Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 73489 

combination with flammable fuel vapors, 

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. 

Actions 

(g) Within 24 months after the effective 

date of this AD, do a detailed inspection of 

the electrical bonding for the water drain 

system (trim tank) and the ventilation intake 

system to verify whether it is equivalent to 

the electrical bonding done in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A340–28– 

4097, Revision 05, including Appendix 1, 

dated June 3, 2010. 

(h) If, during the inspection required by 

paragraph (g) of this AD, the electrical 

bonding of the water drain system and the 

ventilation intake system is found to be not 

equivalent to the electrical bonding done in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–28–4097, Revision 05, 

including Appendix 1, dated June 3, 2010: 

Within 24 months after the effective date of 

this AD, modify the electrical bonding 

associated with the airplane configuration in 

accordance with paragraph 3.B.(11) or 

3.B.(12), as applicable, of the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–28–4097, 

Revision 05, including Appendix 1, dated 

June 3, 2010. 

(i) A review of the airplane maintenance 

records is acceptable in lieu of the inspection 

required by paragraph (g) of this AD provided 

that the accomplishment of the electrical 

bonding for the water drain system (trim 

tank) and the ventilation intake system can 

be conclusively identified as performed in 

accordance with Airbus Mandatory Service 

Bulletin A340–28–4097, Revision 05, 

including Appendix 1, dated June 3, 2010. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) 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. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

Related Information 

(k) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2010–0232, dated 

November 12, 2010; and Airbus Mandatory 

Service Bulletin A340–28–4097, Revision 05, 

including Appendix 1, dated June 3, 2010; 

for related information. 

Material Incorporated by Reference 

(l) You must use Airbus Mandatory Service 

Bulletin A340–28–4097, Revision 05, 

including Appendix 1, dated June 3, 2010, 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 Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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 

November 14, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–30229 Filed 11–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1261; Directorate 

Identifier 2011–NE–38–AD; Amendment 39– 

16875; AD 2011–24–11] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Honeywell International Inc. ALF502L– 

2C, ALF502R–3, ALF502R–3A, 

ALF502R–5, LF507–1F, and LF507–IH 

turbofan engines. This AD requires 

removing from service certain second 

stage high pressure compressor (HPC2) 

discs. This AD was prompted by a 

report of cracks found in an HPC2 disc 

during routine inspection. We are 

issuing this AD to prevent the affected 

discs from fracturing before reaching the 

currently published life limit. A disc 

fracture could result in an uncontained 

failure of the disc and damage to the 

airplane. 

DATES: This AD is effective December 

14, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 14, 2011. 

We must receive comments on this 

AD by January 13, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Honeywell 

International Inc., P.O. Box 52181, 

Phoenix, AZ 85072–2181, phone: (800) 

601–3099; Web site: http:// 


pmangrum on DSK3VPTVN1PROD with RULES
73490 Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 

portal.honeywell.com/wps/portal/aero. 

You may review copies of the 

referenced service information at the 

FAA, Engine & Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call (781) 238–7125. 

Examining the AD Docket 

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 street address for 

the Docket Office (phone: (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Baitoo, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, 3960 Paramount Blvd., Lakewood, 

CA 90712; phone: (562) 627–5245; fax: 

(562) 627–5210; email: 

robert.baitoo@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

During a routine inspection, cracks 

were found in a low-time HPC2 disc, 

part number (P/N) 2–101–332–12. 

Analysis has revealed that the cracks 

initiated during the forging process of a 

certain material ingot. Honeywell 

International Inc. has identified a 

suspect population of 29 HPC2 discs, by 

serial number (S/N), that were made 

from the affected material ingot. This 

condition, if not corrected, could result 

in an uncontained failure of the disc 

and damage to the airplane. 

Relevant Service Information 

We reviewed Honeywell International 

Inc. Service Bulletin (SB) No. ALF/LF– 

72–1113, dated September 16, 2011. The 

SB lists the affected HPC2 discs by 

P/N and S/N, and describes procedures 

for removing them from service. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because there are no U.S. operators 

of airplanes with Honeywell 

International Inc. ALF502L–2C, 

ALF502R–3, ALF502R–3A, ALF502R–5, 

LF507–1F, and LF507–IH turbofan 

engines, with an affected HPC2 disc 

installed. Therefore, we find that notice 

and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2011–1261 and Directorate 

Identifier 2011–NE–38–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects no 

Honeywell International Inc. ALF502L– 

2C, ALF502R–3, ALF502R–3A, 

ALF502R–5, LF507–1F, and LF507–IH 

turbofan engines installed on airplanes 

of U.S. registry. Therefore, we estimate 

the total cost of the AD to U.S. operators 

to be $0. 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 airworthiness 

directive (AD): 

2011–24–11 Honeywell International Inc. 

Turbofan Engines: Amendment 39– 

16875; Docket No. FAA–2011–1261; 

Directorate Identifier 2011–NE–38–AD. 

(a) Effective Date 

This AD is effective December 14, 2011. 

(b) Affected ADs 

None. 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 73491 

(c) Applicability 

This AD applies to Honeywell 

International Inc. ALF502L–2C, ALF502R–3, 

ALF502R–3A, ALF502R–5, LF507–1F, and 

LF507–IH turbofan engines with any of the 

second stage high pressure compressor 

(HPC2) discs, part number (P/N) 2–101–332– 

12, serial numbers (S/N) listed in Table 2 of 

Honeywell International Inc. Service Bulletin 

(SB) No. ALF/LF–72–1113, dated September 

16, 2011, installed. 

(d) Unsafe Condition 

This AD was prompted by a report of 

cracks found in an HPC2 disc during routine 

inspection. We are issuing this AD to prevent 

the affected discs from fracturing before 

reaching the currently published life limit. A 

disc fracture could result in an uncontained 

failure of the disc and damage to the 

airplane. 

(e) Compliance 

Comply with this AD before accumulating 

4,500 cycles-since-new on the affected HPC2 

disc, or before exceeding 7 years after the 

effective date of this AD, whichever occurs 

first, unless already done. 

(f) Removal of Affected HPC2 Discs 

Remove from service HPC2 discs, P/N 2– 

101–332–12, S/Ns listed in Table 2 of 

Honeywell International Inc. SB No. ALF/ 

LF–72–1113, dated September 16, 2011. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Los Angeles Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

(h) Related Information 

For more information about this AD, 

contact Robert Baitoo, Aerospace Engineer, 

Los Angeles Aircraft Certification Office, 

FAA, 3960 Paramount Blvd., Lakewood, CA 

90712; phone: (562) 627–5245; fax: (562) 

627–5210; email: robert.baitoo@faa.gov. 

(i) Material Incorporated by Reference 

You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(1) Honeywell International Inc. Service 

Bulletin No. ALF/LF–72–1113, dated 

September 16, 2011, approved for IBR 

December 14, 2011. 

(2) For service information identified in 

this AD, contact Honeywell International 

Inc., P.O. Box 52181, Phoenix, AZ 85072– 

2181, phone: (800) 601–3099; Web site: 

http://portal.honeywell.com/wps/portal/aero. 

(3) You may review copies of the service 

information at the FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, call 

(781) 238–7125. 

(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 an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

November 15, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–30575 Filed 11–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1206; Directorate 

Identifier 2009–NM–216–AD; Amendment 

39–16868; AD 2011–24–04] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model DC–10–10, DC–10–10F, and MD– 

10–10F airplanes. This AD was 

prompted by reports of three instances 

of fuel leaks in the lower cap splice of 

the wing rear spar at station Xors=409. 

Investigation revealed the fuel leak was 

due to a crack in the lower cap. If not 

corrected, this condition could result in 

fuel leaks or cracking of the lower wing 

skin and structure, causing possible 

inability of the structure to sustain the 

limit load and adversely affecting the 

structural integrity of the airplane. This 

AD requires repetitive inspections for 

cracking on the lower cap of the rear 

spar of the left and right wings between 

stations Xors=417 and the outboard 

edge of the lower cap splice of the wing 

rear spar at station Xors=400; temporary 

and permanent repairs if necessary; and 

repetitive inspections of repaired areas, 

and corrective actions if necessary. We 

are issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective January 3, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of January 3, 2012. 

ADDRESSES: 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; email 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call (425) 227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket 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 (phone: (800) 647–5527) 

is 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: 

Nenita Odesa, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: (562) 

627–5234; fax: (562) 627–5210; email: 

nenita.odesa@faa.gov. 

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 December 30, 2010 (75 FR 

82333). That NPRM proposed to require 

repetitive inspections for cracking on 

the lower cap of the rear spar of the left 

and right wings between stations 

Xors=417 and the outboard edge of the 

lower cap splice of the wing rear spar 

at station Xors=400; temporary and 

permanent repairs if necessary; and 

repetitive inspections of repaired areas, 

and corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (75 

FR 82333, December 30, 2010) or on the 

determination of the cost to the public. 

New Service Information 

Since publication of the NPRM (75 FR 

82333, December 30, 2010), Boeing has 


pmangrum on DSK3VPTVN1PROD with RULES