26962 Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules 

Aerona ́utica S.A., Phenom Maintenance 

Support, Av. Brig. Faria Lima, 2170, Sao Jose 

dos Campos—SP, CEP: 12227–901—PO Box: 

36/2, Brasil; telephone: ++55 12 3927–5383; 

fax: ++55 12 3927–2619; E-mail: 

phenom.reliability@embraer.com.br; Internet: 

http://www.embraer.com.br. You may review 

copies of the referenced service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. 

Issued in Kansas City, Missouri, on May 4, 

2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–11334 Filed 5–9–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0389; Directorate 

Identifier 2007–NM–189–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2–1C, A300 B2–203, A300 B2K– 

3C, A300–B4–103, A300 B4–203, and 

A300 B4–2C Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

* * * [C]racks * * * in sections 13 to 18 of 

the fuselage between rivets of longitudinal 

lap joints between frames 18 and 80 which 

could affect the structural integrity of the 

fuselage if not corrected. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by June 24, 2011. 

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 

W12–40, 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— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

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

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

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; or in person at the 

Docket Operations office 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, 

Washington 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–2011–0389; Directorate Identifier 

2007–NM–189–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 December 20, 1989, we issued AD 

90–01–10, Amendment 39–6448 (55 FR 

261, January 4, 1990). That AD required 

actions intended to address an unsafe 

condition on the products listed above. 

Since we issued AD 90–01–10, Airbus 

has refined the inspection program for 

cracking at areas of the fuselage defined 

in AD 90–01–10 as ‘‘special areas’’ 

(paragraph A.1. of AD 90–01–10), 

‘‘standard areas’’ (paragraph A.2. of AD 

90–01–10), and ‘‘modified or repaired 

areas’’ (paragraph A.3. of AD 90–01–10). 

The new inspection program is designed 

to allow airplanes to reach their limit of 

validity (LOV). Certain compliance 

times are reduced and certain other 

compliance times are extended. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2007–0091, 

dated April 10, 2007, and corrected June 

23, 2008 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

This Airworthiness Directive (AD) is issued 

in order to prevent cracks development in 

sections 13 to 18 of the fuselage between 

rivets of longitudinal lap joints between 

frames 18 and 80 which could affect the 

structural integrity of the fuselage if not 

corrected. 

This new AD: 

—Retains the requirements of DGAC AD 

1989–061–092(B)R4 [which corresponds to 

FAA AD 90–01–10], which is cancelled; 

—Takes into account a new inspection 

program as detailed in AIRBUS Service 

Bulletins (SB) A300–53–0211 Revision 7, 

which will allow A300 aircraft to reach the 

Limit of Validity (LOV). 

This AD has been republished to correctly 

refer to SB A300–53–0211 in Note 2 of the 

Compliance section. 

The inspection program consists of 

repetitive detailed inspections for 

disbonding and cracking of the fuselage 

inner doubler; eddy current and 

ultrasonic inspections of the fuselage 

longitudinal lap joints for cracking; and 

repair if necessary (i.e., repairing any 

cracking or disbonding, or contacting 

Airbus for repair instructions and doing 

the repair). You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A300–53–229, Revision 5, dated April 8, 

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Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules 26963 

1997; and Mandatory Service Bulletin 

A300–53–0211, Revision 07, dated 

December 1, 2006. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

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. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 5 products of U.S. registry. 

We estimate that it would take about 

3,735 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$1,587,375, or $317,475 per product. 

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); and 

3. 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 Amendment 39–6448 (55 FR 

261, January 4, 1990) and adding the 

following new AD: 

Airbus: Docket No. FAA–2011–0389; 

Directorate Identifier 2007–NM–189–AD. 

Comments Due Date 

(a) We must receive comments by June 24, 

2011. 

Affected ADs 

(b) This AD supersedes AD 90–01–10, 

Amendment 39–6448. 

Applicability 

(c) This AD applies to Airbus Model A300 

B2–1C, A300 B2–203, A300 B2K–3C, A300– 

B4–103, A300 B4–203, and A300 B4–2C 

airplanes; certificated in any category; serial 

numbers 0003 through 0156 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

This Airworthiness Directive (AD) is 

issued in order to prevent cracks 

development in sections 13 to 18 of the 

fuselage between rivets of longitudinal lap 

joints between frames 18 and 80 which could 

affect the structural integrity of the fuselage 

if not corrected. 

This new AD: 

—Retains the requirements of DGAC AD 

1989–061–092(B)R4[which corresponds to 

FAA AD 90–10–10], which is cancelled; 

—Takes into account a new inspection 

program as detailed in AIRBUS Service 

Bulletins (SB) A300–53–0211 Revision 7, 

which will allow A300 aircraft to reach the 

Limit of Validity (LOV). 

This AD has been republished to correctly 

refer to SB A300–53–0211 in Note 2 of the 

Compliance section. 

The inspection program consists of repetitive 

detailed inspections for disbonding and 

cracking of the fuselage inner doubler; eddy 

current and ultrasonic inspections of the 

fuselage longitudinal lap joints for cracking; 

and repair if necessary (i.e., repairing any 

cracking or disbonding, or contacting Airbus 

for repair instructions and doing the repair). 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Repetitive Inspections of ‘‘Special Areas’’ 

and Repair or Modification if Necessary 

(g) For airplanes on which an eddy current 

inspection of the ‘‘special’’ areas of the 

longitudinal lap joints has not been done as 

of the effective date of this AD in accordance 

with Airbus Mandatory Service Bulletin 

A300–53–0211: Prior to the accumulation of 

24,000 total flight cycles, or within 2,000 

flight cycles after the effective date of this 

AD, whichever occurs later; do an eddy 

current inspection for cracking of the 

‘‘special’’ areas of the longitudinal lap joints, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–53–0211, Revision 07, dated 

December 1, 2006. If no cracking is found, 

repeat the inspection thereafter at the 

applicable intervals specified in Table 1 of 

this AD. If any crack is found during any 

inspection required by this paragraph, repair 

or modify before further flight, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–53– 

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26964 Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules 

0211, Revision 07, dated December 1, 2006; 

and do the applicable inspection of the 

repaired or modified area in accordance with 

paragraph (k) of this AD. ‘‘Special’’ areas of 

the longitudinal lap joints are defined in 

Airbus Mandatory Service Bulletin A300–53– 

0211, Revision 07, dated December 1, 2006. 

TABLE 1—REPETITIVE INTERVALS FOR INSPECTING SPECIAL AREAS OF THE LONGITUDINAL LAP JOINTS

For airplanes— Inspect special area— Repeat at intervals not to exceed— 

All ............................................................. STGR5 LH and RH (FR54 through FR58) ........... 3,600 flight cycles 

All ............................................................. STGR22 LH and RH (FR26 through FR40) ......... 2,700 flight cycles 

All ............................................................. STGR22 RH (FR58 through FR65) ...................... 3,000 flight cycles 

All ............................................................. STGR31 LH/RH (FR26 through FR39) ................. 3,000 flight cycles 

MSN 003 .................................................. STGR31 LH/RH (FR54 through FR58) ................. 3,600 flight cycles 

(h) For airplanes on which an eddy current 

inspection of the ‘‘special’’ areas of the 

longitudinal lap joints has been done before 

the effective date of this AD in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–53– 

0211; except for airplanes on which a repair 

or modification of the ‘‘special’’ areas has 

been done in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–0211: 

Do the next inspection of the ‘‘special’’ areas 

of the longitudinal lap joints at the earlier of 

the times specified in paragraphs (h)(1) and 

(h)(2) of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006. If no 

cracking is found, repeat the inspection 

thereafter at the applicable intervals specified 

in Table 2 of this AD. If any crack is found 

during any inspection required by this 

paragraph, repair or modify before further 

flight, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006, and do 

the applicable inspection of the repaired or 

modified area in accordance with paragraph 

(k) of this AD. ‘‘Special’’ areas of the 

longitudinal lap joints are defined in Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006. 

(1) Within 6,000 flight cycles after doing 

the last inspection of the ‘‘special’’ areas of 

the longitudinal lap joints, in accordance 

with Airbus Mandatory Service Bulletin 

A300–53–0211. 

(2) Within the applicable intervals 

specified in Table 2 of this AD, or within 60 

days after the effective date of this AD, 

whichever occurs later. 

TABLE 2—REPETITIVE INTERVALS FOR INSPECTING SPECIAL AREAS OF THE LONGITUDINAL LAP JOINTS

For airplanes— Inspect special area— Repeat at intervals not to exceed— 

All ............................................................. STGR5 LH and RH (FR54 through FR58) ........... 3,600 flight cycles 

All ............................................................. STGR22 LH and RH (FR26 through FR40) ......... 2,700 flight cycles 

All ............................................................. STGR22 RH (FR58 through FR65) ...................... 3,000 flight cycles 

All ............................................................. STGR31 LH/RH (FR26 through FR39) ................. 3,000 flight cycles 

MSN 003 .................................................. STGR31 LH/RH (FR54 through FR58) ................. 3,600 flight cycles 

Repetitive Inspections of ‘‘Standard Areas’’ 

and Repair or Modification If Necessary 

(i) For airplanes on which an eddy current 

inspection of the ‘‘standard’’ areas of the 

longitudinal lap joints has not been done 

before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–53–0211: At the applicable 

time specified in Tables 3 and 4 of this AD, 

do an eddy current inspection for cracking of 

the longitudinal lap joints in the ‘‘standard’’ 

areas, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006. Repeat 

the inspection thereafter at the applicable 

intervals specified in Tables 3 and 4 of this 

AD. If any crack is found during any 

inspection required by this paragraph, repair 

or modify before further flight, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–53– 

0211, Revision 07, dated December 1, 2006, 

and do the applicable inspection of the 

applicable area specified in Tables 3 and 4 

of this AD. ‘‘Standard’’ areas of the 

longitudinal lap joints are defined in Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006. 

TABLE 3—INITIAL COMPLIANCE TIMES AND REPETITIVE INTERVALS FOR INSPECTING STANDARD AREAS OF THE

LONGITUDINAL LAP JOINTS

For airplanes— Before the accumulation of— Inspect standard area— Repeat at intervals not to 

exceed— 

All .............................................. 32,000 total flight cycles ..................... STGR5, 13, 22 LH and RH, STGR31

LH (FR18 through FR26).

3,600 flight cycles 

All .............................................. 32,000 total flight cycles ..................... STGR27 RH, STGR39 RH (FR18 

through FR20A, FR25A, FR26).

8,000 flight cycles 

All .............................................. 32,000 total flight cycles ..................... STGR43 LH, STGR46 RH, STGR51 

LH (FR19 through FR26).

5,700 flight cycles 

All .............................................. 32,000 total flight cycles ..................... STGR5 LH/RH (FR26 through FR40)

STGR11 LH/RH (FR27 through 

FR32) STGR13 LH/RH (FR 26 

through FR28, FR31 through FR40) 

STGR27 LH/RH (FR 27 through 

FR32) STGR43 LH/RH (FR 26 

through FR39) STGR49 RH (FR26 

through FR39).

3,000 flight cycles 

All .............................................. 32,000 total flight cycles ..................... STGR47 LH (FR26 through FR39) .... 5,700 

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Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules 26965 

TABLE 3—INITIAL COMPLIANCE TIMES AND REPETITIVE INTERVALS FOR INSPECTING STANDARD AREAS OF THE

LONGITUDINAL LAP JOINTS—Continued 

For airplanes— Before the accumulation of— Inspect standard area— Repeat at intervals not to 

exceed— 

All .............................................. 32,000 total flight cycles ..................... STGR5, 13, 22 LH/RH (FR40 through 

FR54).

5,000 

All except MSN 0003 ................ 32,000 total flight cycles ..................... STGR13, 44, 52 LH/RH (FR54 

through FR58) STGR22 LH/RH 

(FR54, FR55) STGR31 LH/RH 

(FR54 through FR58).

3,600 

(j) For airplanes on which an eddy current 

inspection of the ‘‘standard’’ areas of the 

longitudinal lap joints has been done as of 

the effective date of this AD in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–53– 

0211; except for airplanes on which a repair 

or modification of the ‘‘standard areas’’ has 

been done in accordance with Airbus 

Mandatory Service Bulletin A300–53–0211: 

Do the next inspection of the ‘‘standard’’ areas 

of the longitudinal lap joints at the earlier of 

the times specified in paragraphs (j)(1) and 

(j)(2) of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006. 

Thereafter, if no cracking is found, repeat the 

inspection at the applicable intervals 

specified in Tables 3 and 4 of this AD. If any 

crack is found during any inspection 

required by this paragraph, repair or modify 

before further flight, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006, and do 

the applicable inspection of the repaired or 

modified area in accordance with paragraph 

(k) of this AD. ‘‘Standard’’ areas of the 

longitudinal lap joints are defined in Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006. 

TABLE 4—INITIAL COMPLIANCE TIMES AND REPETITIVE INTERVALS FOR INSPECTING ADDITIONAL STANDARD AREAS OF THE

LONGITUDINAL LAP JOINTS

For airplanes— Before the accumulation of— Inspect standard area— Repeat at intervals not to 

exceed— 

Pre-Mod 1398 ........................... 32,000 total flight cycles ..................... STGR5, 13 LH/RH 22 LH (FR58 

through FR65) STGR31 LH (FR58 

through FR72) STGR31 RH (FR65 

through FR72).

2,700 flight cycles 

All .............................................. 32,000 total flight cycles ..................... STGR27 RH, STGR39 RH (FR58, 

FR59A, FR63A through FR65).

8,000 flight cycles 

Post-Mod 1398 ......................... 32,000 total flight cycles ..................... STGR5, 13 LH/RH 22 LH (FR58 

through FR65) STGR31 LH (FR58 

through FR72) STGR 31 RH (FR65 

through FR72).

3,000 flight cycles 

Pre-Mod 1398 ........................... 32,000 total flight cycles ..................... STGR5, 13, 22 LH/RH (FR65 through 

FR72).

2,300 flight cycles 

Post-Mod 1398 ......................... 32,000 total flight cycles ..................... STGR5, 13, 22 LH/RH (FR65 through 

FR72).

3,000 flight cycles 

All .............................................. 32,000 total flight cycles ..................... STGR44 LH (FR58 through FR72) 

STGR52 LH/RH (FR58 through 

FR65) STGR47 RH (FR58 through 

FR72) STGR57 LH (FR65 through 

FR72).

3,000 flight cycles 

All .............................................. 24,000 total flight cycles ..................... STGR22 RH (FR58 through FR65) .... 3,000 flight cycles 

All .............................................. 32,000 total flight cycles ..................... STGR6 LH/RH (FR72 through FR80)

STGR24 LH/RH (FR76 through 

FR80).

3,000 flight cycles 

All .............................................. 32,000 total flight cycles ..................... STRG17 LH/RH (FR76 through 

FR80) STGR29 LH/RH (FR72 

through FR76).

STGR35 LH/RH (FR72 through 

FR80).

5,700 flight cycles 

All .............................................. 27,000 total flight cycles ..................... STGR51 LH/RH (FR72 through 

FR80).

5,700 flight cycles 

(1) Within the applicable time in paragraph 

(j)(1)(i) or (j)(1)(ii) of this AD after doing the 

last inspection of the ‘‘standard’’ areas of the 

longitudinal lap joints in accordance with 

Airbus Mandatory Service Bulletin A300–53– 

0211. 

(i) For longitudinal lap joints with bonded 

doublers: 6,000 flight cycles. 

(ii) For longitudinal lap joints without 

bonded doublers: 8,000 flight cycles. 

(2) Within the applicable time specified in 

Tables 3 or 4 of this AD, or within 60 days 

after the effective date of this AD, whichever 

occurs later. 

Post-Repair or Modification Inspections and 

Repair or Modification if Necessary 

(k) For airplanes on which a repair or 

modification has been done in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–53– 

0211: At the applicable initial inspection 

time specified in Table 5 of this AD, do an 

eddy current inspection for cracking of the 

repaired or modified areas, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A300–53– 

0211, Revision 07, dated December 1, 2006. 

If no cracking is found, repeat the inspection 

thereafter at the applicable intervals specified 

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26966 Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules 

in Table 5 of this AD. If any crack is found 

during any inspection required by this 

paragraph, repair or modify before further 

flight, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006. 

TABLE 5—POST-REPAIR OR MODIFICATION COMPLIANCE TIME

Repair or retrofit solution/area—as identified in airbus 

mandatory service bulletin 

A300–53–0211 

Initial inspection after repair or retrofit— Follow-up inspections at intervals not to exceed— 

Repair 1: (Without cut out) also applicable to the solution with removed inner doubler.Skin/doubler thickness ....................................................

• < 1 inch: 10,000 flight cycles after repair ....................

1,000 flight cycles. 

• ≥ 1 inch and < 2 inch: 30,000 flight cycles after repair 2,000 flight cycles. 

• ≥ 2 inch: 60,000 flight cycles after repair .................... 6,400 flight cycles. 

Repair 4 (With cut out) ..................................................... Within 32,000 flight cycles after repair ........................... 5,000 flight cycles. 

Repair 4A (With cut out) ................................................... Within 24,000 flight cycles after repair ........................... 5,300 flight cycles. 

Repair 7 (MSN 0095 at STGR52 LH in Section 16) ........ Within 37,000 flight cycles after repair ........................... 12,000 flight cycles. 

Repair 9 (MSN 0073 and 0095 STGR44 LH/RH in Sections 16 and 17).Within 36,000 flight cycles after repair ........................... 5,000 flight cycles. 

Repair 10 (Post-repair inspections in Figure 13) ............. Within 20,000 flight cycles after repair ........................... 11,000 flight cycles. 

Repair 2 (With cut out) ..................................................... Within 24,000 flight cycles after repair ........................... 5,300 flight cycles. 

Repair 3 (Without cut out) ................................................ Within 24,000 flight cycles after repair ........................... 5,300 flight cycles. 

Retrofit 1 (Retrofit lap joint) .............................................. Within 32,000 flight cycles after retrofit .......................... 5,000 flight cycles. 

Retrofit 2 Retrofit lower shell (4 panel solution) STGR43 

LH (FR26 through FR39), STGR43 RH (FR26 through 

FR38), and STGR49 RH (FR26 through FR38).

Within 32,000 flight cycles after retrofit .......................... 3,000 flight cycles. 

Retrofit 2 Retrofit lower shell (4 panel solution) STGR 46 

RH (FR19 through FR26), and STGR47 LH (FR26 

through FR39), and STGR51 LH (FR19 through 

FR26).

Within 32,000 flight cycles after retrofit .......................... 5,700 flight cycles. 

Retrofit 3 Retrofit lower shell (3 panel solution) STGR43 

LH (FR26 through FR39), and STGR43 RH (FR26 

through FR38).

Within 32,000 flight cycles after retrofit .......................... 3,000 flight cycles. 

Retrofit 3 Retrofit lower shell (3 panel solution) STGR46 

RH (FR19 through FR26), and STGR51 LH (FR19 

through FR26), and STGR 54 LH (FR26 through 

FR39).

Within 32,000 flight cycles after retrofit .......................... 5,700 flight cycles. 

Retrofit 3A (STGR43 LH/RH between FR37 and FR39 in 

Section 14).

Within 32,000 flight cycles after retrofit .......................... 5,000 flight cycles. 

Retrofit 4 (Retrofit lap joint without cut out) ...................... Within 42,000 flight cycles after retrofit .......................... 5,000 flight cycles. 

Retrofit 5 (Retrofit lap joint) .............................................. Within 42,000 flight cycles after retrofit .......................... 5,000 flight cycles. 

Retrofit 6 (Retrofit lap joint) .............................................. Within 34,000 flight cycles after retrofit .......................... 12,000 flight cycles. 

Retrofit 7 (Retrofit lap joint) .............................................. Within 47,600 flight cycles after retrofit .......................... 5,400 flight cycles. 

Fuselage Inner Doubler Inspections and 

Repair if Necessary 

(l) For airplanes on which any inspections 

of the fuselage bonded inner doublers of the 

longitudinal lap joints in Sections 13 through 

18 (except Sections 16 and 17 at Stringer 31 

left-hand and right-hand) for disbonding and 

cracking have not been done as of the 

effective date of this AD in accordance with 

Airbus Service Bulletin A300–53–229: Prior 

to the accumulation of 24,000 total flight 

cycles or within 15 years since new, 

whichever occurs first; or within 60 days 

after the effective date of this AD; whichever 

occurs later, do a detailed inspection of the 

fuselage bonded inner doublers of the 

longitudinal lap joints in Sections 13 through 

18 (except Sections 16 and 17 at Stringer 31 

left-hand and right-hand) for disbonding and 

cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–229, Revision 5, 

dated April 8, 1997. If no disbonding and no 

cracking is found, repeat the inspection 

thereafter at the applicable intervals specified 

in Table 6 of this AD. 

TABLE 6—REPETITIVE INTERVALS FOR INSPECTIONS FOR DISBONDING AND CRACKING

For area— Inspect at intervals not to exceed— 

Sections 13 and 14 as specified in Airbus Service Bulletin A300–53–229.Within 7 years or 12,000 flight cycles after doing the inspection, whichever occurs 

first. 

Sections 15 through 18 as specified in Airbus Service 

Bulletin A300–53–229.

Within 8.5 years or 12,000 flight cycles after doing the inspection, whichever occurs 

first. 

(1) If no cracking is found and ‘‘minor’’ 

disbonding, as defined in Airbus Service 

Bulletin A300–53–229, is found: Repeat the 

inspection thereafter at intervals not to 

exceed 1 year for areas below stringer 22, and 

at intervals not to exceed 2 years for areas 

above and including stringer 22. 

(2) If no cracking is found and ‘‘major’’ 

disbonding, as defined in Airbus Service 

Bulletin A300–53–229, is found: Within 

1,000 flight cycles after doing the inspection, 

repair, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–229, Revision 5, 

dated April 8, 1997. 

(3) If any cracking is found, repair prior to 

further flight, in accordance with Airbus 

Service Bulletin A300–53–229, Revision 5, 

dated April 8, 1997. 

(m) For airplanes on which any inspections 

of the fuselage bonded inner doublers of the 

longitudinal lap joints in Sections 13 through 

18 (except Sections 16 and 17 at Stringer 31 

left-hand and right-hand) for disbonding and 

cracking have been done as of the effective 

date of this AD in accordance with Airbus 

Service Bulletin A300–53–229; except for 

airplanes on which a repair of that area has 

been done in accordance with Airbus Service 

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Federal Register / Vol. 76, No. 90 / Tuesday, May 10, 2011 / Proposed Rules 26967 

Bulletin A300–53–229: At the applicable 

time specified in Table 6 of this AD, or 

within 60 days after the effective date of this 

AD, whichever occurs later, do a detailed 

inspection of the fuselage bonded inner 

doublers of the longitudinal lap joints in 

Sections 13 through 18 (except Sections 16 

and 17 at Stringer 31 left-hand and righthand) for disbonding and cracking, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–229, Revision 5, dated April 8, 1997. If no 

disbonding and no cracking is found, repeat 

the inspection at the applicable intervals 

specified in Table 6 of this AD. 

(1) If no cracking is found and ‘‘minor’’ 

disbonding, as defined in Airbus Service 

Bulletin A300–53–229, is found: Repeat the 

inspection thereafter at intervals not to 

exceed 1 year for areas below stringer 22, and 

at intervals not to exceed 2 years for areas 

above and including stringer 22. 

(2) If no cracking is found and ‘‘major’’ 

disbonding, as defined in Airbus Service 

Bulletin A300–53–229, is found: Within 

1,000 flight cycles after doing the inspection, 

repair, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–229, Revision 5, 

dated April 8, 1997. 

(3) If any cracking is found, repair prior to 

further flight, in accordance with Airbus 

Service Bulletin A300–53–229, Revision 5, 

dated April 8, 1997. 

(n) For airplanes on which any inspections 

of the fuselage bonded inner doublers of the 

longitudinal lap joints in Sections 16 and 17 

at Stringer 31 left-hand and right-hand for 

disbonding and cracking have not been done 

as of the effective date of this AD in 

accordance with Airbus Service Bulletin 

A300–53–229: Prior to the accumulation of 

24,000 total flight cycles or within 12 years 

since new, whichever occurs first; or within 

60 days after the effective date of this AD; 

whichever occurs later, do a detailed 

inspection of the fuselage bonded inner 

doubles of the longitudinal lap joints in 

Sections 16 and 17 at Stringer 31 left-hand 

and right-hand for disbonding and cracking, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–229, Revision 5, dated April 8, 1997. If no 

disbonding and no cracking is found, repeat 

the inspection thereafter at intervals not to 

exceed 7 years or 12,000 flight cycles, 

whichever occurs first. 

(1) If no cracking is found and ‘‘minor’’ 

disbonding, as defined in Airbus Service 

Bulletin A300–53–229, is found: Repeat the 

inspection thereafter at intervals not to 

exceed 1 year for areas below stringer 22, and 

at intervals not to exceed 2 years for areas 

above and including stringer 22. Doing a 

repair in accordance with Airbus Service 

Bulletin A300–53–229, Revision 5, dated 

April 8, 1997, terminates the repetitive 

inspections required by this paragraph for 

that area. 

(2) If no cracking is found and ‘‘major’’ 

disbonding, as defined in Airbus Service 

Bulletin A300–53–229, is found: Within 

1,000 flight cycles after doing the inspection, 

repair, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–229, Revision 5, 

dated April 8, 1997. 

(3) If any cracking is found, repair prior to 

further flight, in accordance with Airbus 

Service Bulletin A300–53–229, Revision 5, 

dated April 8, 1997. 

(o) For airplanes on which any inspections 

of the fuselage bonded inner doublers of the 

longitudinal lap joints in Sections 16 and 17 

at Stringer 31 left-hand and right-hand for 

disbonding and cracking have been done as 

of the effective date of this AD in accordance 

with Airbus Service Bulletin A300–53–229; 

except airplanes on which a repair of that 

area has been done in accordance with 

Airbus Service Bulletin A300–53–229: 

Within 7 years or 12,000 flight cycles after 

doing the inspection, whichever occurs first; 

or within 60 days after the effective date of 

this AD; whichever occurs later, do a detailed 

inspection of the fuselage bonded inner 

doubles of the longitudinal lap joints in 

Sections 16 and 17 at Stringer 31 left-hand 

and right-hand for disbonding and cracking 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–229, Revision 5, dated April 8, 1997. If no 

disbonding and corrosion are found, repeat 

the inspection thereafter at intervals not to 

exceed 7 years or 12,000 flight cycles, 

whichever occurs first. 

(1) If no cracking is found and ‘‘minor’’ 

disbonding, as defined in Airbus Service 

Bulletin A300–53–229, is found: Repeat the 

inspection thereafter at intervals not to 

exceed 1 year for areas below stringer 22, and 

at intervals not to exceed 2 years for areas 

above and including stringer 22. Doing a 

repair in accordance with Airbus Service 

Bulletin A300–53–229, Revision 5, dated 

April 8, 1997, terminates the repetitive 

inspections required by this paragraph for 

that area. 

(2) If no cracking is found and ‘‘major’’ 

disbonding, as defined in Airbus Service 

Bulletin A300–53–229, is found: Within 

1,000 flight cycles after doing the inspection, 

repair, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–53–229, Revision 5, 

dated April 8, 1997. 

(3) If any cracking is found, repair prior to 

further flight, in accordance with Airbus 

Service Bulletin A300–53–229, Revision 5, 

dated April 8, 1997. 

(p) Although Airbus Service Bulletin 

A300–53–229, Revision 5, dated April 8, 

1997; and Airbus Mandatory Service Bulletin 

A300–53–0211, Revision 07, dated December 

1, 2006; specify to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

(1) Although the MCAI or service 

information allows further flight after cracks 

are found during compliance with the 

required action, this AD requires that you 

repair the crack(s) before further flight. 

(2) The MCAI or service information does 

not include enforceable compliance times for 

certain actions; however, this AD requires 

that those actions be done at the enforceable 

times specified in this AD. 

(3) Although the MCAI or service 

information tells you to submit information 

to the manufacturer, paragraph (p) of this AD 

specifies that such submittal is not required. 

Other FAA AD Provisions 

(q) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be e-mailed to: 9- 

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

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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(r) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2007–0091, 

dated April 10, 2007, corrected June 23, 

2008; Airbus Service Bulletin A300–53–229, 

Revision 5, dated April 8, 1997; and Airbus 

Mandatory Service Bulletin A300–53–0211, 

Revision 07, dated December 1, 2006; for 

related information. 

Issued in Renton, Washington, on April 28, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–11335 Filed 5–9–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

National Indian Gaming Commission 

25 CFR Chapter III 

Regulatory Review Schedule 

AGENCY: National Indian Gaming 

Commission. 

ACTION: Notice of comment periods on 

preliminary drafts. 

SUMMARY: On November 18, 2010, the 

National Indian Gaming Commission 

(NIGC) issued a Notice of Inquiry and 

mstockstill on DSKH9S0YB1PROD with PROPOSALS