This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

5056 

Vol. 81, No. 20 

Monday, February 1, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0451; Directorate 

Identifier 2013–NM–253–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) 2004–23– 

20 for certain Airbus Model A300 series 

airplanes and Model A300 B4–601, 

A300 B4–603, A300 B4–620, A300 B4– 

622, A300 B4–605R, A300 B4–622R, 

A300 F4–605R, and C4–605R Variant F 

airplanes. AD 2004–23–20 currently 

requires, for certain airplanes, repetitive 

inspections for cracking around certain 

attachment holes, installation of new 

fasteners for certain airplanes, and 

follow-on corrective actions if 

necessary. AD 2004–23–20 also requires 

modifying certain fuselage frames, 

which terminates certain repetitive 

inspections. Since we issued AD 2004– 

23–20, we received a report indicating 

that the material used to manufacture 

the upper frame feet was changed and 

negatively affected the fatigue life of the 

frame feet. This proposed AD would 

reduce the compliance times for the 

initial inspection and the inspection 

intervals. This proposed AD would also 

expand the applicability and require an 

additional repair on certain airplanes 

that have been modified. We are 

proposing this AD to prevent cracking of 

the center section of the fuselage, which 

could result in a ruptured frame foot 

and reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by March 17, 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 NPRM, 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–2016– 

0451; 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, 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–2016–0451; Directorate Identifier 

2013–NM–253–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 November 10, 2004, we issued AD 

2004–23–20, Amendment 39–13875 (69 

FR 68779, November 26, 2004) for all 

Airbus Model A300 series airplanes and 

Model A300 B4–601, A300 B4–603, 

A300 B4–620, A300 B4–622, A300 B4– 

605R, A300 B4–622R, A300 F4–605R 

and A300 C4–605R Variant F airplanes. 

(That AD superseded AD 2001–06–10, 

Amendment 39–12157 (66 FR 17490, 

April 2, 2001)). AD 2004–23–20 requires 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 2004–23–20, 

Amendment 39–13875 (69 FR 68779, 

November 26, 2004) we received a 

report indicating that a change in 

material for manufacturing the frame 

feet for certain airplanes negatively 

impacted the fatigue life of the frame 

feet. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0295, dated December 

11, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for Airbus Model 

A300 B4–601, A300 B4–603, A300 B4– 

620, A300 B4–622, A300 B4–605R, 

A300 B4–622R, A300 F4–605R, and 

A300 C4–605R Variant F airplanes. The 

MCAI states: 

During a scheduled inspection of the 

fuselage frame feet of an in-service A300–600 

aeroplane, cracks were observed in Frame 

(FR) 43, FR 44, FR 45 and FR 46 between 

stringer (STGR) 24 and STGR 30. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 


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To address this unsafe condition, 

[Direction Generale de l’Aviation Civile] 

DGAC France issued [an] AD * * * to 

require repetitive inspections of the affected 

frames and stringers on both sides of the 

fuselage and, depending on findings, repairs, 

as specified in Airbus Service Bulletin (SB) 

A300–53–6122. 

Subsequently, DGAC France issued AD F– 

2004–002 [http://ad.easa.europa.eu/ad/F2004-002] (EASA approval 2003–2108) 

[which corresponds to FAA AD 2004–23–20, 

Amendment 39–13875 (69 FR 68779, 

November 26, 2004)], retaining the 

requirements of [an] AD * * * and required 

the embodiment of Airbus SB A300–53–6125 

(Airbus modification 12168) in order to 

improve the life of the frame foot attachment. 

Since DGAC France AD F–2004–002 was 

issued, a fleet survey and updated Fatigue 

and Damage Tolerance analyses were 

performed in order to substantiate the second 

A300–600 Extended Service Goal (ESG2) 

exercise. 

It was highlighted that the frame feet 

material change from 2024T3511 (A300B4) to 

7175T7351 (A300–600) had an impact on the 

frame feet fatigue life duration. Airbus SB 

A300–53–6122 was revised accordingly to 

decrease the inspection thresholds and 

intervals. Subsequent SB revision introduced 

a second structural modification point 

(SMP2) for aeroplanes that embody Airbus 

SB A300–53–6125 (modification 12168). 

For the reasons described above, this new 

[EASA] AD retains the requirements of DGAC 

France AD F–2004–002, which is 

superseded, but requires those actions within 

the new thresholds and intervals as specified 

in Revision 04 of Airbus SB A300–53–6122. 

The retained requirements include 

rototest inspections for cracking in the 

area surrounding the frame feet 

attachment holes between fuselage FR 

41 and FR 46 from stringers 24 to 28 on 

the left and right sides, and related 

investigative and corrective action if 

necessary. The related investigative 

actions include additional rotating 

probe inspections of the adjacent holes. 

The corrective actions include reaming 

out cracks, cold working fastener holes, 

and installing oversized fasteners, or 

repair. This proposed AD also expands 

the applicability to include airplanes on 

which Airbus Modification 12168 was 

done. 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–2016– 

0451. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A300–53–6122, Revision 04, dated 

February 27, 2012. The service 

information describes procedures for the 

repetitive inspections of certain frame 

feet attachment holes for cracks, 

installation of new fasteners, and repair 

of cracked areas. 

In addition, Airbus has issued Service 

Bulletin A300–53–6125, Revision 01, 

dated June 13, 2003. The service 

information provides compliance times 

for certain airplanes to do the proposed 

modification. 

Airbus has also issued Service 

Bulletin A300–53–6125, Revision 04, 

dated March 17, 2015. The service 

information describes procedures for the 

modification of certain upper frame feet 

fittings. 

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. 

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 2004–23–20, 

Amendment 39–13875 (69 FR 68779, 

November 26, 2004) 

This proposed AD would retain all 

requirements of AD 2004–23–20, 

Amendment 39–13875 (69 FR 68779, 

November 26, 2004). Since AD 2004– 

23–20 was issued the AD format has 

been revised, and certain paragraphs 

have been rearranged. As a result, the 

corresponding paragraph designators 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH DESIGNATORS

Requirement in 

AD 2004–23–20, 

Amendment 

39–13875 

(69 FR 68779, 

November 26, 2004) 

Corresponding 

requirement in 

this proposed 

AD 

paragraph (f) paragraph (g). 

paragraph (g) paragraph (h). 

paragraph (h) paragraph (i). 

paragraph (i) paragraph (j). 

paragraph (j) paragraph (k). 

We have converted ‘‘TABLE 1.— 

SERVICE INFORMATION’’ in AD 2004– 

23–20, Amendment 39–13875 (69 FR 

68779, November 26, 2004) to text in 

paragraphs (j)(3)(i) and (j)(3)(ii) of this 

proposed AD for formatting purposes 

only. 

We have also moved the service 

information acceptable for compliance if 

previously done from ‘‘TABLE 1.— 

SERVICE INFORMATION’’ in AD 2004– 

23–20, Amendment 39–13875 (69 FR 

68779, November 26, 2004) to paragraph 

(r)(2) of this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 65 airplanes of U.S. registry. 

The actions that are required by AD 

2004–23–20, Amendment 39–13875 (69 

FR 68779, November 26, 2004), and 

retained in this proposed AD take about 

90 work-hours per product, at an 

average labor rate of $85 per work-hour. 

Required parts cost about $4,000 per 

product. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2004–23–20 is $11,650 

per product. 

We also estimate that it would take up 

to 109 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost up to $6,070 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $996,775, or 

$15,335 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. 

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 


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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. 

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) 

2004–23–20, Amendment 39–13875 (69 

FR 68779, November 26, 2004), and 

adding the following new AD: 

Airbus: Docket No. FAA–2016–0451; 

Directorate Identifier 2013–NM–253–AD. 

(a) Comments Due Date 

We must receive comments by March 17, 

2016. 

(b) Affected ADs 

This AD replaces AD 2004–23–20, 

Amendment 39–13875 (69 FR 68779, 

November 26, 2004). 

(c) Applicability 

This AD applies to Airbus Model A300 B2– 

1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, 

and B4–203 airplanes; and Model A300 B4– 

601, A300 B4–603, A300 B4–620, A300 B4– 

622, A300 B4–605R, A300 B4–622R, A300 

F4–605R and A300 C4–605R Variant F 

airplanes; certificated in any category, all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report 

indicating that the material used to 

manufacture the upper frame feet was 

changed and negatively affected the fatigue 

life of the frame feet. We are issuing this AD 

to prevent cracking of the center section of 

the fuselage, which could result in a ruptured 

frame foot and reduced structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections 

This paragraph restates the requirements of 

paragraph (f) of AD 2004–23–20, Amendment 

39–13875 (69 FR 68779, November 26, 2004), 

with revised service information. For Model 

A300 B4–600 and A300 B4–600R series 

airplanes, and Model A300 C4–605R Variant 

F and A300 F4–605R airplanes, except those 

airplanes modified by Airbus Modification 

12168: Perform a high-frequency eddycurrent or rototest inspection to detect 

cracking in the area surrounding the frame 

feet attachment holes between fuselage 

frames (FR) 41 and FR 46 from stringers 24 

to 28, left-and right-hand sides, in 

accordance with Airbus Service Bulletin 

A300–53–6122, dated February 9, 2000; or 

the Accomplishment Instructions of Airbus 

Service Bulletin A300–53–6122, Revision 04, 

dated February 27, 2012; at the applicable 

time specified in paragraph (g)(1) or (g)(2) of 

this AD. Accomplishing an inspection 

required by paragraph (m) of this AD 

terminates the inspections required by this 

paragraph. 

(1) For airplanes on which Task 53–15–54 

in Maintenance Review Board Document 

(MRBD), Revision 3, dated April 1998, has 

not been accomplished as of May 7, 2001 (the 

effective date of AD 2001–06–10, 

Amendment 39–12157 (66 FR 17490, April 2, 

2001)): Perform the inspection at the later of 

the times specified in paragraphs (g)(1)(i) and 

(g)(1)(ii) of this AD. 

(i) Prior to the accumulation of the total 

flight-cycle or flight-hour threshold, 

whichever occurs first, specified in 

paragraph 1.E. (‘‘Compliance’’) of Airbus 

Service Bulletin A300–53–6122, dated 

February 9, 2000; or 

(ii) Within the applicable grace period 

specified in paragraph 1.E. (‘‘Compliance’’) of 

Airbus Service Bulletin A300–53–6122, 

dated February 9, 2000. 

(2) For airplanes on which Task 53–15–54 

in the MRBD, Revision 3, dated April 1998, 

has been accomplished as of May 7, 2001 (the 

effective date of AD 2001–06–10, 

Amendment 39–12157 (66 FR 17490, April 2, 

2001)): Perform the next repetitive inspection 

at the later of the times specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. 

(i) Within the flight-cycle or flight-hour 

interval, whichever occurs first, specified in 

paragraph 1.E. (‘‘Compliance’’) of Airbus 

Service Bulletin A300–53–6122, dated 

February 9, 2000, following the latest 

inspection accomplished as specified in 

MRBD, Revision 3, dated April 1998; or 

(ii) Within the grace period specified in 

paragraph 1.E. (‘‘Compliance’’) of Airbus 

Service Bulletin A300–53–6122, dated 

February 9, 2000. 

(h) Retained Installation of Fasteners and 

Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (g) of AD 2004–23–20, 

Amendment 39–13875 (69 FR 68779, 

November 26, 2004), with revised service 

information. For airplanes on which no 

cracking is detected during the inspection 

required by paragraph (g) of this AD, prior to 

further flight, install new fasteners as 

applicable, in accordance with Airbus 

Service Bulletin A300–53–6122, dated 

February 9, 2000; or the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6122, Revision 04, dated February 27, 

2012; and repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed the applicable 

intervals specified in paragraph 1.E. 

(‘‘Compliance’’) of Airbus Service Bulletin 

A300–53–6122, dated February 9, 2000; until 

the actions required by paragraph (j) or (o) of 

this AD have been done or the initial 

inspection required by paragraph (m) of this 

AD is done. 

(i) Retained Corrective Actions 

This paragraph restates the requirements of 

paragraph (h) of AD 2004–23–20, 

Amendment 39–13875 (69 FR 68779, 

November 26, 2004), with revised service 

information. For airplanes on which cracking 

is detected during any inspection required by 

paragraph (g) of this AD: Prior to further 

flight, except as required by paragraph (k) of 

this AD, accomplish corrective actions (e.g., 

performing rotating probe inspections, 

reaming out cracks, cold working fastener 

holes, and installing oversized fasteners) in 

accordance with Airbus Service Bulletin 

A300–53–6122, dated February 9, 2000; or 

the Accomplishment Instructions of Airbus 

Service Bulletin A300–53–6122, Revision 04, 

dated February 27, 2012. Repeat the 

inspection required by paragraph (g) of this 

AD thereafter at intervals not to exceed the 

applicable intervals specified in paragraph 

1.E. (‘‘Compliance’’) of Airbus Service 

Bulletin A300–53–6122, dated February 9, 

2000; until the actions required by paragraph 

(j) or (o) of this AD have been done, or the 

initial inspection required by paragraph (m) 

of this AD is done. 

(j) Retained Modification: Model A300 Series 

Airplanes 

This paragraph restates the requirements of 

paragraph (i) of AD 2004–23–20, Amendment 

39–13875 (69 FR 68779, November 26, 2004), 

for certain airplanes, with no changes. For 

Model A300 series airplanes: Within the 

compliance times specified in paragraph 1.E. 

(‘‘Compliance’’) of Airbus Service Bulletin 

A300–53–0271, Revision 03, dated June 13, 

2003, modify the fuselage frames, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–0271, Revision 03, dated June 13, 2003. 

For airplanes that have exceeded their design 

service goal, as specified in NOTE (01) of 

paragraph 1.E. (‘‘Compliance’’) of Airbus 

Service Bulletin A300–53–0271, Revision 03, 

dated June 13, 2003; this AD requires 

compliance within the earlier of the flightcycle and flight-hour grace periods specified 

in Airbus Service Bulletin A300–53–0271, 

Revision 03, dated June 13, 2003. 


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(k) Retained Exceptions to Service Bulletin 

Procedures 

This paragraph restates the requirements of 

paragraph (j) of AD 2004–23–20, Amendment 

39–13875 (69 FR 68779, November 26, 2004), 

with specific delegation approval language. 

During any inspection required by 

paragraphs (g), (h), (i), or (j) of this AD, if the 

applicable service information specified in 

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

specifies to contact the manufacturer for 

appropriate instructions: Before further 

flight, perform all applicable corrective 

actions in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the Direction Generale 

de l’Aviation Civile (DGAC) (or its delegated 

agent); or the European Aviation Safety 

Agency (EASA); or Airbus’s EASA Design 

Organization Approval (DOA). 

(l) New Definition for This AD: Average 

Flight Time (AFT) 

For the purpose of this AD, use the 

parameters specified in paragraphs (l)(1), 

(l)(2), and (l)(3) of this AD to determine the 

applicable AFT for the actions required by 

paragraph (m) and compliance times required 

by paragraph (n) of this AD. 

(1) The initial inspection compliance time, 

as the total accumulated flight hours counted 

from take-off to touch-down, divided by the 

total accumulated flight cycles as of the 

effective date of this AD. 

(2) The first repetitive inspection interval, 

as the total accumulated flight hours divided 

by the total accumulated flight cycles at the 

time of the inspection. 

(3) The second inspection interval and 

subsequent, as the flight hours divided by the 

flight cycles between the last two 

inspections. 

(m) New Requirements of This AD: 

Inspections and Corrective Actions 

(1) At the applicable time specified in 

paragraph (n)(1) of this AD, do a rotating 

probe inspection for discrepancies of the 

frame feet attachment holes from FR 41 

through FR 46, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–6122, Revision 04, 

dated February 27, 2012. Repeat the 

inspections thereafter at intervals not to 

exceed those specified in paragraph (n)(2) of 

this AD. Accomplishment of this inspection 

terminates the inspections required by 

paragraph (g)(2) of this AD. 

(2) If any discrepancy (e.g., cracking or 

damage) is found during any inspection 

required by paragraph (m)(1) of this AD, 

before further flight, do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6122, Revision 04, dated February 27, 

2012; except where Airbus Service Bulletin 

A300–53–6122, Revision 04, dated February 

27, 2012, specifies to contact Airbus, before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA; or Airbus’s EASA 

DOA. 

(3) Corrective actions, as required by 

paragraph (m)(2) of this AD, do not constitute 

terminating action for the repetitive 

inspections required by paragraph (m)(1) of 

this AD. 

(n) Compliance Times for Initial and 

Repetitive Inspections 

(1) Do the initial rotating probe inspection 

required by paragraph (m)(1) of this AD at the 

applicable times specified in paragraphs 

(n)(1)(i), (n)(1)(ii), and (n)(1)(iii) of this AD; 

or within 1,000 flight cycles after the 

effective date of this AD; whichever occurs 

later. 

(i) For airplanes on which the modification 

specified in Airbus Service Bulletin A300– 

53–6125 has not been done as of the effective 

date of this AD: At the applicable times 

specified in paragraph (n)(1)(i)(A) or 

(n)(1)(i)(B) of this AD. 

(A) If the AFT is greater than 1.5 flight 

hours/flight cycles: Within 14,800 flight 

hours or 6,800 flight cycles, whichever 

occurs first, since the airplane’s first flight. 

(B) If the AFT is less than or equal to 1.5 

flight hours/flight cycles: Within 11,100 

flight hours or 7,400 flight cycles, whichever 

occurs first, since the airplane’s first flight. 

(ii) For airplanes on which the 

modification specified in Airbus Service 

Bulletin A300–53–6125 has been done as of 

the effective date of this AD, except as 

provided by paragraph (n)(1)(iii) of this AD: 

At the applicable times specified in 

paragraph (n)(1)(ii)(A) or (n)(1)(ii)(B) of this 

AD. 

(A) If the AFT is greater than 1.5 flight 

hours/flight cycles: Within 56,400 flight 

hours or 26,100 flight cycles, whichever 

occurs first, after doing the modification 

specified in Airbus Service Bulletin A300– 

53–6125. 

(B) If the AFT is less than or equal to 1.5 

flight hours/flight cycles: Within 42,300 

flight hours or 28,200 flight cycles, 

whichever occurs first, after doing the 

modification specified in Airbus Service 

Bulletin A300–53–6125. 

(iii) For airplanes on which the additional 

modification required by paragraph (p) of 

this AD has been done: At the applicable 

times in paragraph (n)(1)(iii)(A) or 

(n)(1)(iii)(B) of this AD. 

(A) If the AFT is greater than 1.5 flight 

hours/flight cycles: Within 69,400 flight 

hours or 32,100 flight cycles, whichever 

occurs first, after doing the modification 

specified in Airbus Service Bulletin A300– 

53–6125. 

(B) If the AFT is less than or equal to 1.5 

flight hours/flight cycles: Within 52,000 

flight hours or 34,700 flight cycles, 

whichever occurs first, after doing the 

modification specified in Airbus Service 

Bulletin A300–53–6125. 

(2) Do the repetitive rotating probe 

inspections required by paragraph (m)(1) of 

this AD at intervals not to exceed those 

specified in paragraph (n)(2)(i) or (n)(2)(ii) of 

this AD, as applicable. 

(i) If the AFT is greater than 1.5 flight 

hours/flight cycles: 7,800 flight hours or 

3,600 flight cycles, whichever occurs first. 

(ii) If the AFT is less than or equal to 1.5 

flight hours/flight cycles: 5,800 flight hours 

or 3,900 flight cycles, whichever occurs first. 

(o) New Requirement of This AD: 

Modification for Model A300 B4–601, A300 

B4–603, A300 B4–620, A300 B4–622, A300 

B4–605R, A300 B4–622R, A300 F4–605R and 

A300 C4–605R Variant F Airplanes 

(1) For Model A300 B4–601, A300 B4–603, 

A300 B4–620, A300 B4–622, A300 B4–605R, 

A300 B4–622R, A300 F4–605R and A300 C4– 

605R Variant F airplanes, except those 

modified in production before the effective 

date of this AD by Airbus Modification 12168 

or those on which the modification (i.e., 

reinforcement of the upper frame feet fittings) 

specified in the service information 

identified in paragraph (p)(1)(i), (p)(1)(ii), or 

(p)(1)(iii) of this AD has been done before the 

effective date of this AD: At the applicable 

time specified in paragraph (o)(1)(i) or 

(o)(1)(ii) of this AD: Reinforce the upper 

frame feet fittings, including doing all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–6125, Revision 04, 

dated March 17, 2015, except where Airbus 

Service Bulletin A300–53–6125, Revision 04, 

dated March 17, 2015, specifies to contact 

Airbus, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. Do all applicable 

related investigative and corrective actions 

before further flight. 

(i) For airplanes with an AFT greater than 

1.5 flight hours/flight cycles as of the 

effective date of this AD: At the later of the 

times in paragraphs (o)(1)(i)(A) and 

(o)(1)(i)(B) of this AD: 

(A) Within 18,200 flight hours or 8,400 

flight cycles, whichever occurs first, since the 

airplane’s first flight; or 

(B) At the earlier of the times specified in 

paragraphs (o)(1)(i)(B)1 and (o)(1)(i)(B)2 of 

this AD. 

1 Within 1,000 flight cycles after the 

effective date of this AD. 

2 Within the compliance times specified 

in paragraph 1.E. (‘‘Compliance’’) of Airbus 

Service Bulletin A300–53–6125, Revision 01, 

dated June 13, 2003. For airplanes that have 

exceeded their design service goal, as 

specified in NOTE (01) of paragraph 1.E. 

(‘‘Compliance’’) of Airbus Service Bulletin 

A300–53–6125, Revision 01, dated June 13, 

2003; within the earlier of the flight-cycle 

and flight-hour grace periods specified in 

Airbus Service Bulletin A300–53–6125, 

Revision 01, dated June 13, 2003. 

(ii) For airplanes with an AFT less than or 

equal to 1.5 flight hours/flight cycles as of the 

effective date of this AD: At the later of the 

times in paragraphs (o)(1)(ii)(A) and 

(o)(1)(ii)(B) of this AD: 

(A) Within 13,700 flight hours or 9,100 

flight cycles, whichever occurs first, since the 

airplane’s first flight; or 

(B) At the earlier of the times specified in 

paragraphs (o)(1)(ii)(B)1 and (o)(1)(ii)(B)2 of 

this AD. 

1 Within 1,000 flight cycles after the 

effective date of this AD 

2 Within the compliance times specified 

in paragraph 1.E. (‘‘Compliance’’) of Airbus 

Service Bulletin A300–53–6125, Revision 01, 

dated June 13, 2003. For airplanes that have 


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5060 Federal Register / Vol. 81, No. 20 / Monday, February 1, 2016 / Proposed Rules 

exceeded their design service goal, as 

specified in NOTE (01) of paragraph 1.E. 

(‘‘Compliance’’) of Airbus Service Bulletin 

A300–53–6125, Revision 01, dated June 13, 

2003; within the earlier of the flight-cycle 

and flight-hour grace periods specified in 

Airbus Service Bulletin A300–53–6125, 

Revision 01, dated June 13, 2003. 

(2) For the affected Model A300 B4–600 

series airplanes: Accomplishment of the 

modification specified in Airbus Service 

Bulletin A300–53–6125 before the effective 

date of this AD terminates the requirements 

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

(3) For Model A300 B2 and A300 B4 series 

airplanes: Accomplishment of the 

modification specified in Airbus Service 

Bulletin A300–53–6125 terminates certain 

repetitive inspections required by AD 2007– 

04–11, Amendment 39–14943 (72 FR 8604, 

February 27, 2014), i.e., inspections of the 

frame feet holes for frames 41 to 46 (as 

specified in Airbus Service Bulletin A300– 

53–0345) and frames 48 to 54 (as specified 

in Airbus Service Bulletin A300–53–238). 

However, the repetitive inspections of the 

frame foot angle radius (as specified in 

Service Bulletin A300–53–238), which are 

required by AD 2007–04–11, must continue. 

(p) New Requirement of This AD: Additional 

Modification for Certain Airplanes 

(1) For Model A300 B4–601, A300 B4–603, 

A300 B4–620, A300 B4–622, A300 B4–605R, 

A300 B4–622R, A300 F4–605R and A300 C4– 

605R Variant F airplanes modified in 

production before the effective date of this 

AD by Airbus Modification 12168, or 

modified before the effective date of this AD 

by accomplishment of the reinforcement of 

the upper frame feet fittings specified in the 

service information identified in paragraph 

(p)(1)(i), (p)(1)(ii), or (p)(1)(iii) of this AD: 

Within 360 flight cycles prior to reaching the 

applicable compliance time specified in 

paragraph (p)(2)(i) or (p)(2)(ii) of this AD, 

contact the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or EASA; or Airbus’s EASA DOA; for 

modification instructions and within the 

applicable compliance time specified in 

paragraph (p)(2) of this AD, do the 

modification using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. 

(i) Airbus Service Bulletin A300–53–6125, 

dated November 8, 2000. 

(ii) Airbus Service Bulletin A300–53–6125, 

Revision 01, dated June 13, 2003, 

(iii) Airbus Service Bulletin A300–53– 

6125, Revision 02, dated February 25, 2005. 

(2) Do the modification required by 

paragraph (p)(1) of this AD at the applicable 

time specified below. 

(i) For airplanes with an AFT greater than 

1.5 flight hours/flight cycles as of the 

effective date of this AD: Within 32,100 flight 

cycles after the modification was completed. 

(ii) For airplanes with an AFT less than or 

equal to 1.5 flight hours/flight cycles as of the 

effective date of this AD: Within 34,700 flight 

cycles after the modification was completed. 

(q) Modification Is Not Terminating Action 

Accomplishment of the modification 

specified in paragraph (o) or (p) of this AD 

does not constitute terminating action for the 

repetitive inspections required by paragraph 

(m)(1) of this AD. 

(r) Credit for Previous Actions 

(1) For Model A300 B4–600 and B4–600R 

series airplanes, and Model A300 C4–605R 

Variant F and A300 F4–605R airplanes: This 

paragraph provides credit for inspections and 

corrective actions required by paragraphs (g), 

(h), and (i) of this AD, if those actions were 

performed before the effective date of this AD 

using the applicable service information 

specified in paragraphs (r)(1)(i), (r)(1)(ii), and 

(r)(1)(iii) of this AD. 

(i) Airbus Service Bulletin A300–53–6122, 

Revision 01, dated September 5, 2001, which 

is not incorporated by reference in this AD. 

(ii) Airbus Service Bulletin A300–53–6122, 

Revision 02, dated June 17, 2002, which is 

not incorporated by reference in this AD. 

(iii) Airbus Service Bulletin A300–53– 

6122, Revision 03, dated August 25, 2011, 

which is not incorporated by reference in this 

AD. 

(2) This paragraph restates the credit for 

Airbus Model A300 series airplanes for 

previous actions as provided by Table 1 of 

AD 2004–23–20, Amendment 39–13875 (69 

FR 68779, November 26, 2004). For Airbus 

Model A300 series airplanes: This paragraph 

provides credit for actions required by 

paragraph (j) of this AD, if those actions were 

performed before January 3, 2005 (the 

effective date of AD 2004–23–20) using the 

service information specified in paragraph 

(r)(2)(i), (r)(2)(ii), or (r)(2)(iii) of this AD. 

(i) Airbus Service Bulletin A300–53–0271, 

dated September 10, 1991, which is not 

incorporated by reference in this AD. 

(ii) Airbus Service Bulletin A300–53–0271, 

Revision 01, dated February 16, 1993, which 

is not incorporated by reference in this AD. 

(iii) Airbus Service Bulletin A300–53– 

0271, Revision 02, dated July 13, 2000, which 

is not incorporated by reference in this AD. 

(s) 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, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–2125; fax 425–227–1149. Information 

may be emailed to: 9-ANM-116-AMOCREQUESTS@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 

96–13–11, Amendment 39–9679 (61 FR 

35122, July 5, 1996), and AD 2001–06–10, 

Amendment 39–12157, April 2, 2001), are 

approved as AMOCs for the corresponding 

requirements 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’ EASA DOA. If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0295, dated 

December 11, 2013, 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–2016–0451. 

(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 January 

21, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–01736 Filed 1–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 1 

[REG–139483–13] 

RIN 1545–BL87 

Treatment of Certain Transfers of 

Property of Foreign Corporations; 

Hearing Correction 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Correction to a notice of public 

hearing on proposed rulemaking. 

SUMMARY: This document corrects a 

notice of public hearing on proposed 

regulations that published in the 

Federal Register on January 20, 2016, at 

81 FR 3069. 

DATES: The public hearing is being held 

on Monday, February 8, 2016 at 10 a.m. 

The IRS must now receive outlines of 

the topics to be discussed at the public 

hearing by Thursday, February 4, 2016. 


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