Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules 81885 

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, Incorporation by reference, 

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: 

Airbus: Docket No. FAA–2011–1327; 

Directorate Identifier 2011–NM–091–AD. 

(a) Comments Due Date 

We must receive comments by February 

13, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

223F, –243F, –201, –202, –203, –223, –243, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers, except 

airplanes on which Airbus modification 

200616 has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by a report of 

corrosion found on the main fitting of the 

nose landing gear (NLG) leg in the vicinity 

of the dowel pin bushes retaining the lower 

steering flange. We are issuing this AD to 

prevent NLG main fitting rupture, which 

could result in an NLG collapse. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Actions 

At the later of the times specified in 

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

as applicable, modify the NLG main fitting by 

adding primer paint to the cadmium around 

the dowel bush holes, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3241, 

dated November 26, 2010 (for Model A330– 

200 and –300 airplanes); or A340–32–4282, 

dated November 26, 2010 (for Model A340– 

200 and –300 airplanes). 

(1) Within 60 months since first flight of 

the NLG on any airplane. 

(2) Within 60 months since first flight of 

the NLG on any airplane after the most recent 

overhaul of the NLG. 

(3) Within 24 months after the effective 

date of this AD. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: (425) 227–1138; fax: (425) 227– 

1149. Information may be emailed to: 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0032, dated March 1, 2011; Airbus 

Mandatory Service Bulletin A330–32–3241, 

dated November 26, 2010; and Airbus 

Mandatory Service Bulletin A340–32–4282, 

dated November 26, 2010; for related 

information. 

Issued in Renton, Washington, on 

December 16, 2011. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–33341 Filed 12–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0223; Directorate 

Identifier 2010–NM–161–AD] 

RIN 2120–AA64 

Airworthiness Directives; Goodrich 

Evacuation Systems Approved Under 

Technical Standard Order (TSO) TSO– 

C69b and Installed on Airbus Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for Goodrich Evacuation Systems 

approved under Technical Standard 

Order (TSO) TSO–C69b and installed on 

Airbus Model A330–200 and –300 series 

airplanes, Model A340–200 and –300 

series airplanes, and Model A340–500 

and –600 series airplanes. That NPRM 

proposed to supersede an existing AD. 

That NPRM proposed inspecting to 

determine the part number of the 

pressure relief valves on the affected 

Goodrich evacuation systems, replacing 

certain pressure relief valves, and 

adding airplanes to the applicability. 

That NPRM was prompted by reports 

that during workshop testing, certain 

pressure relief valves, which were 

required by the existing AD, did not seal 


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and allowed the pressure in certain 

slides/rafts to fall below the minimum 

raft mode pressure for the unit. This 

action revises that NPRM by adding 

certain airplanes to the applicability. 

We are proposing this supplemental 

NPRM to correct the unsafe condition 

on these products. Since these actions 

impose an additional burden over that 

proposed in the NPRM, we are 

reopening the comment period to allow 

the public the chance to comment on 

these proposed changes. 

DATES: We must receive comments on 

this supplemental NPRM by February 

13, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Goodrich Corporation, 

Aircraft Interior Products, ATTN: 

Technical Publications, 3414 South 

Fifth Street, Phoenix, Arizona 85040; 

phone: (602) 243–2270; email: 

george.yribarren@goodrich.com; 

Internet: http://www.goodrich.com/ 

TechPubs. You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call (425) 227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at 

http://www.regulations.gov; or in person 

at the Docket Management Facility 

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

through Friday, except Federal holidays. 

The AD docket contains this proposed 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Office (phone: (800) 647–5527) 

is in the ADDRESSES section. Comments 

will be available in the AD docket 

shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Tracy Ton, Aerospace Engineer, Cabin 

Safety/Mechanical and Environmental 

Systems Branch, ANM–150L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: (562) 

627–5352; fax: (562) 627–5210; email: 

Tracy.Ton@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–2011–0223; Directorate Identifier 

2010–NM–161–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 because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

apply to Goodrich evacuation systems 

approved under TSO–C69b and 

installed on certain Model A330–200 

and –300 series airplanes, Model A340– 

200 and –300 series airplanes, and 

Model A340–541 and –642 airplanes. 

That NPRM was published in the 

Federal Register on March 21, 2011 (76 

FR 15229). That NPRM proposed to 

supersede AD 2007–23–01, Amendment 

39–15247 (72 FR 62568, November 6, 

2007). That NPRM proposed to require 

inspecting to determine the part number 

of the pressure relief valves on the 

affected Goodrich evacuation systems, 

replacing certain pressure relief valves 

with new improved valves, and marking 

the system identification placard on the 

girt of the replaced part. That NPRM 

also proposed to add Model A330–223F 

and –243F airplanes to the applicability. 

Actions Since AD 2007–23–01, 

Amendment 39–15247 (72 FR 62568, 

November 6, 2007) Was Issued 

Since we issued AD 2007–23–01, 

Amendment 39–15247 (72 FR 62568, 

November 6, 2007, Model A330–302 

and –303 have been added to the United 

States Type Certificate Data Sheet 

A46NM and we have determined they 

are affected by the identified unsafe 

condition. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM (76 FR 

15229, March 21, 2011). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Support for NPRM (76 FR 15229, 

March 21, 2011) 

Hawaiian Airlines concurred with the 

NPRM (76 FR 15229, March 21, 2011). 

Request To Use Later Revisions of 

Goodrich Service Information 

Airbus stated that there are later 

revisions of the service information that 

should be referenced in the NPRM (76 

FR 15229, March 21, 2011). Airbus 

stated that these revisions are Goodrich 

Service Bulletin 7A1508/09/10/39–25– 

373, Revision 3, dated March 30, 2011; 

and Goodrich Service Bulletin 4A3928/ 

4A3934–25–374, Revision 2, dated 

March 30, 2011. Airbus did not 

provided justification for the request. 

We agree, because Goodrich Service 

Bulletin 7A1508/09/10/39–25–373, 

Revision 3, dated March 30, 2011; and 

Goodrich Service Bulletin 4A3928/ 

4A3934–25–374, Revision 2, dated 

March 30, 2011; are the latest revisions 

and do not change the actions proposed 

in this supplemental NPRM. We have 

revised the supplemental NPRM to refer 

to these revisions. We have also revised 

paragraph (j) of the supplemental NPRM 

to give credit for doing the applicable 

actions specified in this supplemental 

NPRM before the effective date of the 

AD in accordance with Goodrich 

Service Bulletin 7A1508/09/10/39–25– 

373, Revision 2, dated May 8, 2009; and 

Goodrich Service Bulletin 4A3928/ 

4A3934–25–374, Revision 1, dated May 

8, 2009. 

Request To Include Changing the Firing 

Pin Cable of Right Hand Configurations 

in This NPRM (76 FR 15229, March 21, 

2011) 

Airbus and the European Aviation 

Safety Agency (EASA) requested that 

the NPRM (76 FR 15229, March 21, 

2011) be revised to include replacing 

certain firing pin cables. Airbus stated 

that they want the NPRM to include 

changing of the firing pin cable of right 

hand configurations of part number 

(P/N) 4A3928 series escape slides. 

Airbus stated that the NPRM preamble 

section ‘‘Differences Between the 

Proposed AD and the Service 

Information’’ makes a statement that 

changes to certain firing pin cables are 

not included in the AD. Airbus stated 

that the change to the firing pin cables 

improves the reliability of the automatic 

inflation as required by part 25 of the 


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Federal Aviation Regulations 

(25.810(a)(1)(i)). EASA stated that 

marking the modified slide unit without 

accomplishing this action would be 

impossible. 

We do not agree. This supplemental 

NPRM proposes to supersede AD 2007– 

23–01, Amendment 39–15247, (72 FR 

62568, November 6, 2007), to correct 

certain pressure relief valves that did 

not seal and allowed the pressure in 

slides/rafts to fall below the minimum 

raft mode pressure for the unit and add 

airplanes to the applicability. This 

supplemental NPRM is necessary to 

prevent loss of pressure in the escape 

slides/rafts after an emergency 

evacuation, which could result in 

inadequate buoyancy to support the 

raft’s passenger capacity during ditching 

and increase the chance for injury to raft 

passengers. The purpose of an AD is to 

correct an identified unsafe condition in 

airplanes. We consider the firing pin 

cable replacement a design 

improvement and not an action that 

addresses the identified unsafe 

condition. Additionally, Goodrich 

Service Bulletin 4A3928/4A3934–25– 

374, Revision 1, dated May 8, 2009, 

included the replacement of firing pin 

cable P/N 4A3622–3 for only Model 

A340–500 Door 3 right hand slides (P/ 

N 4A3928–4 and –6) as an improvement 

of the automatic inflation reliability. 

Goodrich Service Bulletin 4A3928/ 

4A3934–25–374, Revision 1, dated May 

8, 2009, did not specify replacement of 

firing pin cable for other airplanes in the 

applicability of this supplemental 

NPRM. We have not changed the 

supplemental NPRM in this regard. 

Request To Use Generic Term Model 

A330–200 and –300, and Model A340– 

200 and –300 Airplanes 

Airbus requested that the generic term 

Model A330–200 and –300 airplanes be 

used in lieu of Model A330–201, –202, 

–203, –223, –223F, –243, –243F, –301, 

–302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model 

A340–200 and –300 airplanes be used in 

lieu of Model A340–211, –212, –213, 

–311, –312, and –313 airplanes; in 

paragraph (c) of the NPRM (76 FR 

15229, March 21, 2011). 

We agree. We have revised paragraph 

(c) of this AD accordingly. 

Request To Use Generic Term Model 

A340–500 and –600 Airplanes 

Airbus requested that generic term 

Model A340–500 and –600 airplanes be 

used in lieu of Model A340–541 and 

–642 in applicability paragraph (c) of 

the NPRM (76 FR 15229, March 21, 

2011). As justification for its request, 

Airbus stated that evacuation slides and 

included equipment (pressure reducing 

valve) may be removed from Model 

A340–542 airplanes and be installed on 

Model A340–541 and –642 airplanes. 

We agree. We have revised paragraph 

(c) of this AD accordingly. 

Request To Include Model A340–542 

and A340–643 Airplanes 

EASA requested that Model A340– 

542 and A340–643 airplanes be 

included in the AD applicability. EASA 

requested the change to allow it to adopt 

future FAA ADs without changes. 

We agree to revise the applicability of 

the AD. As stated previously, we have 

revised paragraph (c) of this AD to 

include the generic term Model A340– 

500 and –600 series airplanes. 

FAA’s Determination 

We are proposing this supplemental 

NPRM because we evaluated all the 

relevant information and determined 

the unsafe condition described 

previously is likely to exist or develop 

in other products of the same type 

design. Certain changes described above 

expand the scope of the NPRM (76 FR 

15229, March 21, 2011). As a result, we 

have determined that it is necessary to 

reopen the comment period to provide 

additional opportunity for the public to 

comment on this supplemental NPRM. 

Proposed Requirements of the 

Supplemental NPRM 

This supplemental NPRM would 

require accomplishing the actions 

specified in the service information 

described previously. The supplemental 

NPRM also adds Model A330–302 and 

–303 airplanes to the applicability. 

Costs of Compliance 

We estimate that this proposed AD 

affects 41 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection to determine part numbers ........ 1 work-hour × $85 per hour = $85 ............. $0 $85 Up to $3,485. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these replacements. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Valve replacement ..................................................... 1 work-hour × $85 per hour = $85 .......................... $775 $860 per slide. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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 


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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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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 

removing airworthiness directive 

(AD) 2007–23–01, Amendment 39– 

15247 (72 FR 62568, November 6, 2007), 

and adding the following new AD: 

Goodrich (Formerly BF Goodrich): Docket 

No. FAA–2011–0223; Directorate 

Identifier 2010–NM–161–AD. 

(a) Comments Due Date 

We must receive comments by February 

13, 2012. 

(b) Affected ADs 

This AD supersedes AD 2007–23–01, 

Amendment 39–15247 (72 FR 62568, 

November 6, 2007). 

(c) Applicability 

This AD applies to Goodrich evacuation 

systems approved under Technical Standard 

Order (TSO) TSO–C69b, as installed on the 

Airbus airplanes, certificated in any category, 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD. 

(1) Model A330–200 and –300 series 

airplanes, and Model A330–200 freighter 

series airplanes, as identified in Goodrich 

Service Bulletin 7A1508/09/10/39–25–373, 

Revision 3, dated March 30, 2011. 

(2) Model A340–200 and –300 series 

airplanes, as identified in Goodrich Service 

Bulletin 7A1508/09/10/39–25–373, Revision 

3, dated March 30, 2011. 

(3) Model A340–500 and –600 series 

airplanes, as identified in Goodrich Service 

Bulletins 7A1508/09/10/39–25–373, Revision 

3, dated March 30, 2011; and 4A3928/ 

4A3934–25–374, Revision 2, dated March 30, 

2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2560, Emergency Equipment. 

(e) Unsafe Condition 

This AD was prompted by reports that 

during workshop testing, certain pressure 

relief valves did not seal and allowed the 

pressure in certain slides/rafts to fall below 

the minimum raft mode pressure for the unit. 

We are issuing this AD to prevent loss of 

pressure in the escape slides/rafts after an 

emergency evacuation, which could result in 

inadequate buoyancy to support the raft’s 

passenger capacity during ditching and 

increase the chance for injury to raft 

passengers. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 36 months after the effective date 

of this AD, inspect the evacuation systems to 

determine whether any pressure relief valve 

having part number (P/N) 4A3641–1, 

4A3791–3, 4A3641–26, or 4A3791–6 is 

installed. A review of airplane maintenance 

records or the system identification placard 

on the girt is acceptable in lieu of this 

inspection if the part number of the pressure 

relief valve can be conclusively determined 

from that review. 

(h) Part Replacement 

If any valve having P/N 4A3641–1, 

4A3791–3, 4A3641–26, or 4A3791–6 is 

identified during the inspection or review 

specified in paragraph (g) of this AD: Before 

further flight, do the applicable actions 

required by paragraphs (h)(1) and (h)(2) of 

this AD: 

(1) Replace all pressure relief valves having 

P/Ns 4A3641–1 and 4A3791–3 with pressure 

relief valves having P/N 115815–1, and mark 

the system identification placard on the girt, 

in accordance with the Accomplishment 

Instructions of Goodrich Service Bulletin 

7A1508/09/10/39–25–373, Revision 3, dated 

March 30, 2011. 

(2) Replace all pressure relief valves having 

P/Ns 4A3641–26 and 4A3791–6 with 

pressure relief valves having P/N 115815–1 

(for evacuation systems having P/N 4A3934 

series units) or 115815–2 (for evacuation 

systems P/N 4A3928 series units); and mark 

the system identification placard on the girt; 

in accordance with the Accomplishment 

Instructions of Goodrich Service Bulletin 

4A3928/4A3934–25–374, Revision 2, dated 

March 30, 2011. 

(i) Parts Installation 

As of the effective date of this AD, no 

person may install a pressure relief valve 

having P/N 4A3641–1, 4A3791–3, 4A3791–6, 

or 4A3641–26 in the evacuation system on 

any airplane. 

(j) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Actions accomplished before the effective 

date of this AD in accordance with Goodrich 

Service Bulletin 7A1508/09/10/39–25–373, 

dated March 31, 2008, Goodrich Service 

Bulletin 7A1508/09/10/39–25–373, Revision 

1, dated August 1, 2008, or Goodrich Service 

Bulletin 7A1508/09/10/39–25–373, Revision 

2, dated May 8, 2009; or Goodrich Service 

Bulletin 4A3928/4A3934–25–374, dated July 

18, 2008, or Goodrich Service Bulletin 

4A3928/4A3934–25–374, Revision 1, dated 

May 8, 2009; as applicable; are acceptable for 

compliance with the corresponding 

requirements of this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

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. 

(l) Related Information 

(1) For more information about this AD, 

contact Tracy Ton, Aerospace Engineer, 

Cabin Safety/Mechanical and Environmental 

Systems Branch, ANM–150L, FAA, Los 

Angeles Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, California 

90712–4137; phone: (562) 627–5352; fax: 

(562) 627–5210; email: 

(2) For service information identified in 

this AD, contact Goodrich Corporation, 

Aircraft Interior Products, ATTN: Technical 

Publications, 3414 South Fifth Street 

Phoenix, Arizona 85040; phone: (602) 243– 

2270; email: http:// 

www.george.yribarren@goodrich.com; 

Internet: http://www.goodrich.com/ 

TechPubs. You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. For 


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information on the availability of this 

material at the FAA, call (425) 227–1221. 

Issued in Renton, Washington, on 

December 16, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–33359 Filed 12–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1410; Directorate 

Identifier 2011–NM–033–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all Saab 

AB, Saab Aerosystems Model SAAB 

2000 airplanes. This proposed AD was 

prompted by reports of hydraulic 

accumulator failure. This proposed AD 

would require replacing certain 

hydraulic accumulators with stainless 

steel hydraulic accumulators, and 

structural modifications in the nose 

landing gear bay. We are proposing this 

AD to prevent failure of hydraulic 

accumulators, which may result in 

damage to the airplane and injury to 

occupants. 

DATES: We must receive comments on 

this proposed AD by February 13, 2012. 

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 W12–140, 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 Saab AB, 

Saab Aerosystems, SE–581 88, 

Linko ̈ping, Sweden; telephone +46 13 

18 5591; fax +46 13 18 4874; email 

saab2000.techsupport@saabgroup.com; 

Internet http://www.saabgroup.com. 

You may review copies of the 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call (425) 227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket 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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1112; 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–2011–1410; Directorate Identifier 

2011–NM–033–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 EASA 

Airworthiness Directive 2011–0004, 

dated January 17, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Three cases of failure have been reported, 

affecting the same type of hydraulic 

accumulator as installed on SAAB 2000 

aeroplanes, although all occurred on other 

aeroplane types. The reported cause of these 

failures has been traced to corrosion. Any of 

the end parts on the accumulator may depart 

from the pressure vessel if they are affected 

by corrosion. 

This condition, if not detected and 

corrected, may lead to fatigue failure of a 

hydraulic accumulator, possibly resulting in 

damage to the aeroplane and injury to 

occupants. In addition, a quality issue during 

the replacement of the base material in the 

end parts of the accumulator may have 

affected the service life of the accumulator. 

To address this unsafe condition, SAAB 

has introduced a new type of hydraulic 

accumulator, which is made of stainless 

steel. 

For the reasons described above, this 

[EASA] AD requires the replacement of all 

Part Number (P/N) 08 8423 030 1 hydraulic 

accumulators with stainless steel P/N 40800– 

2050 hydraulic accumulators and associated 

structural modifications in the nose landing 

gear bay. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Saab has issued Service Bulletin 

2000–29–024, Revision 01, dated 

November 5, 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 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. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 8 products of U.S. registry. 

We also estimate that it would take 

about 12 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 $9,995 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 parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 


wreier-aviles on DSK3TPTVN1PROD with PROPOSALS