Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules 62673 

This condition, if not corrected, and if 

occurring while the RAT is deployed, could 

result in a degraded direct current power 

which is distributed to essential aeroplane 

systems and therefore aeroplane operations 

might be impaired. 

* * * * * 

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. 

Actions 

(g) Within 28 months after the effective 

date of this AD, replace any RAT TRU having 

P/N 5913703 with a RAT TRU having P/N 

5915825, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin 7X–163, dated 

December 1, 2010. 

Parts Installation 

(h) As of the effective date of this AD, no 

person may install any RAT TRU having 

P/N 5913703, on any airplane. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; 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 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011–0008, 

dated January 18, 2011; and Dassault 

Mandatory Service Bulletin 7X–163, dated 

December 1, 2010; for related information. 

Issued in Renton, Washington, on 

September 28, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–26112 Filed 10–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1066; Directorate 

Identifier 2011–NM–050–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD), for certain 

Airbus Model A300 B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes and Model A300 B4–601, B4– 

603, B4–620, B4–622, B4–605R, B4– 

622R, and F4–605R airplanes, 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: 

Following the occurrence of cracks on the 

MLG [main landing gear] Rib 5 RH [righthand] and LH [left-hand] attachment fitting 

lower flanges, DGAC [Direction Ge ́ne ́rale de 

l’Aviation Civile] France AD 2003–318(B) 

was issued to require repetitive inspections 

and, as terminating action * * * [.] 

Subsequently, new cases of cracks were 

discovered during scheduled maintenance 

checks by operators of A300B4 and A300– 

600 type aeroplanes on which the 

terminating action * * * [was] embodied. 

This condition, if not corrected, could affect 

the structural integrity of those aeroplanes. 

* * * * * 

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 November 25, 

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 W12–140, 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— 

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–2011–1066; Directorate Identifier 

2011–NM–050–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 


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personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On November 3, 2010, we issued AD 

2010–23–26, Amendment 39–16516 (75 

FR 74610, December 1, 2010). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010), we have determined 

that it is necessary to mandate the 

optional spot-facing modification 

specified in paragraph (q) of the existing 

AD: The European Aviation Safety 

Agency (EASA), which is the aviation 

authority for the Member States of the 

European Community, has issued EASA 

Airworthiness Directive 2011–0029, 

dated February 24, 2011 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Following the occurrence of cracks on the 

MLG [main landing gear] Rib 5 RH [righthand] and LH [left-hand] attachment fitting 

lower flanges, DGAC [Direction Ge ́ne ́rale de 

l’Aviation Civile] France AD 2003–318(B) 

was issued to require repetitive inspections 

and, as terminating action, the embodiment 

of Airbus Service Bulletins (SB) A300–57– 

0235 and A300–57–6088 * * *. 

Subsequently, new cases of cracks were 

discovered during scheduled maintenance 

checks by operators of A300B4 and A300– 

600 type aeroplanes on which the 

terminating action SB’s were embodied. This 

condition, if not corrected, could affect the 

structural integrity of those aeroplanes. 

To address and correct this condition, 

Airbus developed an inspection programme 

for aeroplanes modified in accordance with 

SB A300–57–0235 or A300–57–6088. This 

inspection programme was required to be 

implemented by DGAC France AD F–2005– 

113, original issue and later revision 1 

[parallel to part of FAA AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)]. 

A new EASA [European Aviation Safety 

Agency] AD 2008–0111, superseding DGAC 

France AD F–2005–113R1, was issued to 

reduce the applicability. For aeroplanes 

already compliant with DGAC France AD F– 

2005–113R1, no further action was required. 

Since EASA AD 2008–0111 issuance, 

Airbus reviewed the inspection programmes 

of SB A300–57A0246 and SB A300–57A6101 

to introduce repetitive inspections including 

a new inspection technique for holes 47 and 

54 and to reduce inspections threshold and 

intervals from 700 Flight Cycles (FC) to 400 

FC until a revised terminating action is made 

available. 

For the reasons stated above, EASA AD 

2009–0081 superseded EASA AD 2008–0111 

and required operators to comply with the 

new inspection programme introduced in 

Revisions 3 of Airbus SB A300–57A0246 and 

Airbus SB A300–57A6101. 

EASA AD 2009–0081 R1 [which 

corresponds to FAA AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010)] has been published to 

introduce an optional terminating action 

which consisted of spot-facing the sensitive 

holes of the MLG Rib 5 (LH and RH) bottom 

flanges. 

Later discussions with Airbus have 

demonstrated the necessity to require the 

spot-facing modification as a final solution 

(no longer optional). This new [EASA] AD 

retains the inspection requirements of EASA 

AD 2009–0081 R1, which is superseded, and 

requires the spot-facing of sensitive holes of 

the MLG Rib 5 (LH and RH) bottom flanges 

as terminating action. 

Required actions include repairing 

discrepancies (e.g., cracking or a 2nd 

oversize or greater fastener hole). You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletins A300–57–0254, Revision 01, 

including Appendix 1, dated June 14, 

2011; and A300–57–6110, Revision 01, 

including Appendix 1, dated June 6, 

2011. 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 155 products of U.S. 

registry. 

The actions that are required by AD 

2010–23–26, Amendment 39–16516 (75 

FR 74610, December 1, 2010), and 

retained in this AD take about 79 workhours per product, at an average labor 

rate of $85 per work hour. Required 

parts cost about $10,270 per product. 

Based on these figures, the estimated 

cost of the currently required actions is 

$16,985 per product. 

We estimate that it would take about 

100 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 

$1,317,500, or $8,500 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; 


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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 39–16516 (75 FR 

74610, December 1, 2010) and adding 

the following new AD: 

Airbus: Docket No. FAA–2011–1066; 

Directorate Identifier 2011–NM–050–AD. 

Comments Due Date 

(a) We must receive comments by 

November 25, 2011. 

Affected ADs 

(b) This AD supersedes AD 2010–23–26, 

Amendment 39–16516 (75 FR 74610, 

December 1, 2010). 

Applicability 

(c) This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD; except 

airplanes on which Airbus Modification 

11912 or 11932 has been installed. 

(1) Airbus Model A300 B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes. 

(2) Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, and 

F4–605R airplanes. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Following the occurrence of cracks on the 

MLG [main landing gear] Rib 5 RH [righthand] and LH [left-hand] attachment fitting 

lower flanges, DGAC [Direction Ge ́ne ́rale de 

l’Aviation Civile] France AD 2003–318(B) 

was issued to require repetitive inspections 

and, as terminating action, the embodiment 

of Airbus Service Bulletins (SB) A300–57– 

0235 and A300–57–6088 * * *. 

Subsequently, new cases of cracks were 

discovered during scheduled maintenance 

checks by operators of A300B4 and A300– 

600 type aeroplanes on which the 

terminating action SB’s were embodied. This 

condition, if not corrected, could affect the 

structural integrity of those aeroplanes. 

* * * * * 

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. 

Restatement of Requirements of AD 2000– 

05–07, Amendment 39–11616 (65 FR 12077, 

March 8, 2000): 

Repetitive Inspections 

(g) Perform a detailed inspection and a 

high-frequency eddy current (HFEC) 

inspection to detect cracks in Gear Rib 5 of 

the main landing gear (MLG) attachment 

fittings at the lower flange, in accordance 

with the Accomplishment Instructions of any 

applicable service bulletin listed in Table 1 

and Table 2 of this AD, at the time specified 

in paragraph (g)(1) or (g)(2) of this AD. After 

April 12, 2000 (the effective date of AD 

2000–05–07, Amendment 39–11616 (65 FR 

12077, March 8, 2000)), only the service 

bulletins listed in Table 2 of this AD may be 

used. Repeat the inspections thereafter at 

intervals not to exceed 1,500 flight cycles, 

until the actions specified in paragraph (i), 

(j), or (l) of this AD are accomplished. 

TABLE 1—REVISION 01 OF SERVICE BULLETINS

Model— Airbus service 

bulletin— Revision— Dated— 

A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R and F4–605R airplanes.

A300–57–6087 01 ............................................................... March 11, 1998. 

A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes.

A300–57–0234 01 ............................................................... March 11, 1998. 

TABLE 2—OTHER REVISIONS OF SERVICE BULLETINS

Model— Airbus service 

bulletin— Revision— Dated— 

A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R, and F4–605R airplanes.

A300–57A6087 02, including Appendix 01 ......................... June 24, 1999. 

03, including Appendix 01 ......................... May 19, 2000. 

04, including Appendix 01 ......................... February 19, 2002. 

05, including Appendix 01 ......................... March 10, 2008. 

A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes.

A300–57A0234 02 ............................................................... June 24, 1999. 

03, including Appendix 01 ......................... September 2, 1999. 

04, including Appendix 01 ......................... May 19, 2000. 

05, including Appendix 01 ......................... February 19, 2002. 

(1) For airplanes that have accumulated 

20,000 or more total flight cycles as of March 

9, 1998 (the effective date of AD 98–03–06, 

Amendment 39–10298 (63 FR 5224, February 

2, 1998)): Inspect within 500 flight cycles 

after March 9, 1998. 

(2) For airplanes that have accumulated 

less than 20,000 total flight cycles as of 

March 9, 1998: Inspect prior to the 

accumulation of 18,000 total flight cycles, or 

within 1,500 flight cycles after March 9, 

1998, whichever occurs later. 

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 


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lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’ 

Note 2: Accomplishment of the initial 

detailed and HFEC inspections prior to April 

12, 2000, in accordance with Airbus Service 

Bulletin A300–57A0234 or A300–57A6087, 

both dated August 5, 1997, as applicable, is 

considered acceptable for compliance with 

the initial inspections required by paragraph 

(g) of this AD. 

Repair for Any Crack Found During 

Inspections Required by Paragraph (g) of 

This AD 

(h) If any crack is detected during any 

inspection required by paragraph (g) of this 

AD, prior to further flight, accomplish the 

requirements of paragraph (h)(1) or (h)(2) of 

this AD, as applicable. 

(1) If a crack is detected at one hole only, 

and the crack does not extend out of the 

spotface of the hole, repair in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin in Table 2 of this 

AD. 

(2) If a crack is detected at more than one 

hole, or if any crack at any hole extends out 

of the spotface of the hole, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, or the 

European Aviation Safety Agency (EASA) (or 

its delegated agent). 

Terminating Modification for Repetitive 

Inspections Required by Paragraphs (g) and 

(j) of This AD 

(i) Except as required by paragraph (l) of 

this AD, prior to the accumulation of 21,000 

total flight cycles, or within 2 years after 

October 20, 1999 (the effective date of AD 

99–19–26, Amendment 39–11313 (64 FR 

49966, September 15, 1999)), whichever 

occurs later: Modify Gear Rib 5 of the MLG 

attachment fittings at the lower flange in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

in Table 3 of this AD. After July 18, 2006 (the 

effective date of AD 2006–12–13, 

Amendment 39–14639 (71 FR 33994, June 

13, 2006)), only Revision 04 of Airbus 

Service Bulletin A300–57–6088, and 

Revisions 04 and 05 of Airbus Service 

Bulletin A300–57–0235 may be used. 

Accomplishment of this modification 

constitutes terminating action for the 

repetitive inspection requirements of 

paragraphs (g) and (j) of this AD. 

TABLE 3—SERVICE BULLETINS FOR TERMINATING MODIFICATION

Model— Airbus service 

bulletin— Revision— Dated— 

A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R, and F4–605R airplanes.

A300–57–6088 01, including Appendix 01 ......................... February 1, 1999. 

02 ............................................................... September 5, 2002. 

04 ............................................................... December 3, 2003. 

A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes.

A300–57–0235 01, including Appendix 01 ......................... February 1, 1999. 

03 ............................................................... September 5, 2002. 

04 ............................................................... March 13, 2003. 

05 ............................................................... December 3, 2003. 

Note 3: Accomplishment of the 

modification required by paragraph (i) of this 

AD prior to April 12, 2000, in accordance 

with Airbus Service Bulletin A300–57–6088 

or A300–57–0235, both dated August 5, 1998; 

as applicable; is acceptable for compliance 

with the requirements of that paragraph. 

Restatement of Requirements of AD 2006– 

12–13, Amendment 39–14639 (71 FR 33994, 

June 13, 2006): 

Additional Repetitive Inspections 

(j) For airplanes on which the modification 

specified in paragraph (i) or (l) of this AD has 

not been done before July 18, 2006 (the 

effective date of AD 2006–12–13, 

Amendment 39–14639 (69 FR 54063, 

September 7, 2004)), perform a detailed and 

an HFEC inspection to detect cracks of the 

lower flange of Gear Rib 5 of the MLG at 

holes 43, 47, 48, 49, 50, 52, and 54, in 

accordance with the applicable service 

bulletin listed in Table 4 of this AD. Perform 

the inspections at the applicable time 

specified in paragraph (j)(1), (j)(2), (j)(3), or 

(j)(4) of this AD. Repeat the inspections 

thereafter at intervals not to exceed 700 flight 

cycles until the terminating modification 

required by paragraph (l) of this AD is 

accomplished. Accomplishment of the 

inspections per paragraph (j) of this AD 

terminates the inspection requirements of 

paragraph (g) of this AD. 

TABLE 4—SERVICE BULLETINS FOR REPETITIVE INSPECTIONS

Model— Airbus service 

bulletin— Revision— Dated— 

A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R, and F4–605R airplanes.

A300–57A6087 04, including Appendix 01 ......................... February 19, 2002. 

05, including Appendix 01 ......................... March 10, 2008. 

A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes.

A300–57A0234 05, including Appendix 01 ......................... February 19, 2002. 

(1) For Model A300 B2–1C, B2K–3C, B2– 

203, B4–2C, B4–103, and B4–203 airplanes; 

and Model A300 B4–601, B4–603, B4–620, 

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

airplanes that have accumulated 18,000 or 

more total flight cycles as of July 18, 2006: 

Within 700 flight cycles after July 18, 2006. 

(2) For Model A300 B2–1C, B2K–3C, and 

B2–203 airplanes that have accumulated less 

than 18,000 total flight cycles as of July 18, 

2006: Prior to the accumulation of 18,000 

total flight cycles, or within 700 flight cycles 

after July 18, 2006, whichever occurs later. 

(3) For Model A300 B4–2C, B4–103, and 

B4–203 airplanes that have accumulated less 

than 18,000 total flight cycles as of July 18, 

2006: Prior to the accumulation of 14,500 

total flight cycles, or within 700 flight cycles 

after July 18, 2006, whichever occurs later. 

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

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

605R airplanes that have accumulated less 

than 18,000 total flight cycles as of July 18, 

2006: Prior to the accumulation of 11,600 

total flight cycles, or within 700 flight cycles 

after July 18, 2006, whichever occurs later. 


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Crack Repair 

(k) If any crack is detected during any 

inspection required by paragraph (j) of this 

AD, prior to further flight, accomplish the 

requirements of paragraphs (k)(1) and (k)(2) 

of this AD, as applicable. 

(1) If a crack is detected at only one hole, 

and the crack does not extend out of the 

spotface of the hole, repair in accordance 

with Airbus Service Bulletin A300–57A0234, 

Revision 05, including Appendix 01, dated 

February 19, 2002 (for Model A300 B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes); or A300–57A6087, Revision 

04, including Appendix 01, dated February 

19, 2002; or A300–57A6087, Revision 05, 

dated March 10, 2008 (for Model A300 B4– 

601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R, and F4–605R airplanes); as applicable. 

(2) If a crack is detected at more than one 

hole, or if any crack at any hole extends out 

of the spotface of the hole, repair in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, or 

the EASA (or its delegated agent). 

Terminating Modification for Repetitive 

Inspections Required by Paragraphs (g) and 

(j) of This AD for Certain Airplanes 

(l) For airplanes on which the terminating 

modification in paragraph (i) of this AD has 

not been accomplished before July 18, 2006: 

At the earlier of the times specified in 

paragraphs (l)(1) and (l)(2) of this AD, modify 

Gear Rib 5 of the MLG attachment fittings at 

the lower flange. Except as provided by 

paragraph (m) of this AD, do the modification 

in accordance with the applicable service 

bulletin in Table 5 of this AD. This action 

terminates the repetitive inspections 

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

AD. 

(1) Prior to the accumulation of 21,000 

total flight cycles, or within 2 years after 

October 20, 1999, whichever is later. 

(2) Within 16 months after July 18, 2006. 

TABLE 5—SERVICE BULLETINS FOR TERMINATING MODIFICATION

Model— Airbus service 

bulletin— Revision— Dated— 

A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R and F4–605R airplanes.

A300–57–6088 04 ............................................................... December 3, 2003. 

A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes.

A300–57–0235 04 ............................................................... March 13, 2003. 

05 ............................................................... December 3, 2003. 

(m) Where the applicable service bulletin 

specified in paragraph (l) of this AD specifies 

to contact Airbus for modification 

instructions; or if there is a previously 

installed repair at any of the affected fastener 

holes; or if a crack is found when 

accomplishing the modification: Prior to 

further flight, modify in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, or the 

EASA (or its delegated agent). 

Actions Accomplished per Previous Issues of 

Service Bulletins 

(n) Actions accomplished before July 18, 

2006, in accordance with the service 

bulletins listed in Table 6 of this AD, are 

considered acceptable for compliance with 

the corresponding action specified in 

paragraphs (g) through (m) of this AD. 

TABLE 6—PREVIOUS ISSUES OF SERVICE BULLETINS

Airbus service bulletin— Revision— Dated— 

A300–57–0235 ...................................................................... 02, including Appendix 01 .................................................... September 27, 1999. 

03 ......................................................................................... September 5, 2002. 

A300–57–6088 ...................................................................... 02 ......................................................................................... September 5, 2000. 

03 ......................................................................................... March 13, 2003. 

No Reporting 

(o) Although the service bulletins 

identified in Tables 1, 2, 3, 4, 5, and 6 of this 

AD specify to submit certain information to 

the manufacturer, this AD does not include 

such a requirement. 

Restatement of Requirements of AD 2010– 

23–26, Amendment 39–16516 (75 FR 74610, 

December 1, 2010), with Certain Service 

Information Required after the Effective Date 

of This AD: 

Actions and Compliance 

(p) Unless already done, do the following 

actions. 

(1) At the applicable time specified in 

paragraph (p)(2) of this AD, perform a 

detailed inspection for cracking at the 

locations specified in paragraphs (p)(1)(i), 

(p)(1)(ii), and (p)(1)(iii) of this AD, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–57A0246, Revision 03, dated 

March 11, 2009, or Revision 04, dated 

September 9, 2009; or Airbus Mandatory 

Service Bulletin A300–57A6101, Revision 03, 

dated March 11, 2009, or Revision 04, dated 

September 9, 2009; as applicable. As of the 

effective date of this AD only Revision 04 of 

these service bulletins may be used. 

(i) The bottom flange and vertical web in 

the area between the wing rear spar/gear Rib 

5 attachment and the forward reaction-rod 

pick-up lug. 

(ii) On the inboard side, around the 

fastener holes at locations 43, 47 to 50, 52, 

and 54. 

(iii) On the outboard side, the lower flange, 

the vertical web and around the fastener 

holes at locations 43, 47 to 50, 52 and 54. 

(2) Do the inspection required by 

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

times in paragraphs (p)(2)(i) and (p)(2)(ii) of 

this AD. 

(i) Within 400 flight cycles after the 

accomplishment of the actions required by 

paragraph (i) or (l) of this AD, as applicable. 

(ii) Within 400 flight cycles or 4 months 

after January 5, 2011 (the effective date of AD 

2010–23–26, Amendment 39–16516 (75 FR 

74610, December 1, 2010)), whichever occurs 

first. 

(3) If no cracking is detected during the 

inspection required by paragraph (p)(1) of 

this AD, before further flight, perform a 

fluorescent penetrant inspection (FPI) at 

holes location 47 and 54, in the right-hand 

and left-hand MLG Rib 5 attachment fitting 

lower flange, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57A0246, 

Revision 03, dated March 11, 2009, or 

Revision 04, dated September 9, 2009; or 

Airbus Mandatory Service Bulletin A300– 

57A6101, Revision 03, dated March 11, 2009, 

or Revision 04, dated September 9, 2009; as 

applicable. As of the effective date of this 

AD, only Revision 04 of these service 

bulletins may be used. 

(4) Thereafter, at intervals not to exceed 

400 flight cycles, repeat the detailed and FPI 

inspections, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57A0246, 

Revision 03, dated March 11, 2009, or 

Revision 04, dated September 9, 2009; or 

Airbus Mandatory Service Bulletin A300– 

57A6101, Revision 03, dated March 11, 2009, 

or Revision 04, dated September 9, 2009; as 

applicable; until the terminating action 

required by paragraph (q) of this AD has been 


srobinson on DSK4SPTVN1PROD with PROPOSALS
62678 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules 

accomplished. As of the effective date of this 

AD, only Revision 04 of these service 

bulletins may be used. 

(5) If any crack is detected during any of 

the inspections required by paragraphs (p)(1), 

(p)(3), and (p)(4) of this AD, and Airbus 

Mandatory Service Bulletin A300–57A0246, 

Revision 03, dated March 11, 2009, or 

Revision 04, dated September 9, 2009; or 

Airbus Mandatory Service Bulletin A300– 

57A6101, Revision 03, dated March 11, 2009, 

or Revision 04, dated September 9, 2009; 

recommends contacting Airbus for 

appropriate action: Before further flight, 

contact Airbus for a repair solution, and do 

the repair; or repair the cracking using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, or EASA or its 

delegated agent. As of the effective date of 

this AD, only Revision 04 of these service 

bulletins may be used. 

New Requirements of This AD: 

Terminating Action 

(q) Within 30 months after the effective 

date of this AD: Modify the spot-faces around 

all the fastener holes at locations 43, 47 to 

50, 52, and 54 (except for spot-faces of holes 

which have been previously repaired) on the 

bottom flange MLG ribs, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0254, 

Revision 01, including Appendix 1, dated 

June 14, 2011; or Airbus Mandatory Service 

Bulletin A300–57–6110, Revision 01, 

including Appendix 1, dated June 6, 2011; as 

applicable. Accomplishing this modification 

terminates the repetitive inspection 

requirements of paragraph (p)(4) of this AD. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(r) Modifying the spot-faces before the 

effective date of this AD, in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–57–0254, 

dated June 4, 2010; or Airbus Mandatory 

Service Bulletin A300–57–6110, dated June 

7, 2010; as applicable; is considered 

acceptable for compliance with the 

requirements of paragraph (q) of this AD. 

FAA AD Differences 

Note 4: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(s) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 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. AMOCs approved previously in 

accordance with AD 2000–05–07, 

Amendment 39–11616 (65 FR 12077, March 

8, 2000); AD 2006–12–13, Amendment 39– 

14639 (69 FR 54063, September 7, 2004); and 

AD 2010–23–26, Amendment 39–16516 (75 

FR 74610, December 1, 2010), are approved 

as AMOCs for the corresponding provisions 

of 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 

(t) Refer to MCAI EASA Airworthiness 

Directive 2011–0029, dated February 24, 

2011; and the service information specified 

in Table 7 of this AD, for related information. 

TABLE 7—RELATED SERVICE INFORMATION

Airbus— Revision— Dated— 

Mandatory Service Bulletin A300–57A0246 ......................... 04, including Appendices 1 and 2 ....................................... September 9, 2009. 

Mandatory Service Bulletin A300–57–0254 .......................... 01 ......................................................................................... June 14, 2011. 

Mandatory Service Bulletin A300–57A6101 ......................... 04, including Appendices 1 and 2 ....................................... September 9, 2009. 

Mandatory Service Bulletin A300–57–6110 .......................... 01 ......................................................................................... June 6, 2011. 

Service Bulletin A300–57A0234 ............................................ 02 ......................................................................................... June 24, 1999. 

03, including Appendix 01 ................................................... September 2, 1999. 

04, including Appendix 01 ................................................... May 19, 2000. 

05, including Appendix 01 ................................................... February 19, 2002. 

Service Bulletin A300–57A6087 ............................................ 02, including Appendix 01 ................................................... June 24, 1999. 

03, including Appendix 01 ................................................... May 19, 2000. 

04, including Appendix 01 ................................................... February 19, 2002. 

05, including Appendix 01 ................................................... March 10, 2008. 

Service Bulletin A300–57–0235 ............................................ 04 ......................................................................................... March 13, 2003. 

05 ......................................................................................... December 3, 2003. 

Service Bulletin A300–57–6088 ............................................ 04 ......................................................................................... December 3, 2003. 

Issued in Renton, Washington, on 

September 30, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–26113 Filed 10–7–11; 8:45 am] 

BILLING CODE 4910–13–P 

CONSUMER PRODUCT SAFETY 

COMMISSION 

16 CFR Chapter II 

[Docket No. CPSC–2011–0074] 

Table Saw Blade Contact Injuries; 

Advance Notice of Proposed 

Rulemaking; Request for Comments 

and Information 

AGENCY: Consumer Product Safety 

Commission. 

ACTION: Advance notice of proposed 

rulemaking. 

SUMMARY: The Consumer Product Safety 

Commission (‘‘CPSC’’ or ‘‘Commission’’ 

or ‘‘we’’) is considering whether a new 

performance safety standard is needed 

to address an unreasonable risk of injury 

associated with table saws. We are 

conducting this proceeding under the 

authority of the Consumer Product 

Safety Act (‘‘CPSA’’), 15 U.S.C. 2051– 

2084. This advance notice of proposed 

rulemaking (‘‘ANPR’’) invites written 

comments from interested persons 


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