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

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

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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.


## 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,


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

–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—S ERVICE 

### I NFORMATION

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—P REVIOUS 

### I SSUES OF 

### S ERVICE 

### B ULLETIN 

### 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.


## 66662 Federal Register / Vol. 75, No. 209 / Friday, October 29, 2010 / Rules and Regulations

TABLE 

### 3—I NITIAL 

### I NSPECTION 

### I NTERNAL 

### A NGLE

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—R EPETITIVE 

### I NTERVALS

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)


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

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—I NITIAL 

### I NSPECTION 

### T EE 

### F ITTING

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 BulletinA310–57–2035 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 BulletinA310–57–2035 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—R EPETITIVE 

### I NTERVALS

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.


## 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—P REVIOUS 

### I SSUES OF 

### A IRBUS 

### S ERVICE 

### B ULLETIN 

### 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


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

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