service Bulletin A300–57–6073) 

airplanes: 

(i) The term ‘‘flight cycles’’ in the 

‘‘Inspection Threshold’’ column is flight 

cycles accumulated by the airplane after the 

modification was done. 

(ii) The term ‘‘flight hours’’ in the 

‘‘Inspection Threshold’’ column is flight 

hours accumulated by the airplane after the 

modification was done. 

(4) For post-Airbus Modification 07601 

airplanes: 

(i) The term ‘‘flight cycles’’ in the 

‘‘Inspection Threshold’’ column is total flight 

cycles accumulated by the airplane. 

(ii) The term ‘‘flight hours’’ in the 

‘‘Inspection Threshold’’ column is total flight 

hours accumulated by the airplane. 

(i) Repairs 

If any crack is found during any inspection 

required by paragraph (h) of this AD: Before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

(j) Repair Not Terminating Action 

Accomplishment of any repair as required 

by paragraph (i) of this AD is not terminating 

action for the repetitive inspections required 

by paragraph (g) or (h) of this AD. 

(k) 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 any of the 

following service information: 

(1) Airbus Service Bulletin A300–57–6017, 

dated November 22, 1993, which is not 

incorporated by reference in this AD. 

(2) Airbus Service Bulletin A300–57–6017, 

Revision 01, including Appendix 1, dated 

July 25, 1994, which was incorporated by 

reference in AD 95–20–02, Amendment 39– 

9380 (60 FR 52618, October 10, 1995). 

(3) Airbus Service Bulletin A300–57–6017, 

Revision 02, dated January 14, 1997, 

including Appendix 1, dated July 25, 1994, 

which is not incorporated by reference in this 

AD. 

(4) Airbus Service Bulletin A300–57–6017, 

Revision 03, dated November 19, 1997, 

including Appendix 1, which was 

incorporated by reference in AD 99–16–01, 

Amendment 39–11236 (64 FR 40743, July 28, 

1999). 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–2125; fax: 425–227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

99–16–01, Amendment 39–11236 (64 FR 

40743, July 28, 1999), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0180, dated 

August 9, 2013, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov 

searching for and locating Docket No. FAA– 

2015–4813. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

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. 

Issued in Renton, Washington, on 

November 4, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28892 Filed 11–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 35 

[Docket No. RM15–23–000] 

Collection of Connected Entity Data 

from Regional Transmission 

Organizations and Independent 

System Operators 

AGENCY: Federal Energy Regulatory 

Commission. DOE. 

ACTION: Order Granting Motion for 

Technical Conference and Request to 

Postpone Comment Deadline. 

SUMMARY: In this order, the Federal 

Energy Regulatory Commission 

(Commission) grants a motion for a 

technical conference and request to 

postpone comment deadline that was 

filed in response to the Notice of 

Proposed Rulemaking for the Collection 

of Connected Entity Data from Regional 

Transmission Organizations and 

Independent System Operators (NOPR) 

that Commission issued on September 

17, 2015.1 The Commission directs staff 

to convene a technical conference on 

December 8, 2015 and postpones the 

due date for comments on the NOPR 

until January 22, 2016, 45 days after the 

technical conference. 

DATES: The technical conference will be 

held on December 8, 2015 and NOPR 

comments will be due January 22, 2016. 

FOR FURTHER INFORMATION CONTACT: 

David Pierce (Technical Information), 

Office of Enforcement, Federal Energy 

Regulatory Commission, 888 First Street 

NE., Washington, DC 20426, (202) 502– 

6454 david.pierce@ferc.gov. 

Kathryn Kuhlen (Legal Information), 

Office of Enforcement, Federal Energy 

Regulatory Commission, 888 First Street 

NE., Washington, DC 20426, (202) 502– 

6855 kathryn.kuhlen@ferc.gov. 

SUPPLEMENTARY INFORMATION: 

Before Commissioners: Norman C. 

Bay, Chairman; Cheryl A. LaFleur, Tony 

Clark, and Colette D. Honorable. 

Collection of Connected Entity Data 

from Regional Transmission 

Organizations and Independent System 

Operators 

Docket No. RM15–23–000 


wgreen on DSK2VPTVN1PROD with PROPOSALS