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 


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issued Alert Service Bulletin DC10– 

57A156, Revision 2, dated August 23, 

2011. We have updated the references in 

paragraphs (c) and (g) of this AD to 

include Boeing Alert Service Bulletin 

DC10–57A156, Revision 2, dated August 

23, 2011. The changes in this revised 

service bulletin are for clarification 

only. However, certain inspections 

called eddy current test high frequency 

(ETHF) inspections in Boeing Alert 

Service Bulletin DC10–57A156, 

Revision 1, dated March 10, 2010 

(which was referenced in the NPRM (75 

FR 82333, December 30, 2010) as the 

appropriate source of service 

information for certain actions), are 

called high frequency eddy current 

inspections in Boeing Alert Service 

Bulletin DC10–57A156, Revision 2, 

dated August 23, 2011. This is different 

terminology for the same inspection 

method. We have followed the 

terminology in Boeing Alert Service 

Bulletin DC10–57A156, Revision 2, 

dated August 23, 2011, and used both 

terminologies as specified in Boeing 

Alert Service Bulletin DC10–57A156, 

Revision 2, dated August 23, 2011. We 

are also allowing credit for actions done 

before the effective date of this AD, in 

accordance with Boeing Alert Service 

Bulletin DC10–57A156, Revision 1, 

dated March 10, 2010, and have added 

that reference to paragraph (h) of this 

AD. 

Since publication of the NPRM (75 FR 

82333, December 30, 2010), Boeing has 

also issued revised service rework 

drawings to clarify the repair 

instructions. These service rework 

drawings do not provide repairs for all 

conditions specified in the NPRM (75 

FR 82333, December 30, 2010). We have 

updated the references in paragraph (g) 

of this AD to include Boeing DC–10–10 

Service Rework Drawing SR10570019, 

Revision K, dated April 17, 2009, 

including Parts List PL SR10570019, 

Revision K, dated April 23, 2009, 

including Boeing Engineering Order, 

Revision L, dated April 14, 2010; and 

Boeing DC–10–10 Service Rework 

Drawing SR10570048, Revision K, dated 

October 7, 2010, including Parts List PL 

SR10570048, Revision K, dated October 

14, 2010. We have also revised the 

actions in paragraph (g) of this AD to 

specify which conditions are addressed 

by these service rework drawings, and 

which conditions need a repair method 

approved by the FAA. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed with the changes described 

previously—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (75 FR 

82333, December 30, 2010), for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD affects 68 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ........................ 2 work-hours × $85 per hour = $170 per inspection cycle.$0 $170 per inspection 

cycle.

$11,560 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this 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 

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): 

2011–24–04 McDonnell Douglas 

Corporation: Amendment 39–16868; 

Docket No. FAA–2010–1206; Directorate 

Identifier 2009–NM–216–AD. 

(a) Effective Date 

This AD is effective January 3, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to McDonnell Douglas 

Corporation Model DC–10–10, DC–10–10F, 

and MD–10–10F airplanes; certificated in any 

category; as identified in Boeing Alert 


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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 73493 

Service Bulletin DC10–57A156, Revision 2, 

dated August 23, 2011. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Unsafe Condition 

This AD results from reports of three 

instances of fuel leaks in the lower cap splice 

of the wing rear spar at station Xors=409. The 

Federal Aviation Administration is issuing 

this AD to detect and correct 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, which 

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. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection 

Within 1,750 flight cycles after the 

effective date of this AD, do an eddy current 

test high frequency (ETHF) inspection 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, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin DC10–57A156, Revision 2, 

dated August 23, 2011. 

(1) If no cracking is found, repeat the 

inspection required by paragraph (g) of this 

AD thereafter at intervals not to exceed 1,750 

flight cycles. 

(2) If any cracking is found in the spar cap 

aft leg at the fastener holes, and that cracking 

can be removed by hole enlargement, before 

further flight, do a permanent repair, in 

accordance with Boeing DC–10–10 Service 

Rework Drawing SR10570048, Revision K, 

dated October 7, 2010, including Parts List 

PL SR10570048, Revision K, dated October 

14, 2010. Within 1,750 flight cycles after 

doing the applicable permanent repair, and 

thereafter at intervals not to exceed 1,750 

flight cycles, do ETHF and high frequency 

eddy current inspections for cracking in 

accordance with Boeing DC–10–10 Service 

Rework Drawing SR10570048, Revision K, 

dated October 7, 2010, including Parts List 

PL SR10570048, Revision K, dated October 

14, 2010. If any cracking is found during any 

inspection required by this paragraph, before 

further flight, repair the cracking, in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(3) If any cracking is found in the spar cap 

aft leg at the fastener holes, and that cracking 

cannot be removed by hole enlargement but 

it does not extend into the vertical leg, before 

further flight, do the applicable actions 

specified in paragraph (g)(3)(i) or (g)(3)(ii) of 

this AD: 

(i) If cracking is found between Station 

Xors=400 and inboard of Station Xors=408, 

repair the cracking, in accordance with the 

procedures specified in paragraph (i) of this 

AD (Alternative Method of Compliance 

(AMOCs) paragraph). 

(ii) If cracking is found between Stations 

Xors=408 and Xors=417, do a permanent 

repair, in accordance with Boeing DC–10–10 

Service Rework Drawing SR10570048, 

Revision K, dated October 7, 2010, including 

Parts List PL SR10570048, Revision K, dated 

October 14, 2010. Within 4,550 flight cycles 

after doing a permanent repair, and thereafter 

at intervals not to exceed 4,550 flight cycles, 

do ETHF and ultrasonic inspections for 

cracking, in accordance with Boeing DC–10– 

10 Service Rework Drawing SR10570048, 

Revision K, dated October 7, 2010, including 

Parts List PL SR10570048, Revision K, dated 

October 14, 2010. If any cracking is found 

during any inspection required by this 

paragraph, before further flight, repair the 

cracking, in accordance with the procedures 

specified in paragraph (i) of this AD. 

(4) If any cracking is found in the spar cap 

aft leg at fastener holes and that cracking 

extends into the vertical leg of the spar cap, 

do the actions specified in paragraph (g)(4)(i) 

or (g)(4)(ii) of this AD. 

(i) If any cracking is found between Station 

Xors=400 and inboard of Station Xors=408, 

before further flight, do the applicable 

permanent repair, in accordance with Boeing 

DC–10–10 Service Rework Drawing 

SR10570019, Revision K, dated April 17, 

2009, including Parts List PL SR10570019, 

Revision K, dated April 23, 2009, including 

Boeing Engineering Order, Revision L, dated 

April 14, 2010. Within 4,550 flight cycles 

after doing the permanent repair, and 

thereafter at intervals not to exceed 4,550 

flight cycles, do ETHF and ultrasonic 

inspections for cracking of the repaired area, 

in accordance with Boeing DC–10–10 Service 

Rework Drawing SR10570019, Revision K, 

dated April 17, 2009, including Parts List PL 

SR10570019, Revision K, dated April 23, 

2009, including Boeing Engineering Order, 

Revision L, dated April 14, 2010. If any 

cracking is found during any inspection 

required by this paragraph, before further 

flight, repair the cracking, in accordance with 

the procedures specified in paragraph (i) of 

this AD. 

(ii) If any cracking is found between 

Stations Xors=408 and Xors=417, do the 

actions in paragraphs (g)(4)(ii)(A) or 

(g)(4)(ii)(B) of this AD. 

(A) Do the actions in paragraphs 

(g)(4)(ii)(A)(1) and (g)(4)(ii)(A)(2) of this AD. 

(1) Before further flight, do a temporary 

repair, in accordance with Boeing DC–10–10 

Service Rework Drawing SR10570048, 

Revision K, dated October 7, 2010, including 

Parts List PL SR10570048, Revision K, dated 

October 14, 2010. Within 1,650 flight cycles 

after doing the temporary repair; and 

thereafter at intervals not to exceed 1,650 

flight cycles, do ETHF and ultrasonic 

inspections for cracking of the repaired area, 

in accordance with Boeing DC–10–10 Service 

Rework Drawing SR10570048, Revision K, 

dated October 7, 2010, including Parts List 

PL SR10570048, Revision K, dated October 

14, 2010, until the permanent repair required 

by paragraph (g)(4)(ii)(A)(2) of this AD is 

done. If any cracking is found during any 

inspection required by this paragraph, before 

further flight, repair the cracking, in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(2) Within 7,000 flight cycles after the 

temporary repair has been done, do the 

applicable permanent repair, in accordance 

with Boeing DC–10–10 Service Rework 

Drawing SR10570019, Revision K, dated 

April 17, 2009, including Parts List PL 

SR10570019, Revision K, dated April 23, 

2009, including Boeing Engineering Order, 

Revision L, dated April 14, 2010. Within 

4,550 flight cycles after doing the permanent 

repair, and thereafter at intervals not to 

exceed 4,550 flight cycles, do ETHF and 

ultrasonic inspections for cracking of the 

repaired area, in accordance with Boeing DC– 

10–10 Service Rework Drawing SR10570019, 

Revision K, dated April 17, 2009, including 

Parts List PL SR10570019, Revision K, dated 

April 23, 2009, including Boeing Engineering 

Order, Revision L, dated April 14, 2010. If 

any cracking is found during any inspection 

required by this paragraph, before further 

flight, repair the cracking, in accordance with 

the procedures specified in paragraph (i) of 

this AD. 

(B) Before further flight do the applicable 

permanent repair, in accordance with Boeing 

DC–10–10 Service Rework Drawing 

SR10570019, Revision K, dated April 17, 

2009, including Parts List PL SR10570019, 

Revision K, dated April 23, 2009, including 

Boeing Engineering Order, Revision L, dated 

April 14, 2010. Within 4,550 flight cycles 

after doing the permanent repair, and 

thereafter at intervals not to exceed 4,550 

flight cycles, do ETHF and ultrasonic 

inspections for cracking of the repaired area, 

in accordance with Boeing DC–10–10 Service 

Rework Drawing SR10570019, Revision K, 

dated April 17, 2009, including Parts List PL 

SR10570019, Revision K, dated April 23, 

2009, including Boeing Engineering Order, 

Revision L, dated April 14, 2010. If any 

cracking is found during any inspection 

required by this paragraph, before further 

flight, repair the cracking, in accordance with 

the procedures specified in paragraph (i) of 

this AD. 

(h) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Actions accomplished before the effective 

date of this AD according to Boeing Alert 

Service Bulletin DC10–57A156, dated 

September 16, 2009; and Revision 1, dated 

March 10, 2010; are considered acceptable 

for compliance with the corresponding 

actions specified in this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(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: 

Nenita Odesa, Aerospace Engineer, Airframe 

Branch, ANM–120L, FAA, Los Angeles ACO, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: (562) 627– 

5234; fax: (562) 627–5210; email: 

nenita.odessa@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 


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73494 Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 

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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(j) Related Information 

For more information about this AD, 

contact Nenita Odesa, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; phone: 

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

nenita.odessa@faa.gov. 

(k) 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) Boeing Alert Service Bulletin DC10– 

57A156, Revision 2, dated August 23, 2011; 

IBR approved January 3, 2012. 

(2) Boeing DC–10–10 Service Rework 

Drawing SR10570019, Revision K, dated 

April 17, 2009, including Parts List PL 

SR10570019, Revision K, dated April 23, 

2009, including Boeing Engineering Order, 

Revision L, dated April 14, 2010; IBR 

approved January 3, 2012. Only Sheet 1 of 

this drawing indicates the revision date of 

this document. 

(3) Boeing DC–10–10 Service Rework 

Drawing SR10570048, Revision K, dated 

October 7, 2010, including Parts List PL 

SR10570048, Revision K, dated October 14, 

2010; IBR approved January 3, 2012. Only 

Sheet 1 of this drawing indicates the revision 

date for this document. 

(4) 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. 

(5) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

(425) 227–1221. 

(6) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at 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 Renton, Washington, on 

November 7, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–29801 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–2011–1031; Directorate 

Identifier 2011–NE–27–AD; Amendment 39– 

16871; AD 2011–24–07] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Arriel 2B Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Non-conformities on adjustment of some 

hydromechanical units (HMUs) have been 

reported by a Turbomeca repair centre. The 

technical investigations carried out by 

Turbomeca are showing that only a limited 

number of HMUs are potentially affected by 

this non-conformity to HMU adjustment. 

Twenty nine HMUs have been 

identified with the non-conformities. 

We are issuing this AD to prevent an 

uncommanded inflight shutdown, 

which could result in an emergency 

autorotation landing. 

DATES: This AD becomes effective 

December 14, 2011. 

We must receive comments on this 

AD by December 29, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of December 14, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

For service information identified in 

this AD, contact Turbomeca S.A., 40220 

Tarnos, France; phone: 33–05–59–74– 

40–00, fax: 33–05–59–74–45–15. 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. 

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 this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

(800) 647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7758; fax: (781) 238– 

7199; email: mark.riley@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0128–E, 

dated July 6, 2011 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Non-conformities on adjustment of some 

hydromechanical units (HMUs) have been 

reported by a Turbomeca repair centre. The 

technical investigations carried out by 

Turbomeca are showing that only a limited 

number of HMUs are potentially affected by 

this non-conformity to HMU adjustment. 

Twenty nine HMUs have been 

identified with potential nonconformities in the proper adjustment of 


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