74610 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No. 2010–0099, 

dated May 26, 2010; and Socie ́te ́ Nouvelle 

Centrair Service Bulletin No. 101–29, dated 

July 30, 2009, for related information. 

Material Incorporated by Reference 

(i) You must use Socie ́te ́ Nouvelle Centrair 

Service Bulletin No. 101–29, dated July 30, 

2009, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Socie ́te ́ Nouvelle 

CENTRAIR, Aerodome—36300 Le Blanc, 

France; telephone: +33 (0)254 370796; fax: 

+33 (0)54. 374864; Internet: http:// 

www.societe.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/ibr_

locations.html. 

Issued in Kansas City, Missouri, on 

November 17, 2010. 

Patrick R. Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–29461 Filed 11–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1067; Directorate 

Identifier 2009–NM–071–AD; Amendment 

39–16516; AD 2010–23–26] 

RIN 2120–AA64 

Airworthiness Directives; 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 

AGENCY: Federal Aviation 

Administration, Department of 

Transportation. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This 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) 

[parallel to part of FAA AD 2006–12–13] 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. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

January 5, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 5, 2011. 

On July 18, 2006 (71 FR 33994, June 

13, 2006), the Director of the Federal 

Register approved the incorporation by 

reference of certain other publications 

listed in this AD. 

On April 12, 2000 (65 FR 12077, 

March 8, 2000), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 18, 2009 (74 FR 

59483), and proposed to supersede AD 

2006–12–13, Amendment 39–14639 (71 

FR 33994, June 13, 2006). That NPRM 

proposed 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) 

[parallel to part of FAA AD 2006–12–13] 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]. 

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, AD 2009– 

0081 superseded EASA AD 2008–0111 and 

required operators to comply with the new 

inspection programme introduced in 

WReier-Aviles on DSKGBLS3C1PROD with RULES

Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations 74611 

Revisions 3 of Airbus SB A300–57A0246 and 

Airbus SB A300–57A6101. 

This AD is revised to introduce an optional 

terminating action which consists of spotfacing the sensitive holes of the MLG Rib 5 

(LH and RH) bottom flanges. 

Required actions include contacting 

Airbus for repair instructions, if 

necessary, and doing the repair. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Revise Proposed Costs of 

Compliance 

FedEx Express commented that the 

NPRM would affect 57 of its airplanes. 

FedEx Express states that the 

inspections do not require any special 

inspection techniques, training, or 

tooling, and that it has scheduled the 

proposed inspections although it has 

not yet inspected any airplanes. FedEx 

Express also states that the inspection 

interval is sufficient, but if cracks are 

found, significant downtime will be 

required. 

From these comments, we infer that 

FedEx Express is requesting that we 

revise the Costs of Compliance section 

of the NPRM. We do not agree with the 

request. We recognize that, in 

accomplishing the requirements of any 

AD, operators might incur ‘‘incidental’’ 

costs in addition to the ‘‘direct’’ costs 

that are reflected in the cost analysis 

presented in the AD preamble. 

However, the cost analysis in AD 

rulemaking actions typically does not 

include incidental costs. We have, 

however, reviewed the figures that we 

have used over the past several years to 

calculate costs to operators. To account 

for various inflationary costs in the 

airline industry, we find it necessary to 

increase the labor rate used in these 

calculations from $80 per work hour to 

$85 per work hour. The cost impact 

information, below, reflects this 

increase in the specified hourly rate. We 

have also corrected the calculations 

used in determining the cost to 

operators. 

Explanation of Change to the NPRM 

Paragraph (p)(5) of the NPRM 

specifies contacting Airbus for a repair 

solution and doing the repair. The 

European Aviation Safety Agency 

(EASA) has assumed responsibility for 

the airplane models subject to this AD. 

Therefore, we have revised paragraph 

(p)(5) of this AD to add a provision for 

making repairs using a method 

approved by either the Manager of the 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA or 

the EASA (or its delegated agent). 

Explanation of Change to AD 

We have revised paragraphs (j) and (k) 

of this AD; and Tables 1, 2, 3, 4, and 5 

of this AD to remove Airbus Model 

A300 B2–1A, F4–622R, and C4–605R 

Variant F airplanes. We have 

determined that these airplanes were 

inadvertently carried over from the 

paragraph callouts of the previous AD 

into the NPRM. These airplanes are not 

subject to the identified unsafe 

condition and therefore are not affected 

by this AD. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 155 products of U.S. registry. 

The actions that are required by AD 

2006–12–13 and retained in this AD 

take about 76 work-hours 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 $16,730 per product. 

We estimate that it will take about 3 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $39,525 or $255 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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

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 AD and placed it in the AD docket. 

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 the NPRM, 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. 

WReier-Aviles on DSKGBLS3C1PROD with RULES

74612 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–14639 (71 FR 

33994, June 13, 2006) and adding the 

following new AD: 

2010–23–26 Airbus: Amendment 39–16516. 

Docket No. FAA–2009–1067; Directorate 

Identifier 2009–NM–071–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 5, 2011. 

Affected ADs 

(b) This AD supersedes AD 2006–12–13, 

Amendment 39–14639. 

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) 

[parallel to part of FAA AD 2006–12–13] 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]. 

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, 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. 

This AD is revised to introduce an optional 

terminating action which consists of spotfacing the sensitive holes of the MLG Rib 5 

(LH and RH) bottom flanges. 

Required actions include contacting Airbus 

for repair instructions, if necessary, and 

doing the repair. 

Restatement of Requirements of AD 2000– 

05–07 

(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 

(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), 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 

level— 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 level— 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. 

WReier-Aviles on DSKGBLS3C1PROD with RULES

Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations 74613 

(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): 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 

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), 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), 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 level— 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 

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), 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 level— 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. 

WReier-Aviles on DSKGBLS3C1PROD with RULES

74614 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations 

(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. 

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 level— 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 level— 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. 

New Requirements 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. 

(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 the effective date of this AD, 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. 

(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– 

WReier-Aviles on DSKGBLS3C1PROD with RULES

Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations 74615 

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

or Revision 04, dated September 9, 2009; as 

applicable. 

(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. 

(q) Spot-facing the sensitive holes on the 

bottom flange MLG ribs, 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; terminates the 

repetitive inspection requirements of 

paragraph (p)(4) 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 

(r) 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. 

Send information 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. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards 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 

(s) Refer to MCAI EASA Airworthiness 

Directive 2009–0081R1, dated July 30, 2010, 

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 ....................... 03, including Appendices 1 and 2 ..................................... March 11, 2009. 

04, including Appendices 1 and 2 ..................................... September 9, 2009. 

Mandatory Service Bulletin A300–57–0254 ....................... 0, including Appendix 1 ..................................................... June 4, 2010. 

Mandatory Service Bulletin A300–57A6101 ....................... 03, including Appendixes 1 and 2 ..................................... March 11, 2009. 

04, including Appendices 1 and 2 ..................................... September 9, 2009. 

Mandatory Service Bulletin A300–57–6110 ....................... 0, including Appendix 1 ..................................................... June 7, 2010. 

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. 

Material Incorporated by Reference 

(t) You must use the service information 

specified in Table 8 of this AD to do the 

actions required by this AD, as applicable, 

unless the AD specifies otherwise. 

TABLE 8—ALL MATERIAL INCORPORATED BY REFERENCE

Airbus— Revision— Dated— 

Mandatory Service Bulletin A300–57A0246 ....................... 03, including Appendices 1 and 2 ..................................... March 11, 2009. 

04, including Appendices 1 and 2 ..................................... September 9, 2009. 

Mandatory Service Bulletin A300–57–0254 ....................... 0, including Appendix 1 ..................................................... June 4, 2010. 

Mandatory Service Bulletin A300–57A6101 ....................... 03, including Appendices 1 and 2 ..................................... March 11, 2009. 

04, including Appendices 1 and 2 ..................................... September 9, 2009. 

Mandatory Service Bulletin A300–57–6110 ....................... 0, including Appendix 1 ..................................................... June 7, 2010. 

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 05 ................................................. 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. 

WReier-Aviles on DSKGBLS3C1PROD with RULES

74616 Federal Register / Vol. 75, No. 230 / Wednesday, December 1, 2010 / Rules and Regulations 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 9 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 9—NEW MATERIAL INCORPORATED BY REFERENCE

Airbus— Revision— Dated— 

Mandatory Service Bulletin A300–57A0246 ....................... 03, including Appendices 1 and 2 ..................................... March 11, 2009. 

04, including Appendices 1 and 2 ..................................... September 9, 2009. 

Mandatory Service Bulletin A300–57–0254 ....................... Original ............................................................................... June 4, 2010. 

Mandatory Service Bulletin A300–57A6087 ....................... 05, including Appendix 1 ................................................... March 10, 2008. 

Mandatory Service Bulletin A300–57A6101 ....................... 03, including Appendices 1 and 2 ..................................... March 11, 2009. 

04, including Appendices 1 and 2 ..................................... September 9, 2009. 

Mandatory Service Bulletin A300–57–6110 ....................... 0, including Appendix 1 ..................................................... June 7, 2010. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information specified 

in Table 10 of this AD on July 18, 2006 (71 

FR 33994, June 13, 2006). 

TABLE 10—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2006–12–13 

Airbus— Revision— Dated— 

Service Bulletin A300–57A0234 ......................................... 04, including Appendix 01 ................................................. May 19, 2000. 

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

Service Bulletin A300–57A6087 ......................................... 03, including Appendix 01 ................................................. May 19, 2000. 

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

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

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

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

(3) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information specified 

in Table 11 of this AD on April 12, 2000 (65 

FR 12077, March 8, 2000). 

TABLE 11—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE IN AD 2000–05–07 

Airbus— Revision— Dated— 

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

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

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

(4) For service information identified in 

this 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(5) You may review copies of the 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. 

(6) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

November 3, 2010. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28589 Filed 11–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28348; Directorate 

Identifier 2007–NM–060–AD; Amendment 

39–16530; AD 2010–24–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–600, –700, –700C, 

–800, and –900 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Model 737–600, –700, –700C, –800, and 

–900 series airplanes. This AD requires 

sealing the fasteners on the front and 

WReier-Aviles on DSKGBLS3C1PROD with RULES