This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

25259 

Vol. 76, No. 86 

Wednesday, May 4, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0388; Directorate 

Identifier 2010–NM–004–AD] 

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), 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) 

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. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by June 20, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact the 

appropriate office listed below. 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. 

• 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. 

• For Model A318, A319, A320, and 

A321 series airplanes: Airbus, 

Airworthiness 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. 

• 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. 

• 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, IL 61125–7002; telephone 

860–654–3575; fax 860–998–4564; email tech.solutions@hs.utc.com; Internet 

http://www.hamiltonsundstrand.com. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
25260 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 

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 (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

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–2011–0388; Directorate Identifier 

2010–NM–004–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 we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued the EASA 

airworthiness directives identified in 

the following table (referred to after this 

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

condition for the specified products. 

TABLE—APPLICABLE 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). 

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. 

Relevant Service Information 

Airbus has issued the following all 

operator telexes (AOTs). 

TABLE—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. 


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Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 25261 

TABLE—AIRBUS AOTS—Continued 

Model Document Date 

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 A340–300 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. 

Hamilton Sundstrand has issued the 

following service bulletins. 

TABLE—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. 

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 another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

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 proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 1,004 products of U.S. 

registry. We also estimate that it would 

take about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would 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 

proposed 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 proposed AD 

will not have federalism implications 

under Executive Order 13132. This 

proposed 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, 

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, Incorporation by reference, 

Safety. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
25262 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 

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: 

Airbus: Docket No. FAA–2011–0388; 

Directorate Identifier 2010–NM–004–AD. 

Comments Due Date 

(a) We must receive comments by June 20, 

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 

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. 


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Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 25263 

TABLE 1—AIRBUS AOTS—Continued 

Model Document Date 

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 A340–300 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. 

(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 


srobinson on DSKHWCL6B1PROD with PROPOSALS
25264 Federal Register / Vol. 76, No. 86 / Wednesday, May 4, 2011 / Proposed Rules 

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, 

and 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). 

Issued in Renton, Washington, on April 26, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–10816 Filed 5–3–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0450; Directorate 

Identifier 2011–CE–010–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company (Cessna) Models 

337, 337A (USAF 02B), 337B, 337C, 

337D, 337E, T337E, 337F, T337F, 337G, 

T337G, M337B, F 337E, FT337E, F 

337F, FT337F, F 337G, and FT337GP 

Airplanes 

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 would require inspecting the wings 

for internal and external damage, 

repairing any damage, reinforcing the 

wings, installing operational limitation 

placards in the cockpit, and adding 

limitations to the airplane flight manual 

supplement. This proposed AD was 

prompted by a review of installed Flint 

Aero, Inc. wing tip auxiliary fuel tanks, 

Supplemental Type Certificate (STC) 

SA5090NM. We are issuing this 

proposed AD to detect and correct 

damage in the wings and to prevent 

overload failure of the wing due to the 

installation of the STC. Damage in the 

wing or overload failure of the wing 

could result in structural failure of the 

wing, which could result in loss of 

control. 

DATES: We must receive comments on 

this proposed AD by June 20, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Flint Aero, 

Inc., 1942 Joe Crosson Drive, El Cajon, 

CA 92020; phone: (619) 448–1551; fax: 

(619) 448–1571; Internet: http:// 

www.flintaero.com. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

MO 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 


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