47430 Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Accomplishing the actions required in 

paragraph (g) of this AD before the effective 

date of this AD in accordance with Boeing 

Alert Service Bulletin 747–25A3588, dated 

July 19, 2010, is considered acceptable for 

compliance with the corresponding actions 

specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle 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. 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. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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 Francis Smith, Aerospace Engineer, 

Cabin Safety & Environmental Systems 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; phone: 425–917–6596 ; fax: 425–917– 

6590; e-mail: Francis.Smith@faa.gov. 

Material Incorporated by Reference 

(k) You must use Boeing Alert Service 

Bulletin 747–25A3588, Revision 1, dated 

April 7, 2011, 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, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; phone: 

206–544–5000, extension 1; fax: 206–766– 

5680; e-mail: me.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 July 26, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–19828 Filed 8–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0388; Directorate 

Identifier 2010–NM–004–AD; Amendment 

39–16761; AD 2011–16–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600, A300 B4–600R, and A300 

F4–600R Series Airplanes, and Model 

A300 C4–605R Variant F Airplanes 

(Collectively Called Model A300–600 

Series Airplanes); Model A310 Series 

Airplanes; Model A318 Series 

Airplanes; Model A319 Series 

Airplanes; Model A320–211, –212, 

–214, –231, –232, and –233 Airplanes; 

Model A321 Series Airplanes; Model 

A330–200 and A330–300 Series 

Airplanes; and Model A340–200, A340– 

300, A340–500, and A340–600 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. For Model A310 and A300–600 

series airplanes, the MCAI describes the 

unsafe condition as: 

Hamilton Sundstrand (HS), the 

manufacturer of the RAT [ram air turbine], 

reported the failure during a wind tunnel test 

of a balance weight fastening screw on the 

RAT turbine cover. After investigation, it has 

been discovered that a batch of screws, 

which are used to attach the balance washers 

of the HS RAT Turbine Assembly, has not 

been subject to the correct heat treatment and 

are consequently exposed to potential 

fracture. 

This condition, if not corrected, might lead 

to the ejection of screw heads and 

consequently to the detachment of the 

associated balance washers. The loss of 

balance washers could increase RAT 

vibrations, which might lead to a possible 

detachment of RAT parts and consequent 

loss of RAT functionality. The loss of the 

RAT, in combination with a total engine 

flame out, could result in loss of control of 

the aeroplane. 

* * * * * 

For Model A318, A319, A320, and 

A321 series airplanes, the MCAI 

describes the unsafe condition as: 

Hamilton Sundstrand (HS) reported the 

failure of a balance weight fastening screw on 

the RAT turbine cover during a wind tunnel 

test. After investigation, it has been 

discovered that a batch of screws, used to 

attach the balance washers of the RAT 

Turbine assembly, has not received the 

correct heat treatment, making them more 

subject to a potential failure. 

This condition, if left uncorrected, could 

lead to the ejection of screw heads and 

detachment of the associated balance 

washers. The loss of balance washers would 

increase RAT vibrations, which could lead to 

a possible detachment of RAT parts and loss 

of RAT functionality. The loss of the RAT, in 

combination with a double engine failure, or 

a total loss of normal electrical power 

generation, could result in loss of control of 

the aeroplane. 

* * * * * 

For Model A330 and A340 series 

airplanes, the MCAI describes the 

unsafe condition as: 

Hamilton Sundstrand (HS), the 

manufacturer of the RAT, reported the failure 

of a balance weight fastening screw on the 

RAT cover during a wind tunnel test. After 

investigation, it has been discovered that a 

batch of screws, which are used to attach the 

balance washers of the HS RAT turbine lower 

gear box assembly, has not been subject to 

the correct heat treatment and the screws are 

consequently exposed to potential fracture. 

This condition, if not corrected, might lead 

to the ejection of screw heads and 

consequently to the detachment of the 

associated balance washers. The loss of 

balance washers could increase RAT 

vibrations, which might lead to a possible 

detachment of RAT parts, and thus to damage 

to the aeroplane and risk of injury to persons 

on the ground. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

September 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 9, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 


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Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

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 May 4, 2011 (76 FR 25259). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. 

The MCAI for Model A300–600 and 

A310 series airplanes states: 

Hamilton Sundstrand (HS), the 

manufacturer of the RAT [ram air turbine], 

reported the failure during a wind tunnel test 

of a balance weight fastening screw on the 

RAT turbine cover. After investigation, it has 

been discovered that a batch of screws, 

which are used to attach the balance washers 

of the HS RAT Turbine Assembly, has not 

been subject to the correct heat treatment and 

are consequently exposed to potential 

fracture. 

This condition, if not corrected, might lead 

to the ejection of screw heads and 

consequently to the detachment of the 

associated balance washers. The loss of 

balance washers could increase RAT 

vibrations, which might lead to a possible 

detachment of RAT parts and consequent 

loss of RAT functionality. The loss of the 

RAT, in combination with a total engine 

flame out, could result in loss of control of 

the aeroplane. 

For the reasons described above, this AD 

requires the identification of the affected 

RAT turbine assemblies and replacement of 

all balance weight screws or, in case balance 

washer detachment is found, replacement of 

the RAT turbine assembly. 

The MCAI for Model A318, A319, 

A320, and A321 series airplanes states: 

Hamilton Sundstrand (HS) reported the 

failure of a balance weight fastening screw on 

the RAT turbine cover during a wind tunnel 

test. After investigation, it has been 

discovered that a batch of screws, used to 

attach the balance washers of the RAT 

Turbine assembly, has not received the 

correct heat treatment, making them more 

subject to a potential failure. 

This condition, if left uncorrected, could 

lead to the ejection of screw heads and 

detachment of the associated balance 

washers. The loss of balance washers would 

increase RAT vibrations, which could lead to 

a possible detachment of RAT parts and loss 

of RAT functionality. The loss of the RAT, in 

combination with a double engine failure, or 

a total loss of normal electrical power 

generation, could result in loss of control of 

the aeroplane. 

For the reasons described above, EASA AD 

2009–0259 was issued in December 2009 to 

require the replacement of all balance weight 

screws on the affected RAT turbine 

assemblies, or replacement of the RAT, if any 

balancing washer was found missing. 

This AD retains some of the requirements 

of AD 2009–0259, which is superseded, and 

corrects its applicability by adding Airbus 

model A320–215 and A320–216 aeroplanes 

which were inadvertently omitted. Also, this 

AD requires the replacement of the set of 

balancing weights screws before the next 

operational or functional check of the RAT 

assembly. 

The MCAI for Model A330 and A340 

series airplanes states: 

Hamilton Sundstrand (HS), the 

manufacturer of the RAT, reported the failure 

of a balance weight fastening screw on the 

RAT cover during a wind tunnel test. After 

investigation, it has been discovered that a 

batch of screws, which are used to attach the 

balance washers of the HS RAT turbine lower 

gear box assembly, has not been subject to 

the correct heat treatment and the screws are 

consequently exposed to potential fracture. 

This condition, if not corrected, might lead 

to the ejection of screw heads and 

consequently to the detachment of the 

associated balance washers. The loss of 

balance washers could increase RAT 

vibrations, which might lead to a possible 

detachment of RAT parts, and thus to damage 

to the aeroplane and risk of injury to persons 

on the ground. 

For the reasons described above, this AD 

requires the identification of the affected 

RAT turbine lower gear box assemblies and 

replacement of all balance screws or, in case 

balance washer detachment is found, 

replacement of the RAT turbine lower gear 

box assembly. * * * 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

1,004 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $100 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these costs. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of the AD 

on U.S. operators to be $271,080, or 

$270 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ’’significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ’’significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 


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47432 Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations 

.gov; or in person at the Docket 

Operations office between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–16–03 Airbus: Amendment 39–16761. 

Docket No. FAA–2011–0388; Directorate 

Identifier 2010–NM–004–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 9, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Airbus airplanes 

listed in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), 

and (c)(5) of this AD, certificated in any 

category. 

(1) Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, F4– 

605R, F4–622R, and C4–605R Variant F 

airplanes; and Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes; 

all certified models, all manufacturer serial 

numbers, if equipped with a Hamilton 

Sundstrand ram air turbine (RAT) turbine 

assembly, as identified by part number (P/N) 

in Hamilton Sundstrand Service Bulletin 

730816–29–15, dated August 4, 2009 (for 

Model A310 airplanes), and Hamilton 

Sundstrand Service Bulletin 732365–29–7, 

dated August 4, 2009 (for Model A300–600 

series airplanes); or equipped with a 

Hamilton Sundstrand RAT turbine lower gear 

box assembly on which the part number 

cannot be determined. 

(2) Airbus Model A318–111, –112, –121, 

and –122 airplanes; Model A319–111, –112, 

–113, –114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, –213, 

–231, and –232 airplanes; all manufacturer 

serial numbers, if equipped with a Hamilton 

Sundstrand RAT turbine assembly Model 

ERPS08M, as identified by part number in 

Hamilton Sundstrand Service Bulletin 

ERPS08M–29–8, dated June 17, 2009; or 

equipped with a Hamilton Sundstrand RAT 

turbine lower gear box assembly on which 

the part number cannot be determined. 

(3) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes; all 

manufacturer serial numbers, if equipped 

with a Hamilton Sundstrand RAT turbine 

lower gearbox assembly, as identified by part 

number in Hamilton Sundstrand Service 

Bulletin ERPS06G–29–6, dated July 20, 2009; 

or equipped with a Hamilton Sundstrand 

RAT turbine lower gear box assembly on 

which the part number cannot be 

determined. 

(4) Model A340–211, –212, –213, –311, 

–312, and –313 airplanes; all manufacturer 

serial numbers, if equipped with a Hamilton 

Sundstrand RAT turbine lower gearbox 

assembly, as identified by part number in 

Hamilton Sundstrand Service Bulletin 

ERPS06G–29–6, dated July 20, 2009; or 

equipped with a Hamilton Sundstrand RAT 

turbine lower gear box assembly on which 

the part number cannot be determined. 

(5) Model A340–541 and –642 airplanes, 

all manufacturer serial numbers, if equipped 

with a Hamilton Sundstrand RAT turbine 

lower gearbox assembly, as identified by part 

number in Hamilton Sundstrand Service 

Bulletin ERPS33G–29–1, dated July 20, 2009; 

or equipped with a Hamilton Sundstrand 

RAT turbine lower gear box assembly on 

which the part number cannot be 

determined. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 29: Hydraulic power. 

Reason 

(e) For Model A310 and A300–600 series 

airplanes, the MCAI describes the unsafe 

condition as: 

Hamilton Sundstrand (HS), the 

manufacturer of the RAT, reported the failure 

during a wind tunnel test of a balance weight 

fastening screw on the RAT turbine cover. 

After investigation, it has been discovered 

that a batch of screws, which are used to 

attach the balance washers of the HS RAT 

Turbine Assembly, has not been subject to 

the correct heat treatment and are 

consequently exposed to potential fracture. 

This condition, if not corrected, might lead 

to the ejection of screw heads and 

consequently to the detachment of the 

associated balance washers. The loss of 

balance washers could increase RAT 

vibrations, which might lead to a possible 

detachment of RAT parts and consequent 

loss of RAT functionality. The loss of the 

RAT, in combination with a total engine 

flame out, could result in loss of control of 

the aeroplane. 

* * * * * 

For Model A318, A319, A320, and A321 

series airplanes, the MCAI describes the 

unsafe condition as: 

Hamilton Sundstrand (HS) reported the 

failure of a balance weight fastening screw on 

the RAT turbine cover during a wind tunnel 

test. After investigation, it has been 

discovered that a batch of screws, used to 

attach the balance washers of the RAT 

Turbine assembly, has not received the 

correct heat treatment, making them more 

subject to a potential failure. 

This condition, if left uncorrected, could 

lead to the ejection of screw heads and 

detachment of the associated balance 

washers. The loss of balance washers would 

increase RAT vibrations, which could lead to 

a possible detachment of RAT parts and loss 

of RAT functionality. The loss of the RAT, in 

combination with a double engine failure, or 

a total loss of normal electrical power 

generation, could result in loss of control of 

the aeroplane. 

* * * * * 

For Model A330 and A340 series airplanes, 

the MCAI describes the unsafe condition as: 

Hamilton Sundstrand (HS), the 

manufacturer of the RAT, reported the failure 

of a balance weight fastening screw on the 

RAT cover during a wind tunnel test. After 

investigation, it has been discovered that a 

batch of screws, which are used to attach the 

balance washers of the HS RAT turbine lower 

gear box assembly, has not been subject to 

the correct heat treatment and the screws are 

consequently exposed to potential fracture. 

This condition, if not corrected, might lead 

to the ejection of screw heads and 

consequently to the detachment of the 

associated balance washers. The loss of 

balance washers could increase RAT 

vibrations, which might lead to a possible 

detachment of RAT parts, and thus to damage 

to the aeroplane and risk of injury to persons 

on the ground. 

* * * * * 

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) At the applicable time specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD: 

Inspect to determine the part number and 

serial number of the RAT turbine lower gear 

box assembly, in accordance with the 

applicable Airbus all operator telex (AOT) 

identified in table 1 of this AD. If the RAT 

turbine lower gear box assembly has a part 

number and a serial number that are not 

listed in the applicable Hamilton Sundstrand 

service bulletin identified in table 2 of this 

AD, no further action is required by this AD, 

except as required by paragraph (k) of this 

AD. A review of airplane maintenance 


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Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 47433 

records is acceptable in lieu of this 

inspection if the part and serial numbers of 

the RAT turbine lower gear box assembly can 

be conclusively determined from that review. 

TABLE 1—AIRBUS AOTS

Model Document Date 

Model A300–600 series airplanes ........................................................................ Airbus AOT A300–29A6062 ................. September 1, 2009. 

Model A310 series airplanes ................................................................................ Airbus AOT A310–29A2098 ................. September 1, 2009. 

Model A318 series airplanes; Model A319 series airplanes; Model A320–211, 

–212, –214, –231, –232, and –233 airplanes; Model A321 series airplanes.

Airbus AOT A320–29A1150 ................. June 24, 2009. 

Model A330–200 and A330–300 series airplanes ............................................... Airbus AOT A330–29A3110 ................. September 1, 2009. 

Model A340–200 and A340n–300 series airplanes ............................................. Airbus AOT A340–29A4085 ................. September 1, 2009. 

Model A340–500 and A340–600 series airplanes ............................................... Airbus AOT A340–500/600–29A5015 .. September 1, 2009. 

(1) For airplanes identified in paragraph 

(c)(1) of this AD: Before the next RAT spin 

test, or within 1,500 flight hours or 9 months 

after the effective date of this AD, whichever 

occurs first. 

(2) For airplanes identified in paragraph 

(c)(2) of this AD: Before the next RAT spin 

test, or within 3,000 flight hours or 12 

months after the effective date of this AD, 

whichever occurs first. 

(3) For airplanes identified in paragraph 

(c)(3), (c)(4), and (c)(5) of this AD: Before the 

next RAT spin test, or within 3,000 flight 

hours or 8 months after the effective date of 

this AD, whichever occurs first. 

(h) If, during the inspection required by 

paragraph (g) of this AD, the RAT turbine 

lower gear box assembly has a part number 

and a serial number identified in the 

applicable Hamilton Sundstrand service 

bulletin specified in table 2 of this AD; or if 

the part number or serial number of the RAT 

turbine lower gear box assembly cannot be 

determined: Before further flight, inspect the 

RAT turbine lower gear box assembly to 

determine if the nameplate is identified with 

the applicable symbol specified in table 3 of 

this AD, in accordance with the applicable 

Airbus AOT specified in table 1 of this AD. 

If the RAT turbine lower gear box assembly 

nameplate has the applicable symbol that is 

identified in table 3 of this AD, no further 

action is required by this AD except as 

required by paragraph (k) of this AD. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

symbol identified on the nameplate can be 

conclusively determined from that review. 

TABLE 2—APPLICABLE HAMILTON SUNDSTRAND SERVICE BULLETINS

Model Document Date 

Model A300–600 series airplanes ........................................................................ Hamilton Sundstrand Service Bulletin 

732365–29–7.

August 4, 2009. 

Model A310 series airplanes ................................................................................ Hamilton Sundstrand Service Bulletin 

730816–29–15.

August 4, 2009. 

Model A318 series airplanes; Model A319 series airplanes; Model A320–211, 

–212, –214, –231, –232, and –233 airplanes; Model A321 series airplanes.

Hamilton Sundstrand Service Bulletin 

ERPS08M–29–8.

June 17, 2009. 

Model A330–200 and A330–300 series airplanes and Model A340–200 and 

A340–300 series airplanes.

Hamilton Sundstrand Service Bulletin 

ERPS06G–29–6.

July 20, 2009. 

Model A340–500 and A340–600 series airplanes ............................................... Hamilton Sundstrand Service Bulletin

ERPS33G–29–1.

July 20, 2009. 

TABLE 3—NAMEPLATE IDENTIFICATION

Model Symbol 

Model A300–600 series airplanes ................................................................................................................................................... 29–7 

Model A310 series airplanes ........................................................................................................................................................... 29–15 

Model A318 series airplanes; Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; 

Model A321 series airplanes ....................................................................................................................................................... 29–8 

Model A330–200 and A330–300 series airplanes .......................................................................................................................... 29–6 

Model A340–200 and A340–300 series airplanes .......................................................................................................................... 29–6 

Model A340–500 and A340–600 series airplanes .......................................................................................................................... 29–1 

(i) If, during the inspection required by 

paragraph (h) of this AD, the RAT turbine 

lower gear box assembly does not have the 

applicable symbol specified in table 3 of this 

AD: Before further flight, do a general visual 

inspection for the missing and fractured 

balance screws and for missing washers in 

accordance with the applicable Airbus AOT 

specified in table 1 of this AD. 

(1) If all balance screws are fitted on the 

turbine and are not fractured or missing, at 

the applicable time specified in paragraph 

(i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD: 

Replace the RAT turbine lower gear box 

assembly with a new or serviceable RAT 

turbine lower gear box assembly, or replace 

all balance screws on the RAT turbine lower 

gear box assembly with new or serviceable 

balance screws, in accordance with the 

applicable Airbus AOT specified in table 1 of 

this AD. 

(i) For airplanes identified in paragraph 

(c)(1) of this AD: Within 1,500 flight hours 

or 9 months after the effective date of this 

AD, whichever occurs first. 

(ii) For airplanes identified in paragraph 

(c)(2) of this AD: Within 3,000 flight hours 

or 12 months after the effective date of this 

AD, whichever occurs first. 

(iii) For airplanes identified in paragraphs 

(c)(3), (c)(4), and (c)(5) of this AD: Within 

3,000 flight hours or 8 months after the 

effective date of this AD, whichever occurs 

first. 

(2) If one or more screws are fractured but 

the associated balance washers are still fitted 

on the RAT turbine lower gear box assembly, 

before further flight, do the actions specified 

in paragraph (i)(2)(i) or (i)(2)(ii) of this AD, 

in accordance with the applicable Airbus 

AOT specified in table 1 of this AD. 

(i) Replace the RAT turbine lower gear box 

assembly with a new or serviceable RAT 

turbine lower gear box assembly. 

(ii) Replace all balance screws on the RAT 

turbine lower gear box assembly with new or 

serviceable balance screws, including 

replacing any missing washers. 


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(3) If one or more screws are fractured and 

any balance washer is missing, before further 

flight, replace the RAT turbine lower gear 

box assembly with new or serviceable RAT 

turbine lower gear box assembly, in 

accordance with the applicable Airbus AOT 

specified in table 1 of this AD. 

Reporting Requirement 

(j) At the applicable time specified in 

paragraph (j)(1) or (j)(2) of this AD, submit a 

report of the findings (both positive and 

negative) of the inspection required by 

paragraph (i) of this AD to Airbus, as 

specified in Paragraph 7 of the applicable 

AOT specified in table 1 of this AD. The 

report must include the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the number of 

landings and flight hours on the airplane. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Parts Installation 

(k) As of the effective date of this AD, no 

person may install, on any airplane, a RAT 

turbine lower gear box assembly, as 

identified by part number in the applicable 

Hamilton Sundstrand service bulletin 

specified in table 2 of this AD, unless it has 

been inspected and all applicable corrective 

actions have been done, in accordance with 

the requirements of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(l) 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: 

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. 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. 

(3) Reporting Requirements: A Federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(m) Refer to the applicable MCAI European 

Aviation Safety Agency (EASA) AD specified 

in table 4 of this AD, the Airbus AOTs 

specified in table 1 of this AD, and the 

Hamilton Sundstrand service bulletins 

specified in table 2 of this AD, for related 

information. 

TABLE 4—EASA ADS

For model— EASA AD— Dated— 

A300–600 and A310 series airplanes ...................................... 2009–0258 December 10, 2009. 

A318, A319, A320, and A321 series airplanes ........................ 2010–0120 June 21, 2010. 

A330 and A340 series airplanes .............................................. 2009–0260 December 10, 2009 (corrected December 14, 2009). 

Material Incorporated by Reference 

(n) You must use the service information 

contained in table 5 of this AD, as applicable, 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 5—MATERIAL INCORPORATED BY REFERENCE

Document Date 

Airbus All Operator Telex A300–29A6062 .............................................................................................................................. September 1, 2009. 

Airbus All Operator Telex A310–29A2098 .............................................................................................................................. September 1, 2009. 

Airbus All Operator Telex A320–29A1150 .............................................................................................................................. June 24, 2009. 

Airbus All Operator Telex A330–29A3110 .............................................................................................................................. September 1, 2009. 

Airbus All Operator Telex A340–29A4085 .............................................................................................................................. September 1, 2009. 

Airbus All Operator Telex A340–500/600–29A5015 ............................................................................................................... September 1, 2009. 

Hamilton Sundstrand Service Bulletin 732365–29–7 .............................................................................................................. August 4, 2009. 

Hamilton Sundstrand Service Bulletin 730816–29–15 ............................................................................................................ August 4, 2009. 

Hamilton Sundstrand Service Bulletin ERPS08M–29–8 ......................................................................................................... June 17, 2009. 

Hamilton Sundstrand Service Bulletin ERPS06G–29–6 ......................................................................................................... July 20, 2009. 

Hamilton Sundstrand Service Bulletin ERPS33G–29–1 ......................................................................................................... July 20, 2009. 

(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 Airbus service information 

identified in this AD, contact the appropriate 

office listed below. 

(i) For Model A300–600 and A310 series 

airplanes: Airbus SAS—EAW (Airworthiness 

Office), 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(ii) For Model A318, A319, A320, and 

A321 series airplanes: Airbus, Airworthiness 


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Federal Register / Vol. 76, No. 151 / Friday, August 5, 2011 / Rules and Regulations 47435 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(iii) For Model A330 and A340 series 

airplanes: 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; e-mail 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(3) For Hamilton Sundstrand service 

information identified in this AD, contact 

Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 Harrison 

Avenue, P.O. Box 7002, Rockford, Illinois 

61125–7002; telephone 860–654–3575; fax 

860–998–4564; e-mail 

tech.solutions@hs.utc.com; Internet http:// 

www.hamiltonsundstrand.com. 

(4) 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. 

(5) 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 July 20, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–19433 Filed 8–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–0516; Airspace 

Docket No. 11–ANM–12] 

Modification of Class E Airspace; 

Forsyth, MT 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action will modify Class 

E airspace at Forsyth, MT. Controlled 

airspace is necessary to accommodate 

aircraft using Area Navigation (RNAV) 

Global Positioning System (GPS) 

standard instrument approach 

procedures at Tillitt Field Airport. This 

action also corrects a typographical 

error in the regulatory text for the Class 

E airspace area. This action improves 

the safety and management of 

Instrument Flight Rules (IFR) operations 

at the airport. 

DATES: Effective date, 0901 UTC, 

October 20, 2011. The Director of the 

Federal Register approves this 

incorporation by reference action under 

1 CFR part 51, subject to the annual 

revision of FAA Order 7400.9 and 

publication of conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Eldon Taylor, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue, SW., Renton, WA 98057; 

telephone (425) 203–4537. 

SUPPLEMENTARY INFORMATION: 

History 

On June 7, 2011, the FAA published 

in the Federal Register a notice of 

proposed rulemaking to modify 

controlled airspace at Forsyth, MT (76 

FR 32879). Interested parties were 

invited to participate in this rulemaking 

effort by submitting written comments 

on the proposal to the FAA. No 

comments were received. 

Class E airspace designations are 

published in paragraph 6005 of FAA 

Order 7400.9U dated August 18, 2010, 

and effective September 15, 2010, which 

is incorporated by reference in 14 CFR 

Part 71.1. The Class E airspace 

designations listed in this document 

will be published subsequently in that 

Order. 

The Rule 

This action amends Title 14 Code of 

Federal Regulations (14 CFR) part 71 by 

modifying Class E airspace extending 

upward from 700 feet above the surface, 

at Tillitt Field Airport, Forsyth, MT, to 

accommodate IFR aircraft executing 

RNAV (GPS) standard instrument 

approach procedures at the airport. This 

action also corrects a typographical 

error in the regulatory text of the Class 

E airspace area by correcting ‘lat. 

46°05′00′′ N., long. 106°210′3′′ W.’ to 

‘lat. 46°05′ 00′′ N., long. 106°21′ 03′′ W.’. 

This action is necessary for the safety 

and management of IFR operations. 

Except for administrative changes, and 

the changes listed above, this rule is the 

same as that proposed in the NPRM. 

The FAA has determined this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. Therefore, this regulation: (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) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified this rule, when promulgated, 

will not have a significant economic 

impact on a substantial number of small 

entities under the criteria of the 

Regulatory Flexibility Act. The FAA’s 

authority to issue rules regarding 

aviation safety is found in Title 49 of the 

U.S. Code. Subtitle 1, Section 106 

discusses the authority of the FAA 

Administrator. Subtitle VII, Aviation 

Programs, describes in more detail the 

scope of the agency’s authority. This 

rulemaking is promulgated under the 

authority described in Subtitle VII, Part 

A, Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 

scope of that authority as it establishes 

additional controlled airspace at Tillitt 

Field Airport, Forsyth, MT. 

List of Subjects in 14 CFR Part 71 

Airspace, Incorporation by reference, 

Navigation (air). 

Adoption of the Amendment 

In consideration of the foregoing, the 

Federal Aviation Administration 

amends 14 CFR part 71 as follows: 

PART 71—DESIGNATION OF CLASS A, 

B, C, D AND E AIRSPACE AREAS; AIR 

TRAFFIC SERVICE ROUTES; AND 

REPORTING POINTS 

■ 1. The authority citation for 14 CFR 

Part 71 continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40103, 40113, 

40120; E. O. 10854, 24 FR 9565, 3 CFR, 1959– 

1963 Comp., p. 389. 

§ 71.1 [Amended] 

■ 2. The incorporation by reference in 

14 CFR Part 71.1 of the Federal Aviation 

Administration Order 7400.9U, 

Airspace Designations and Reporting 

Points, dated August 18, 2010, and 

effective September 15, 2010 is 

amended as follows: 

Paragraph 6005 Class E airspace areas 

extending upward from 700 feet or more 

above the surface of the earth. 

* * * * * 

ANM MT E5 Forsyth, MT [Modified] 

Tillitt Field Airport, MT 

(Lat. 46°16′16′′ N., long. 106°37′26′′ W.) 

That airspace extending upward from 700 

feet above the surface within a 7-mile radius 

of Tillitt Field Airport, and within 2.5 miles 

north and 5.5 miles south of the 075° bearing 

of the airport extending from the 7-mile 

radius to 13 miles east of the airport; that 

airspace extending upward from 1,200 feet 


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