Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 66659 

a new airworthiness directive (AD), 

Amendment 39 16486, to read as 

follows: 

2010–22–07 Eurocopter Deutschland 

GmbH: Amendment 39–16486; Docket 

No. FAA–2010–0780; Directorate 

Identifier 2009–SW–68–AD. Supersedes 

AD 2006–26–51, Amendment 39 14961, 

Docket No. FAA–2006–26721, 

Directorate Identifier 2006–SW–28–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on December 3, 2010. 

Other Affected ADs 

(b) This AD supersedes AD 2006–26–51, 

Amendment 39–14961, Docket No. FAA 

2006–26721, Directorate Identifier 2006–SW– 

28–AD. 

Applicability 

(c) This AD applies to Model MBB–BK 117 

C–2 helicopters with a tail rotor control lever 

B642M1009103, installed, certificated in any 

category. 

Reason 

(d) The mandatory continued 

airworthiness information (MCAI) AD states: 

‘‘European Aviation Safety Agency (EASA) 

was informed by the manufacturer of an inflight incident in which a dynamic weight 

broke off the control lever subsequently 

leading to considerable vibrations. A visual 

inspection revealed that the threaded bolt of 

the control lever had broken off.’’ This AD 

requires actions that are intended to prevent 

separation of dynamic weights, severe 

vibration, and subsequent loss of control of 

the helicopter. 

Actions and Compliance 

(e) Before further flight, unless already 

done, mark the position of the weights, 

remove the split pins, remove the weights, 

and visually inspect the tail rotor control 

lever in the area around the split pin bore for 

score marks, notching, scratching, or a crack. 

Inspect by following the Accomplishment 

Instructions, paragraph 3.A.(1) through 

3.A.(3) and Figure 1, of Eurocopter Alert 

Service Bulletin MBB BK 117 C–2–64A–002, 

Revision 2, dated August 6, 2007 (ASB). 

(1) If done previously, within the next 8 

hours time-in-service (TIS) or before reaching 

25 hours TIS after the last inspection, and 

thereafter at intervals not to exceed 8 hours 

TIS, repeat the visual inspection of the tail 

rotor control lever as required by paragraph 

(e) of this AD. 

(2) If you find a score mark, a notch, or a 

scratch that exceeds the maintenance manual 

limits, or find a crack, before further flight: 

(i) Replace the tail rotor control lever with 

an airworthy tail rotor control lever; and 

(ii) Reidentify the tail rotor head, head 

assembly, and drive system with the new 

part numbers by following the 

Accomplishment Instructions, paragraph 

3.B.(1) through 3.B.(8) and 3.C.(1) through 

3.C.(2), of the ASB. 

(f) Within 100 hours TIS, unless already 

done, replace the control levers and 

reidentify the tail rotor head, head assembly, 

and drive system with the new part numbers 

by following the Accomplishment 

Instructions, paragraph 3.B.(1) through 

3.B.(8) and 3.C.(1) through 3.C.(2), of the 

ASB. 

(g) Replacing the control levers and 

reidentifying the part numbers is terminating 

action for the requirements of this AD. 

Differences Between the FAA AD and the 

MCAI AD 

(h) We refer to flight hours as hours TIS. 

We do not refer to a date of October 31, 2007, 

for replacing the levers because the date has 

passed. 

Other Information 

(i) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, ATTN: DOT/FAA Southwest Region, 

Sharon Miles, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, Regulations 

and Policy Group, 2601 Meacham Blvd., Fort 

Worth, Texas 76137, telephone (817) 222– 

5122, fax (817) 222 5961, has the authority 

to approve AMOCs for this AD, if requested, 

using the procedures found in 14 CFR 39.19. 

(j) Special flight permits are prohibited. 

Related Information 

(k) MCAI EASA Airworthiness Directive 

No. 2006–0237, dated August 31, 2007, 

which supersedes EASA Emergency AD 

2007–0189–E, dated July 12, 2007, contains 

related information. 

Joint Aircraft System/Component Code 

(l) The Joint Aircraft System/Component 

Code is 6400: Tail rotor system-control lever. 

Material Incorporated by Reference 

(m) The actions shall be done in 

accordance with the specified portions of 

Eurocopter Deutschland GmbH Alert Service 

Bulletin MBB BK117 C–2–64A–002, Revision 

2, dated August 6, 2007. The Director of the 

Federal Register approved this incorporation 

by reference in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, Texas 75053–4005, telephone (972) 

641–3460, fax (972) 641–3527. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas, or 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 Fort Worth, Texas, on October 12, 

2010. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–26563 Filed 10–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0680; Directorate 

Identifier 2008–NM–195–AD; Amendment 

39–16482; AD 2010–22–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

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: 

Analysis performed in the frame of the 

Extended Service Goal has led Airbus to 

modify the inspection programme 

[modification of thresholds, intervals and 

associated configurations] which is currently 

required by DGAC (Direction Ge ́ne ́rale de 

l’Aviation Civile) France AD F–2005–001. 

This modified inspection programme is 

necessary to detect and prevent damage 

associated with a structural fatigue 

phenomenon of the rear spar internal angle 

and the tee fitting located in the centre wing 

box. This condition, if not corrected, could 

affect the structural integrity of the centre 

wing box. 

* * * * * 

The unsafe condition is reduced 

structural integrity of the wings. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

December 3, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 3, 2010. 

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, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

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66660 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 

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 July 13, 2010 (75 FR 39863), 

and proposed to supersede AD 2006– 

09–05, Amendment 39–14575 (71 FR 

25921, May 3, 2006). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Analysis performed in the frame of the 

Extended Service Goal has led Airbus to 

modify the inspection programme 

[modification of thresholds, intervals and 

associated configurations] which is currently 

required by DGAC (Direction Ge ́ne ́rale de 

l’Aviation Civile) France AD F–2005–001 

[which corresponds to FAA AD 2006–09–05]. 

This modified inspection programme is 

necessary to detect and prevent damage 

associated with a structural fatigue 

phenomenon of the rear spar internal angle 

and the tee fitting located in the centre wing 

box. This condition, if not corrected, could 

affect the structural integrity of the centre 

wing box. 

For the reason stated above, this new 

EASA AD retains the requirements of DGAC 

France AD F–2005–001, which is 

superseded, and refers to the latest revision 

of Airbus Service Bulletin (SB) A310–57– 

2047. 

The unsafe condition is reduced 

structural integrity of the wings. This 

AD retains the requirements of AD 

2006–09–05, but with certain reduced 

compliance times. The required actions 

include doing repetitive rotating probe 

inspections for any crack of the rear spar 

internal angle and the left and right 

sides of the tee fitting, and doing related 

investigative/corrective actions if 

necessary. The actions also include 

modifying the holes in the internal 

angle and tee fitting by cold expansion. 

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 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 

Based on the service information, we 

estimate that this AD will affect about 

66 products of U.S. registry. 

The actions that are required by AD 

2006–09–05 and retained in this AD 

take up to 600 work-hours per product, 

at an average labor rate of $85 per work 

hour. Required parts cost up to $38,900 

per product. Based on these figures, the 

estimated cost of the currently required 

actions is up to $89,900 per product. 

This new AD adds no new costs to 

affected operators; the manufacturer has 

modified the inspection program 

currently required by AD 2006–09–05. 

This AD reduces the compliance times 

required by the existing AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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. 

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 39–14575 (71 FR 

25921, May 3, 2006) and adding the 

following new AD: 

2010–22–03 Airbus: Amendment 39–16482. 

Docket No. FAA–2010–0680; Directorate 

Identifier 2008–NM–195–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 3, 2010. 

Affected ADs 

(b) This AD supersedes AD 2006–09–05, 

Amendment 39–14575. This AD also affects 

certain requirements of AD 98–26–01, 

Amendment 39–10942. 

Applicability 

(c) This AD applies to all Airbus Model 

A310–203, –204, –221, –222, –304, –322, 

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Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 66661 

–324, and –325 airplanes, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Analysis performed in the frame of the 

Extended Service Goal has led Airbus to 

modify the inspection programme 

[modification of thresholds, intervals and 

associated configurations] which is currently 

required by DGAC (Direction Ge ́ne ́rale de 

l’Aviation Civile) France AD F–2005–001 

[which corresponds to FAA AD 2006–09–05]. 

This modified inspection programme is 

necessary to detect and prevent damage 

associated with a structural fatigue 

phenomenon of the rear spar internal angle 

and the tee fitting located in the centre wing 

box. This condition, if not corrected, could 

affect the structural integrity of the centre 

wing box. 

* * * * * 

The unsafe condition is reduced structural 

integrity of the wings. 

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 Certain Requirements of AD 

2006–09–05 

Modification 

(g) For all airplanes except those that are 

modified by Airbus Modifications 

06672S6812, 06673S6813, and 07387S7974 

in production: Within 60 months after June 

7, 2006 (the effective date of AD 2006–09– 

05), modify the holes in the internal angle 

and tee fitting and do all applicable related 

investigative and corrective actions by 

accomplishing all the actions specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2035, Revision 08, 

dated September 19, 2005; or Airbus 

Mandatory Service Bulletin A310–57–2035, 

Revision 10, dated March 25, 2008; except as 

required by paragraph (h) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. As of 

the effective date of this AD, use only Airbus 

Mandatory Service Bulletin A310–57–2035, 

Revision 10, dated March 25, 2008. 

Contact the FAA 

(h) Where the service information specified 

in Table 1 of this AD specifies to contact the 

manufacturer if certain cracks are found, 

before further flight, repair those conditions 

according to a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent); or EASA (or 

its delegated agent). 

TABLE 1—SERVICE INFORMATION

Document Revision Date 

Airbus Mandatory Service Bulletin A310–57–2035 .............................................................................................. 10 March 25, 2008. 

Airbus Service Bulletin A310–57–2035 ................................................................................................................ 08 September 19, 2005. 

Actions Accomplished According to 

Previous Issues of Airbus Service Bulletin 

A310–57–2035 

(i) Actions accomplished before June 7, 

2006, in accordance with the service 

information specified in Table 2 of this AD, 

are considered acceptable for compliance 

with the corresponding actions specified in 

paragraph (g) of this AD. 

TABLE 2—PREVIOUS ISSUES OF SERVICE BULLETIN A310–57–2035 

Document Revision Date 

Airbus Service Bulletin A310–57–2035 .................................................................................................................. 1 October 13, 1989. 

Airbus Service Bulletin A310–57–2035 .................................................................................................................. 2 February 26, 1990. 

Airbus Service Bulletin A310–57–2035 .................................................................................................................. 3 May 23, 1990. 

Airbus Service Bulletin A310–57–2035 .................................................................................................................. 4 April 15, 1992. 

Airbus Service Bulletin A310–57–2035 .................................................................................................................. 5 May 27, 1992. 

Airbus Service Bulletin A310–57–2035 .................................................................................................................. 6 March 8, 1994. 

Airbus Service Bulletin A310–57–2035 .................................................................................................................. 7 April 17, 1996. 

New Requirements of This AD—Revised 

Compliance Times for Inspections Required 

by AD 2006–09–05 

Initial and Repetitive Inspections of the Rear 

Spar Internal Angle 

(j) For airplanes on which an inspection of 

the rear spar internal angle has not been done 

in accordance with Airbus Service Bulletin 

A310–57–2047 as of the effective date of this 

AD: At the later of the times specified in 

paragraphs (j)(1) and (j)(2) of this AD, do a 

rotating probe inspection for any crack of the 

rear spar internal angle located in the center 

wing box and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2047, Revision 08, dated July 2, 2009; 

except as required by paragraphs (n) and (o) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection 

thereafter at the applicable time specified in 

Table 4 of this AD. Certain compliance times 

are applicable to short range use, average 

flight time (AFT) equal to or less than 4 

hours, or long range use, AFT exceeding 4 

hours. 

Note 1: To establish the AFT, divide the 

accumulated flight time (counted from the 

take-off up to the landing) by the number of 

accumulated flight cycles. This gives the 

average flight time per flight cycle. 

(1) Within the applicable time specified in 

Table 3 of this AD. 

(2) Within the applicable time specified in 

paragraph (j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this 

AD: 

(i) For A310–203, –204, –221, and –222 

airplanes: Within 700 flight cycles or 1,500 

flight hours after the effective date of this AD, 

whichever occurs first. 

(ii) For A310–304, –322, –324, and –325 

short range airplanes: Within 700 flight 

cycles or 1,900 flight hours after the effective 

date of this AD, whichever occurs first. 

(iii) For A310–304, –322, –324, and –325 

long range airplanes: Within 500 flight cycles 

or 2,500 flight hours after the effective date 

of this AD, whichever occurs first. 

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TABLE 3—INITIAL INSPECTION INTERNAL ANGLE

Model and configuration Compliance time (whichever occurs first) 

A310–203, –204, –221, and –222 airplanes on which Mod 6672S6812 

and Mod 7387S7974 are not done.

Before the accumulation of 9,200 

total flight cycles.

Before the accumulation of 18,500 

total flight hours. 

A310–203, –204, –221, and –222 airplanes on which Mod 6672S6812 

and Mod 7387S7974 are done in production.

Before the accumulation of 19,800 

total flight cycles.

Before the accumulation of 39,600 

total flight hours. 

A310–203, –204, –221, and –222 airplanes on which Mod 6672S6812 

and Mod 7387S7974 are done in accordance with Airbus Service 

Bulletin A310–57–2035 and before the accumulation of 6,200 total 

flight cycles and 12,500 total flight hours.

Within 19,800 flight cycles after 

the effective date of this AD.

Within 39,600 flight hours after the 

effective date of this AD. 

A310–203, –204, –221, and –222 airplanes on which Mod 6672S6812 

and Mod 7387S7974 are done in accordance with Airbus Service 

Bulletin A310–57–2035 and are not done before the accumulation of 

6,200 total flight cycles and 12,500 total flight hours.

Within 8,200 flight cycles after the 

effective date of this AD.

Within 16,400 flight hours after the 

effective date of this AD. 

A310–304, –322, –324, and –325 short range airplanes on which Mod 

6672S6812 and Mod 7387S7974 are not done.

Before the accumulation of 7,500 

total flight cycles.

Before the accumulation of 21,100 

total flight hours. 

A310–304, –322, –324, and –325 long range airplanes on which Mod 

6672S6812 and Mod 7387S7974 are not done.

Before the accumulation of 5,300 

total flight cycles.

Before the accumulation of 26,900 

total flight hours. 

A310–304, –322, –324, and –325 short range airplanes on which Mod 

6672S6812 and Mod 7387S7974 are done.

Before the accumulation of 15,900 

total flight cycles.

Before the accumulation of 44,700 

total flight hours. 

A310–304, –322, –324, and –325 long range airplanes on which Mod 

6672S6812 and Mod 7387S7974 are done in production.

Before the accumulation of 11,300 

total flight cycles.

Before the accumulation of 56,900 

total flight hours. 

A310–304, –322, –324, and –325 short range airplanes on which Mod 

6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and before the accumulation of 

4,700 total flight cycles and 13,100 total flight hours.

Within 15,900 flight cycles after 

the effective date of this AD.

Within 44,700 flight hours after the 

effective date of this AD. 

A310–304, –322, –324, and –325 short range airplanes on which Mod 

6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and not done before the accumulation of 4,700 total flight cycles and 13,100 total flight hours.

Within 8,500 flight cycles after the 

effective date of this AD.

Within 23,800 flight hours after the 

effective date of this AD. 

A310–304, –322, –324, and –325 long range airplanes on which Mod 

6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 before the accumulation of 

3,300 total flight cycles and 16,700 total flight hours.

Within 11,300 flight cycles after 

the effective date of this AD.

Within 56,900 flight hours after the 

effective date of this AD. 

A310–304, –322, –324, and –325 long range airplanes on which Mod 

6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310–57–2035 and not done before the accumulation of 3,300 total flight cycles and 16,700 total flight hours.

Within 6,000 flight cycles after the 

effective date of this AD.

Within 30,300 flight hours after the 

effective date of this AD. 

TABLE 4—REPETITIVE INTERVALS

Model and configuration Interval (not to exceed) 

A310–203, –204, –221, and –222 airplanes ............................................ Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first. 

A310–304, –322, –324, and –325 short range airplanes ........................ Within 6,800 flight cycles or 19,100 flight hours, whichever occurs first. 

A310–304, –322, –324, and –325 long range airplanes ......................... Within 4,800 flight cycles or 24,300 flight hours, whichever occurs first. 

(k) For airplanes on which an inspection of 

the rear spar internal angle has been done in 

accordance with Airbus Service Bulletin 

A310–57–2047 as of the effective date of this 

AD: At the applicable time specified in 

paragraphs (k)(1), (k)(2), and (k)(3) of this AD, 

do a rotating probe inspection for any crack 

of the rear spar internal angle located in the 

center wing box and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2047, Revision 08, dated July 2, 2009; 

except as required by paragraphs (n) and (o) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection 

thereafter at the applicable time specified in 

Table 4 of this AD. Certain compliance times 

are applicable to short range use, AFT equal 

to or less than 4 hours, or long range use, 

AFT exceeding 4 hours. 

(1) For A310–203, –204, –221, and –222 

airplanes: At the earlier of the times specified 

in paragraphs (k)(1)(i) and (k)(1)(ii) of this 

AD. 

(i) Within 7,940 flight cycles or 15,880 

flight hours after the most recent inspection, 

whichever occurs first. 

(ii) At the later of the times specified in 

paragraphs (k)(1)(ii)(A) and (k)(1)(ii)(B) of 

this AD. 

(A) Within the applicable interval specified 

in Table 4 of this AD. 

(B) Within 740 flight cycles or 1,480 flight 

hours after the effective date of this AD, 

whichever occurs first. 

(2) For A310–304, –322, –324, and –325 

short range airplanes: At the later of the times 

specified in paragraphs (k)(2)(i) and (k)(2)(ii) 

of this AD. 

(i) Within the applicable interval specified 

in Table 4 of this AD. 

(ii) Within 700 flight cycles or 1,900 flight 

hours after the effective date of this AD, 

whichever occurs first. 

(3) For A310–304, –322, –324, and –325 

long range airplanes: At the later of the times 

specified in paragraphs (k)(3)(i) and (k)(3)(ii) 

of this AD. 

(i) Within the applicable interval specified 

in Table 4 of this AD. 

(ii) Within 500 flight cycles or 2,500 flight 

hours after the effective date of this AD, 

whichever occurs first. 

Initial and Repetitive Inspections of the Tee 

Fitting 

(l) For airplanes on which an inspection of 

the left and right sides of the tee fitting has 

not been done in accordance with Airbus 

Service Bulletin A310–57–2047 as of the 

effective date of this AD: At the later of the 

times specified in paragraphs (l)(1) and (l)(2) 

of this AD, do a rotating probe inspection for 

any crack of the left and right sides of the tee 

fitting, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

57–2047, Revision 08, dated July 2, 2009; 

except as required by paragraphs (n) and (o) 

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Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 66663 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspection 

thereafter at the applicable time specified in 

Table 6 of this AD. Certain compliance times 

are applicable to short range use, AFT equal 

to or less than 4 hours, or long range use, 

AFT exceeding 4 hours. 

(1) Within the applicable time specified in 

Table 5 of this AD. 

(2) Within the applicable time in paragraph 

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

(i) For A310–203, –204, –221, and –222 

airplanes: Within 800 flight cycles or 1,600 

flight hours, whichever occurs first. 

(ii) For A310–304, –322, –324, and –325 

short range airplanes: Within 800 flight 

cycles or 2,200 flight hours, whichever 

occurs first. 

(iii) For A310–304, –322, –324, and –325 

long range airplanes: Within 600 flight cycles 

or 3,100 flight hours, whichever occurs first. 

TABLE 5—INITIAL INSPECTION TEE FITTING

Model and configuration Compliance time (whichever occurs first) 

A310–203, –204, –221, and –222 airplanes on which Mod 6673S6813 

is not done.

Before the accumulation of 14,300 

flight cycles.

Within 28,700 flight hours after the 

effective date of this AD. 

A310–203, –204, –221, and –222 airplanes on which Mod 6673S6813 

is done in production.

Before the accumulation of 17,500 

total flight cycles.

Before the accumulation of 35,000 

total flight hours. 

A310–203, –204, –221, and –222 airplanes on which Mod 6673S6813 

is done in accordance with Airbus Service Bulletin A310–57–2035 

and before the accumulation of 8,100 total flight cycles and 16,200 

total flight hours.

Within 17,500 flight cycles after 

the effective date of this AD.

Within 35,000 flight hours after the 

effective date of this AD. 

A310–203, –204, –221, and –222 airplanes on which Mod 6673S6813 

is done in accordance with Airbus Service Bulletin A310–57–2035 

and not before the accumulation of 8,100 total flight cycles and 

16,200 total flight hours.

Within 9,600 flight cycles after the 

effective date of this AD.

Within 19,200 flight hours after the 

effective date of this AD. 

A310–304, –322, –324, and –325 short range airplanes on which Mod 

6673S6813 is not done.

Within 10,800 flight cycles after 

the effective date of this AD.

Within 30,400 flight hours after the 

effective date of this AD. 

A310–304, –322, –324, and –325 long range airplanes on which Mod 

6673S6813 is not done.

Before the accumulation of 8,500 

total flight cycles.

Before the accumulation of 42,800 

total flight hours. 

A310–304, –322, –324, and –325 short range airplanes on which Mod 

6673S6813 is done in production.

Before the accumulation of 13,100 

total flight cycles.

Before the accumulation of 36,700 

total flight hours. 

A310–304, –322, –324, and –325 long range airplanes on which Mod 

6673S6813 is done in production.

Before the accumulation of 10,300 

total flight cycles.

Before the accumulation of 51,600 

total flight hours. 

A310–304, –322, –324, and –325 short range airplanes on which Mod 

6673S6813 is done in accordance with Airbus Service Bulletin 

A310–57–2035 and before the accumulation of 5,800 total flight cycles and 16,400 total flight hours.

Within 13,100 flight cycles after 

the effective date of this AD.

Within 36,700 flight hours after the 

effective date of this AD. 

A310–304, –322, –324, and –325 short range airplanes on which Mod 

6673S6813 is done in accordance with Airbus Service Bulletin 

A310–57–2035 and not before the accumulation of 5,800 total flight 

cycles and 16,400 total flight hours.

Within 7,400 flight cycles after the 

effective date of this AD.

Within 20,900 flight hours after the 

effective date of this AD. 

A310–304, –322, –324, and –325 long range airplanes on which Mod 

6673S6813 is done in accordance with Airbus Service Bulletin 

A310–57–2035 and before the accumulation of 4,600 total flight cycles and 23,100 total flight hours.

Within 10,300 flight cycles after 

the effective date of this AD.

Within 51,600 flight hours after the 

effective date of this AD. 

A310–304, –322, –324, and –325 long range airplanes on which Mod 

6673S6813 is done in accordance with Airbus Service Bulletin 

A310–57–2035 and not before the accumulation of 4,600 total flight 

cycles and 23,100 total flight hours.

Within 6,000 flight cycles after the 

effective date of this AD.

Within 30,300 flight hours after the 

effective date of this AD. 

TABLE 6—REPETITIVE INTERVALS

Model and configuration Interval (not to exceed) 

A310–203, –204, –221, and –222 airplanes ................................................................................. 9,100 flight cycles or 18,300 flight hours, whichever occurs first. 

A310–304, –322, –324, and –325 short range airplanes .............................................................. 7,300 flight cycles or 20,400 flight hours, whichever occurs first. 

A310–304, –322, –324, and –325 long range airplanes ............................................................... 5,900 flight cycles or 29,600 flight hours, whichever occurs first. 

(m) For airplanes on which an inspection 

of the rear left and right sides of the tee 

fitting has been done in accordance with 

Airbus Service Bulletin A310–57–2047 as of 

the effective date of this AD: At the 

applicable time specified in paragraphs 

(m)(1) or (m)(2) of this AD, do a rotating 

probe inspection for any crack of the left and 

right sides of the tee fitting, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2047, Revision 08, 

dated July 2, 2009; except as required by 

paragraphs (n) and (o) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the inspection thereafter at the 

applicable time specified in Table 6 of this 

AD. Certain compliance times are applicable 

to short range use, AFT equal to or less than 

4 hours, or long range use, AFT exceeding 4 

hours. 

(1) For A310–203, –204, –221, and –222 

airplanes: At the earlier of the times specified 

in paragraphs (m)(1)(i) and (m)(1)(ii) of this 

AD. 

(i) Within 10,800 flight cycles or 17,400 

flight hours after the most recent inspection, 

whichever occurs first. 

(ii) At the later of the times specified in 

paragraphs (m)(1)(ii)(A) and (m)(1)(ii)(B) of 

this AD. 

(A) Within the applicable interval specified 

in Table 6 of this AD. 

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66664 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 

(B) Within 700 flight cycles or 1,500 flight 

hours after the effective date of this AD, 

whichever occurs first. 

(2) For A310–304, –322, –324, and – 325 

airplanes: At the later of the times specified 

in paragraphs (m)(2)(i) and (m)(2)(ii) of this 

AD. 

(i) Within the applicable interval specified 

in Table 6 of this AD. 

(ii) Within 700 flight cycles or 1,900 flight 

hours after the effective date of this AD, 

whichever occurs first. 

Contact the FAA 

(n) Where Airbus Service Bulletin A310– 

57–2047, Revision 08, dated July 2, 2009, 

specifies to contact the manufacturer if 

certain cracks are found, before further flight, 

repair those conditions according to a 

method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent). 

No Reporting Required 

(o) Although Airbus Service Bulletin 

A310–57–2047, Revision 08, dated July 2, 

2009, specifies to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 

(p) Actions accomplished before the 

effective date of this AD in accordance with 

Airbus Mandatory Service Bulletin A310–57– 

2035, Revision 09, dated September 27, 2007, 

are considered acceptable for compliance 

with the corresponding actions specified in 

paragraph (g) of this AD. 

(q) Actions accomplished before the 

effective date of this AD in accordance with 

the service information specified in Table 7 

of this AD, are considered acceptable for 

compliance with the corresponding actions 

specified in paragraphs (j) through (m) of this 

AD. 

TABLE 7—PREVIOUS ISSUES OF AIRBUS SERVICE BULLETIN A310–57–2047 

Document Revision Date 

Airbus Service Bulletin A310–57–2047 ..................................................................................................... 03 November 26, 1997. 

Airbus Service Bulletin A310–57–2047 ..................................................................................................... 04 March 5, 1999. 

Airbus Service Bulletin A310–57–2047 ..................................................................................................... 05 August 3, 2000. 

Airbus Service Bulletin A310–57–2047 ..................................................................................................... 06 July 13, 2004. 

Airbus Service Bulletin A310–57–2047 ..................................................................................................... 07 March 14, 2008. 

Related AD 

(r) Accomplishing a rotating probe 

inspection of the rear spar internal angle and 

the tee fitting in accordance with Airbus 

Service Bulletin A310–57–2047, Revision 08, 

dated July 2, 2009, or a service bulletin listed 

in Table 7 of this AD, terminates the 

requirements specified in paragraph (o) of 

AD 98–26–01. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

Although the MCAI or service information 

tells you to contact the manufacturer for 

repair information, paragraph (n) of this AD 

requires that you contact the FAA or EASA 

(or its delegated agent) instead. 

Although the MCAI or service information 

tells you to submit information to the 

manufacturer, paragraph (o) of this AD 

specifies that such submittal is not required. 

Other FAA AD Provisions 

(s) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; 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) AMOCs approved previously in 

accordance with AD 2006–09–05, 

Amendment 39–14575, are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(3) 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 2008–0187, dated October 10, 2008; 

Airbus Service Bulletin A310–57–2047, 

Revision 08, dated July 2, 2009; and Airbus 

Mandatory Service Bulletin A310–57–2035, 

Revision 10, dated March 25, 2008; for 

related information. 

Material Incorporated by Reference 

(u) You must use Airbus Mandatory 

Service Bulletin A310–57–2035, Revision 10, 

dated March 25, 2008; and Airbus Service 

Bulletin A310–57–2047, Revision 08, dated 

July 2, 2009; as applicable; to do the actions 

required by this AD, unless the AD specifies 

otherwise. Airbus Service Bulletin A310–57– 

2047 contains the following effective pages: 

Page No. 

Revision 

level 

shown on 

page 

Date shown on page 

1–7a, 26, 86, 88 ........................................................................................................................................... 08 ................ July 2, 2009. 

7b–21, 26, 29–31, 33, 35, 38, 39, 44, 45, 95, 96 ........................................................................................ 07 ................ March 14, 2008. 

22–25, 37 ..................................................................................................................................................... 06 ................ July 13, 2004. 

27, 28, 36, 47–56, 61–74 ............................................................................................................................. Original ........ February 26, 1991. 

32, 34, 40–43, 59–60, 81–85, 87, 89–94 .................................................................................................... 04 ................ March 5, 1999. 

46, 75–80 ..................................................................................................................................................... 05 ................ August 3, 2000. 

57, 58 ........................................................................................................................................................... 2 .................. January 22, 1997. 

(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 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. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

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Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations 66665 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) 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 October 

13, 2010. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–26659 Filed 10–28–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

Bureau of Ocean Energy Management, 

Regulation, and Enforcement 

30 CFR Parts 201, 202, 203, 204, 206, 

207, 208, 210, 212, 217, 218, 219, 220, 

227, 228, 229, 241, 243, and 290 

Office of Natural Resources Revenue 

30 CFR Parts 1201, 1202, 1203, 1204, 

1206, 1207, 1208, 1210, 1212, 1217, 

1218, 1219, 1220, 1227, 1228, 1229, 

1241, 1243, and 1290 

[Docket No. MMS–2010–MRM–0033] 

RIN 1010–AD70 

Reorganization of Title 30, Code of 

Federal Regulations 

In rule document 2010–24721 

beginning on page 61051 in the issue of 

Monday, October 4, 2010, make the 

following corrections: 

PART 1206—PRODUCT VALUATION 

[CORRECTED] 

1. On page 61070, in the table, in the 

first column, in the fourth row, 

‘‘§ 1206.52(c)(2)’’ should read 

‘‘§ 1206.52(c)(2)(i)’’. 

2. On the same page, in the same 

table, in the same column, in the 

eleventh row, ‘‘§ 1206.53(e)(5) two 

times’’ should read ‘‘1206.52(e)(5) two 

times’’. 

3. On the same page, in the same 

table, in the same column, in both the 

fifteenth and sixteenth rows, 

‘‘§ 1206.52(c) introductory text’’ should 

read ‘‘§ 1206.53(c) introductory text’’. 

4. On page 61071, in the table, in the 

third column, in the eighteenth row 

from the bottom of the page, ‘‘part 207’’ 

should read ‘‘part 1207.’’ 

5. On the same page, in the same 

table, in the same column, in the 

seventh row from the bottom of the 

page, the blank entry should read 

‘‘ONRR.’’ 

6. On page 61072, in the table, in the 

third column, in the 22nd row, the 

blank entry should read ‘‘§ 1206.111’’. 

7. On page 61073, in the table, in the 

third column, in the 16th row, 

‘‘Associate Director’’ should read 

‘‘Director’’. 

PART 1208—SALE OF FEDERAL 

ROYALTY OIL [CORRECTED] 

8. On page 61081, in the table, in the 

third column, in the first row, 

‘‘§ 208.8(a)’’ should read ‘‘§ 1208.8(a)’’. 

9. On the same page, in the same 

table, in the same column, in the fifth 

row, ‘‘§ 208.7(g)’’ should read 

‘‘§ 1208.7(g)’’. 

[FR Doc. C1–2010–24721 Filed 10–28–10; 8:45 am] 

BILLING CODE 4310–MR–W–P 

DEPARTMENT OF EDUCATION 

34 CFR Part 600 

RIN 1840–AD04 

[Docket ID ED–2010–OPE–0012] 

Program Integrity: Gainful 

Employment—New Programs 

AGENCY: Office of Postsecondary 

Education, Department of Education. 

ACTION: Final regulations. 

SUMMARY: The Secretary amends the 

regulations for Institutional Eligibility 

Under the Higher Education Act of 

1965, as amended (HEA), to establish a 

process under which an institution 

applies for approval to offer an 

educational program that leads to 

gainful employment in a recognized 

occupation. 

DATES: These regulations are effective 

July 1, 2011. However, affected parties 

do not have to comply with the 

information collection requirements in 

§ 600.20(d) until the Department of 

Education publishes in the Federal 

Register the control number assigned by 

the Office of Management and Budget 

(OMB) to these information collection 

requirements. Publication of the control 

number notifies the public that OMB 

has approved these information 

collection requirements under the 

Paperwork Reduction Act of 1995. 

FOR FURTHER INFORMATION CONTACT: John 

Kolotos or Fred Sellers. Telephone: 

(202) 502–7762 or (202) 502–7502, or 

via the Internet at: John.Kolotos@ed.gov 

or Fred.Sellers@ed.gov. 

If you use a telecommunications 

device for the deaf (TDD), call the 

Federal Relay Service (FRS), toll free, at 

1–800–877–8339. 

Individuals with disabilities can 

obtain this document in an accessible 

format (e.g., braille, large print, 

audiotape, or computer diskette) on 

request to one of the contact persons 

listed under FOR FURTHER INFORMATION

CONTACT. 

SUPPLEMENTARY INFORMATION: On July 

26, 2010, the Secretary published a 

notice of proposed rulemaking (NPRM) 

for gainful employment issues in the 

Federal Register (75 FR 43616). 

In the preamble to the NPRM, the 

Secretary discussed on pages 43617 

through 43624 the major regulations 

proposed in that document to establish 

measures for determining whether 

certain programs lead to gainful 

employment in recognized occupations 

and the conditions under which those 

programs remain eligible for title IV, 

HEA program funds. In these final 

regulations, we address in a limited way 

only one issue from the proposed 

regulations: The provisions relating to 

the Secretary’s approval of additional 

programs. The remaining issues will be 

addressed in final regulations that we 

intend to publish in the next few 

months. 

Implementation Date of These 

Regulations 

Section 482(c) of the HEA requires 

that regulations affecting programs 

under title IV of the HEA be published 

in final form by November 1 prior to the 

start of the award year (July 1) to which 

they apply. However, that section also 

permits the Secretary to designate any 

regulation as one that an entity subject 

to the regulation may choose to 

implement earlier and to specify the 

conditions under which the entity may 

implement the provisions early. 

The Secretary has not designated any 

of the provisions in these final 

regulations for early implementation. 

Analysis of Comments and Changes 

These final regulations were 

developed through the use of negotiated 

rulemaking. Section 492 of the HEA 

requires that, before publishing any 

proposed regulations to implement 

programs under title IV of the HEA, the 

Secretary must obtain public 

involvement in the development of the 

proposed regulations. After obtaining 

advice and recommendations, the 

Secretary must conduct a negotiated 

rulemaking process to develop the 

proposed regulations. The negotiated 

rulemaking committee did not reach 

WReier-Aviles on DSKGBLS3C1PROD with RULES