## 23572 Federal Register / Vol. 75, No. 85 / Tuesday, May 4, 2010 / Rules and Regulations

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

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 that this AD:

(1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866,

(2) Is not a ‘‘significant rule’’ under 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.

You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. 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 adding the following new AD: 2010–09–12 McDonnell Douglas Corporation: Amendment 39–16277. Docket No. FAA–2010–0032; Directorate Identifier 2009–NM–213–AD.

Effective Date

(a) This airworthiness directive (AD) is effective June 8, 2010.

Affected ADs

(b) None. Applicability

(c) This AD applies to McDonnell Douglas Corporation Model DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD– 10–10F, MD–10–30F, MD–11, and MD–11F airplanes; certificated in any category. Subject

(d) Air Transport Association (ATA) of America Code 28: Fuel.

Unsafe Condition

(e) This AD results from fuel system reviews conducted by the manufacturer. The Federal Aviation Administration is issuing this AD to prevent point-of-contact arcing or filament heating damage in the fuel tanks, which could result in fuel tank explosions and consequent loss of the airplane. 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.

Installation

(g) Within 60 months after the effective date of this AD, install electrical bonding jumpers for the fill valve controllers of the fuel tanks, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC10–28–249, Revision 1, dated November 6, 2008 (for Model DC–10– 10, DC–10–10F, DC–10–15, DC–10–30, DC– 10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD–10–10F, and MD–10–30F airplanes); or Boeing Service Bulletin MD11– 28–135, Revision 1, dated November 6, 2008 (for Model MD–11 and MD–11F airplanes). Alternative Methods of Compliance (AMOCs)

(h)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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: Philip Kush, Aerospace Engineer, Propulsion Branch, ANM–140L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627– 5263; fax (562) 627–5210.

(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. 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. Material Incorporated by Reference

(i) You must use Boeing Service Bulletin DC10–28–249, Revision 1, dated November 6, 2008; or Boeing Service Bulletin MD11–28– 135, Revision 1, dated November 6, 2008; as applicable; to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846– 0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https:// www.myboeingfleet.com.

(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call
425–227–1221.

(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 April 22,
2010. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–9945 Filed 5–3–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–0789; Directorate Identifier 2008–NM–185–AD; Amendment**  **39–16228; AD 2010–06–04]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus Model **A300 B2–1C, B2–203, B2K–3C, B4–103, B4–203, B4–2C Airplanes; Model A310**  **Series Airplanes; and Model A300 B4– 601, B4–603, B4–605R, B4–620, B4–**  **622, and B4–622R Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule; correction.

**SUMMARY** 

### : The FAA is correcting a typographical error in an existing


## 23573 Federal Register / Vol. 75, No. 85 / Tuesday, May 4, 2010 / Rules and Regulations

airworthiness directive (AD) that was published in the Federal Register on March 11, 2010. The error resulted in an imprecise compliance time in a table. This AD applies to certain Airbus Model A300 B2–1C, B2–203, B2K–3C, B4–103, B4–203, B4–2C airplanes; Model A310 series airplanes; and Model A300 B4– 601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes. This AD requires repetitive inspections to detect cracks of the pylon side panels (upper section) at rib 8; and corrective actions if necessary.

**DATES** 

### : This correction is effective May 4, 2010. The effective date of AD 2010– 06–04 remains April 15, 2010.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT** 

### : Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION** 

### : On March 4, 2010, the FAA issued AD 2010–06– 04, Amendment 39–16228 (75 FR 11428, March 11, 2010), for certain Airbus Model A300 B2–1C, B2–203, B2K–3C, B4–103, B4–203, B4–2C airplanes; Model A310 series airplanes; and Model A300 B4–601, B4–603, B4– 605R, B4–620, B4–622, and B4–622R airplanes. The AD requires repetitive inspections to detect cracks of the pylon side panels (upper section) at rib 8; and corrective actions if necessary.

As published, Table 1 of this AD contained a typographical error in the second row in the second column. The compliance time of ‘‘>17,500 total flight 1 

### ’’ has been corrected to read

’’>17,500 total flight cycles 1



### . ’’ (The word

‘‘cycles’’ was omitted in the AD.)

No other part of the regulatory information has been changed; therefore, the final rule is not republished in the Federal Register

.

The effective date of this AD remains April 15, 2010.

**§ 39.13 [Corrected]**

■ 

### In the Federal Register of March 11, 2010, on page 11430, in the second row in the second column, Table 1 of AD 2010–06–04 is corrected to read as follows:
* * * * *



### TABLE 

### 1—C OMPLIANCE 

### T IMES FOR 

### C ONFIGURATION 

### 1

For Model— That have accumulated— Whichever occurs later And repeat the inspectionat intervals not to exceed— Inspect before the accumulation of— Or within—

A300 B2–1C, B2–203, and

B2K–3C airplanes. ≤ 17,500 total flight cycles 1 5,350 total flight cycles ..... 2,500 flight cycles 2 ........... 4,300 flight cycles.

A300 B2–1C, B2–203, and

B2K–3C airplanes. >17,500 total flight cycles 1 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 4,300 flight cycles.

A300 B4–103, B4–203,

and B4–2C airplanes. ≤ 18,000 total flight cycles 1 5,350 total flight cycles ..... 2,000 flight cycles 2 ........... 4,300 flight cycles.

A300 B4–103, B4–203,

and B4–2C airplanes. >18,000 total flight cycles 1 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 4,300 flight cycles.

A300 B4–601, B4–603,

B4–605R, B4–620, B4–622, and B4–622R airplanes. ≤ 18,000 total flight cycles 1 4,200 total flight cycles ..... 2,000 flight cycles 2 ........... 3,600 flight cycles.

A300 B4–601, B4–603,

B4–605R, B4–620, B4–622, and B4–622R airplanes. >18,000 total flight cycles 1 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 3,600 flight cycles.

A310–200 airplanes with

GE CF6–80A3 or Pratt & Whitney engines. ≤ 18,000 total flight cycles 1 9,700 total flight cycles or 19,400 total flight hours, whichever occurs first. 1,500 flight cycles 2 ........... 6,700 flight cycles or 13,400 flight hours, whichever occurs first. A310–200 airplanes with

GE CF6–80A3 or Pratt & Whitney engines. >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 6,700 flight cycles or 13,400 flight hours, whichever occurs first. A310–200 airplanes with

GE CF6–80C2 engines. ≤ 18,000 total flight cycles 1 7,800 total flight cycles or 15,600 total flight hours, whichever occurs first. 1,500 flight cycles 2 ........... 5,800 flight cycles or 11,600 flight hours, whichever occurs first. A310–200 airplanes with

GE CF6–80C2 engines. >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 5,800 flight cycles or 11,600 flight hours, whichever occurs first. A310–300 SR 3 airplanes

with Pratt & Whitney JT9D engines. ≤ 18,000 total flight cycles 1 8,600 total flight cycles or 24,000 total flight hours, whichever occurs first. 1,500 total flight cycles 2 ... 6,700 flight cycles or 18,700 flight hours, whichever occurs first. A310–300 SR 3 airplanes

with Pratt & Whitney JT9D engines. >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 6,700 flight cycles or 18,700 flight hours, whichever occurs first. A310–300 SR 3 airplanes

with GE engines. ≤ 18,000 total flight cycles 1 7,000 total flight cycles or 19,600 total flight hours, whichever occurs first. 1,500 flight cycles 2 ........... 5,700 flight cycles or 15,900 flight hours, whichever occurs first.


## 23574 Federal Register / Vol. 75, No. 85 / Tuesday, May 4, 2010 / Rules and Regulations

TABLE 

### 1—C OMPLIANCE 

### T IMES FOR 

### C ONFIGURATION 

### 1—Continued

For Model— That have accumulated— Whichever occurs later And repeat the inspectionat intervals not to exceed— Inspect before the accumulation of— Or within—

A310–300 SR 3 airplanes

with GE engines. >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 5,700 flight cycles or 15,900 flight hours, whichever occurs first. A310–300 SR 3 airplanes

with Pratt & Whitney 4000 engines. ≤ 18,000 total flight cycles 1 7,000 total flight cycles or 19,600 total flight hours, whichever occurs first. 1,500 flight cycles 2 ........... 5,800 flight cycles or 16,200 flight hours, whichever occurs first. A310–300 SR 3 airplanes

with Pratt & Whitney 4000 engines. >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 5,800 flight cycles or 16,200 flight hours, whichever occurs first. A310–300 LR 4 airplanes

with Pratt & Whitney JT9D engines. ≤ 18,000 total flight cycles 1 5,900 total flight cycles or 29,500 total flight hours, whichever occurs first. 1,500 flight cycles 2 ........... 6,000 flight cycles or 30,300 flight hours, whichever occurs first. A310–300 LR 4 airplanes

with Pratt & Whitney JT9D engines. >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 6,000 flight cycles or 30,300 flight hours, whichever occurs first. A310–300 LR 4 airplanes

with GE engines. ≤ 18,000 total flight cycles 1 4,800 total flight cycles or 24,100 total flight hours, whichever occurs first. 1,500 flight cycles 2 ........... 5,100 flight cycles or 25,500 flight hours, whichever occurs first. A310–300 LR 4 airplanes

with GE engines. >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 5,100 flight cycles or 25,500 flight hours, whichever occurs first. A310–300 LR 4 airplanes

with Pratt & Whitney 4000 engines. ≤ 18,000 total flight cycles 1 4,800 total flight cycles or 24,000 total flight hours, whichever occurs first. 1,500 flight cycles 2 ........... 5,200 flight cycles or 26,300 flight hours, whichever occurs first. A310–300 LR 4 airplanes

with Pratt & Whitney 4000 engines. >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 5,200 flight cycles or 26,300 flight hours, whichever occurs first.

1 As of the effective date of this AD.

2 After the effective date of this AD.

3 ‘‘SR’’ applies to airplanes with average flights less than 4 flight hours.

4 ‘‘ LR’’ refers to airplanes with average flights of 4 or more flight hours.



### * * * * *

Issued in Renton, Washington on April 15,
2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–9521 Filed 5–3–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2008–1353; Directorate Identifier 2008–NE–46–AD; Amendment 39–**  **16279; AD 2010–09–14]**

**RIN 2120–AA64**



### Airworthiness Directives; CFM **International, S.A. CFM56–5B1/P, –5B2/ P, –5B3/P, –5B3/P1, –5B4/P, –5B5/P,**  **–5B6/P, –5B7/P, –5B8/P, –5B9/P, –5B1/ 2P, –5B2/2P, –5B3/2P, –5B3/2P1, –5B4/**  **2P, –5B4/P1, –5B6/2P, –5B4/2P1, and –5B9/2P Turbofan Engines** 

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT). **ACTION** 

### : Final rule.

**SUMMARY** 

### : The FAA is superseding an existing airworthiness directive (AD) for CFM International, S.A. CFM56–5B series turbofan engines. That AD requires reviewing exhaust gas temperature (EGT) monitoring records to determine EGT margin deterioration, and for airplanes where both engines have greater than 80 ° centigrade (C) ofEGT margin deterioration, borescopeinspecting the high-pressure compressor (HPC) of both engines. That AD also requires removing from service any engine that does not pass the borescope inspection and, if both engines pass, replacing one of the engines with an engine that has 80 °C or less of EGT margin deterioration. That AD also requires continuous monitoring of EGT margin deterioration on engines in service to prevent two engines on an airplane from having greater than 80 °C of EGT margin deterioration. This AD:

• Reduces the number of engine models affected;

• Continues to monitor EGT margin deterioration;

• Lowers the EGT margin threshold from 80 °C to 75 °C;

• Removes FADEC software version 5.B.Q and earlier versions from the engine as mandatory terminating action to the continuous EGT margin deterioration monitoring, for certain engine models;

• Removes the requirement to borescope inspect; and

• Removes the requirement to replace one of the engines with an engine that has 80 °C or less deterioration of EGT margin as a corrective action.

This AD results from a reduction of the affected engine models listed in AD 2009–01–01 from 25 to 19, a reduction in the engine EGT margin deterioration threshold from 80 °C to 75 °C, the introduction of terminating action to the continuous EGT monitoring for certain engines, and a change to the removal plan for the remaining engines if the EGT margin deterioration is greater than
75 °C. We are issuing this AD to prevent HPC stalls, which could prevent continued safe flight or landing.

**DATES** 

### : This AD becomes effective June 8, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of June 8, 2010.

**ADDRESSES** 

### : You can get the service information identified in this AD from CFM International, S.A., Technical Customer Support, 1 Neumann Way,