Federal Register / Vol. 76, No. 169 / Wednesday, August 31, 2011 / Proposed Rules 54143 

identified in table 1 of this AD. Cessna 

Temporary FAA Approved Airplane Flight 

Manual Change 68FM TC–R09–13, dated 

October 15, 2010, introduces procedures to 

use when the left or right generator is 

selected OFF. Operate the airplane according 

to the procedures in Cessna Temporary FAA 

Approved Airplane Flight Manual Change 

68FM TC–R09–13, dated October 15, 2010. 

TABLE 1—TCS TO REMOVE FROM THE

CESSNA 680 AFM 

Cessna TCs— Dated— 

68FM TC–R09–09 ........ October 15, 2010. 

68FM TC–R09–10 ........ October 15, 2010. 

68FM TC–R09–11 ........ October 15, 2010. 

68FM TC–R09–12 ........ October 15, 2010. 

Note 1: Updating the Cessna 680 Citation 

Sovereign AFM may be done by inserting a 

copy of Cessna Temporary FAA Approved 

Airplane Flight Manual Change 68FM TC– 

R09–13, dated October 15, 2010, into the 

AFM. When this TC has been included in 

general revisions of the AFM, the general 

revisions may be inserted in the AFM, 

provided the relevant information in the 

general revision is identical to that in Cessna 

Temporary FAA Approved Airplane Flight 

Manual Change 68FM TC–R09–13, and this 

TC may be removed. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Wichita Aircraft 

Certification Office (ACO), ACE–115W, 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 manager of the ACO, send it 

to the attention of the person identified in the 

Related Information section of this AD. 

(2) 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. 

Related Information 

(j) For more information about this AD, 

contact Nhien Hoang, Aerospace Engineer, 

Electrical Systems and Avionics Branch, 

ACE–119W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, Wichita, 

Kansas 67209; phone: (316) 946–4190; fax: 

(316) 946–4107; e-mail: 

nhien.hoang@faa.gov. 

(k) For service information identified in 

this AD, contact Cessna Aircraft Co., P.O. Box 

7706, Wichita, Kansas 67277; telephone 316– 

517–6215; fax 316–517–5802; e mail 

citationpubs@cessna.textron.com; Internet 

https://www.cessnasupport.com/ 

newlogin.html. 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. 

Issued in Renton, Washington, on August 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–22225 Filed 8–30–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0904; Directorate 

Identifier 2010–NE–33–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arriel 1B Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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: 

During quality inspections in repair centre 

some 2nd stage Nozzle Guide Vanes (NGVs) 

to be installed on Pre TU 148 standard Arriel 

1B were found not conforming to the 

definition. The affected parts had been 

repaired and were found drilled on the rear 

flange instead of the front flange. This 

configuration corresponds to 2nd stage 

Turbine NGVs to be installed on post-TU 148 

standard Arriel 1B engines. This non 

compliance may only be found on post-TU 

76 standard 2nd stage Turbine NGVs (i.e., 

with flexible hub). 

This non compliance would increase hot 

gas ingestion and generate an increase of 

temperature in the Gas Generator (GG) 

turbine rotor, potentially resulting in turbine 

damage and an uncommanded in-flight 

shutdown. 

We are proposing this AD to prevent 

over-temperature damage of the gas 

generator turbine, which could result in 

an uncommanded in-flight engine 

shutdown, and a subsequent forced 

autorotation landing or accident. 

DATES: We must receive comments on 

this proposed AD by October 17, 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: Docket Management Facility, 

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. 

Contact Turbomeca, 40220 Tarnos, 

France; phone: 33 05 59 74 40 00, fax: 

33 05 59 74 45 15, for the service 

information identified in this proposed 

AD. 

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 proposed 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: Rose 

Len, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7772; fax: 781–238– 

7199; e-mail: rose.len@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–0904; Directorate Identifier 

2010–NE–33–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 


Emcdonald on DSK2BSOYB1PROD with PROPOSALS
54144 Federal Register / Vol. 76, No. 169 / Wednesday, August 31, 2011 / Proposed Rules 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2010– 

0273R1, dated February 16, 2011 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

During quality inspections in repair centre 

some 2nd stage Nozzle Guide Vanes (NGVs) 

to be installed on Pre TU 148 standard Arriel 

1B were found not conforming to the 

definition. The affected parts had been 

repaired and were found drilled on the rear 

flange instead of the front flange. This 

configuration corresponds to 2nd stage 

Turbine NGVs to be installed on post-TU 148 

standard Arriel 1B engines. This non 

compliance may only be found on post-TU 

76 standard 2nd stage Turbine NGVs (i.e., 

with flexible hub). 

This non compliance would increase hot 

gas ingestion and generate an increase of 

temperature in the Gas Generator (GG) 

turbine rotor, potentially resulting in turbine 

damage and an uncommanded in-flight 

shutdown. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Turbomeca has issued Mandatory 

Service Bulletin (MSB) No. A292 72 

0829, Version B, dated December 13, 

2010. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of France and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, they have 

notified us of the unsafe condition 

described in the MCAI and service 

information referenced above. We are 

proposing this AD because we evaluated 

all information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. 

This proposed AD would require 

daily checks for evidence of turbine 

damage, and removal of the engine from 

service before further flight if turbine 

damage is found. This proposed AD 

would also require inspecting the 

configuration of the holes in the 

repaired 2nd stage turbine NGV. If the 

holes are non-conforming, then before 

further flight this proposed AD would 

require replacing the 2nd stage turbine 

NGV, 1st stage turbine disc, and 2nd 

stage turbine disc, with discs eligible for 

installation. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 20 Turbomeca Arriel 1B 

turboshaft engines installed on 

helicopters of U.S. registry. We also 

estimate that it would take about 40 

work-hours per engine to inspect a 

repaired 2nd stage turbine NGV for the 

non-conforming hole configuration. We 

also estimate that it would take about 60 

work-hours to replace the NGV, the 1st 

stage turbine disc, and the 2nd stage 

turbine disc, and that one engine would 

require these replacements. The average 

labor rate is $85 per work-hour. 

Required parts would cost about 

$19,889 per engine. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$92,989. Our cost estimate is exclusive 

of possible warranty coverage. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Turbomeca: Docket No. FAA–2010–0904; 

Directorate Identifier 2010–NE–33–AD. 

Comments Due Date 

(a) We must receive comments by October 

17, 2011. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Turbomeca Arriel 1B 

turboshaft engines with M03 modules 

modified by TU 76 or TU 202, and not 

modified by TU 148, and if fitted with a 

repaired 2nd stage turbine nozzle guide vane. 

The M03 module contains the 2nd stage 

turbine NGV, 1st stage turbine disc, and 2nd 

stage turbine disc. Guidance on determining 

if an engine has an unrepaired 2nd stage 

turbine nozzle guide vane installed can be 

found in paragraph 1.C. of Turbomeca 

Mandatory Service Bulletin (MSB) No. A292 

72 0829, Version B, dated December 13, 

2010. 

Reason 

(d) During quality inspections in repair 

centre some 2nd stage Nozzle Guide Vanes 

(NGVs) to be installed on Pre TU 148 

standard Arriel 1B were found not 

conforming to the definition. The affected 

parts had been repaired and were found 

drilled on the rear flange instead of the front 

flange. This configuration corresponds to 2nd 

stage Turbine NGVs to be installed on postTU 148 standard Arriel 1B engines. This non 

compliance may only be found on post-TU 


Emcdonald on DSK2BSOYB1PROD with PROPOSALS
Federal Register / Vol. 76, No. 169 / Wednesday, August 31, 2011 / Proposed Rules 54145 

76 standard 2nd stage Turbine NGVs (i.e., 

with flexible hub). 

This non compliance would increase hot 

gas ingestion and generate an increase of 

temperature in the Gas Generator (GG) 

turbine rotor, potentially resulting in turbine 

damage and an uncommanded in-flight 

shutdown. On a single-engine helicopter, this 

could ultimately lead to an emergency 

autorotation landing. 

We are issuing this AD to prevent overtemperature damage of the gas generator 

turbine, which could result in an 

uncommanded in-flight engine shutdown, 

and a subsequent forced autorotation landing 

or accident. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Daily Checks 

(f) Starting from the effective date of this 

AD, perform a daily check (after last flight of 

the day) for: 

(1) Normal rundown time of the gas 

generator rotor; and 

(2) The free rotation of the gas generator 

rotor; and 

(3) No grinding noise during the rundown 

check, and during the free rotation check of 

the gas generator rotor. 

(g) Guidance on performing the daily 

checks can be found in the Maintenance 

Manual, task 71–02–09–760–801 and task 

05–20–01–200–801. 

(h) If the engine fails any of these daily 

checks, remove the engine from service 

before further flight. 

Inspection of Repaired 2nd Stage Turbine 

NGVs 

(i) Inspect the 2nd stage turbine NGV for 

a non-conforming hole configuration, at the 

compliance times in Table 1 of this AD. 

Guidance on 2nd stage turbine NGV nonconforming hole configuration can be found 

in Turbomeca MSB No. A292 72 0829, 

Version B, dated December 13, 2010. 

TABLE 1—INSPECTION COMPLIANCE TIMES

If accumulated Gas Generator (GG) Cycles-in-Service (CIS) on the effective date 

of this AD are: 

Then inspect: 

(1) Fewer than 1,200 CIS on both the 1st 

and 2nd stage turbines.

Before exceeding 1,500 GG CIS. 

(2) 1,200 or more but fewer than 1,800 CIS 

on either the 1st or 2nd stage turbines.

Before exceeding 300 GG CIS after the effective date of this AD but not to exceed 2,000 CIS on 

either the 1st or 2nd stage turbines. 

(3) 1,800 or more but fewer than 2,400 CIS 

on either the 1st or 2nd stage turbine.

Before exceeding 200 GG CIS after the effective date of this AD but not to exceed 2,500 CIS on 

either the 1st or 2nd stage turbines. 

(4) Greater than 2,400 CIS on either the 

1st or 2nd stage turbine.

Before exceeding 100 GG CIS after the effective date of this AD but not to exceed 3,000 CIS on 

either the 1st or 2nd stage turbine. 

(j) If the configuration of the holes in the 

repaired 2nd stage turbine NGV are 

conforming, then no further action is 

required. 

(k) If the configuration of the holes in the 

repaired 2nd stage turbine NGV are nonconforming, then before further flight: 

(1) Replace the 2nd stage turbine NGV with 

a 2nd stage turbine NGV eligible for 

installation; and 

(2) Replace the 1st stage turbine disc and 

2nd stage turbine disc with discs eligible for 

installation. 

Terminating Action 

(l) Complying with paragraph (i) and either 

paragraph (j) or paragraphs (k)(1) through 

(k)(2) of this AD, or replacing the M03 

module with an M03 module that is eligible 

for installation, is terminating action for the 

requirements of this AD. 

Installation Prohibition 

(m) Do not reinstall the 1st stage turbine 

disc and the 2nd stage turbine disc removed 

in paragraph (k)(2) of this AD into any 

engine. 

(n) After the effective date of this AD, do 

not install an M03 module that has 

incorporated TU 202 but not incorporated TU 

148, unless the module is in compliance with 

the requirements of this AD. 

(o) After the effective date of this AD, do 

not install an M03 module that has 

incorporated TU 76 but not incorporated TU 

148, unless the module is in compliance with 

the requirements of this AD. 

FAA AD Differences 

(p) This AD differs from the Mandatory 

Continuing Airworthiness Information 

(MCAI) and/or service information as 

follows: 

(1) This AD does not require sending data 

to Turbomeca to confirm whether Turbomeca 

MSB No. A292 72 0829, Version B, dated 

December 13, 2010, is applicable to the 

operator’s engine; the MCAI does. 

(2) This AD does not incorporate by 

reference (IBR) Turbomeca MSB No. A292 72 

0829, Version B, dated December 13, 2010; 

the MCAI does. 

(3) This AD requires replacing nonconforming 2nd stage turbine NGVs and 1st 

stage and 2nd stage turbine discs that were 

operated with non-conforming 2nd stage 

turbine NGVs but does not require replacing 

affected M03 modules. The MCAI requires 

replacing affected M03 modules with M03 

modules eligible for installation. 

Definition 

(q) For the purpose of this AD, a 

conforming repaired 2nd stage turbine NGV 

is one with cooling holes in the forward 

inner flange, and with no cooling holes in the 

rear flange. 

Alternative Methods of Compliance 

(AMOCs) 

(r) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(s) Refer to European Aviation Safety 

Agency AD 2010–0273R1, dated February 16, 

2011, and Turbomeca MSB No. A292 72 

0829, Version B, dated December 13, 2010, 

for related information. Contact Turbomeca, 

40220 Tarnos, France; telephone 33 05 59 74 

40 00, fax 33 05 59 74 45 15, for a copy of 

this service information. 

(t) Contact Rose Len, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: rose.len@faa.gov; phone: 781–238– 

7772; fax: 781–238–7199, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

August 23, 2011. 

Thomas A. Boudreau, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–22246 Filed 8–30–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0912; Directorate 

Identifier 2011–NM–035–AD] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Model 328– 

100 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


Emcdonald on DSK2BSOYB1PROD with PROPOSALS