76230 Federal Register / Vol. 77, No. 248 / Thursday, December 27, 2012 / Rules and Regulations 

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; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

December 7, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30369 Filed 12–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1222; Directorate 

Identifier 2010–NM–268–AD; Amendment 

39–17286; AD 2012–25–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This AD was prompted 

by reports of escape slides failing to 

deploy from the forward and aft righthand doors during scheduled 

maintenance slide deployments. This 

AD requires modifying the escape slide. 

Also, for certain airplanes, this AD 

requires modifying or replacing the 

Vespel piston. For certain other 

airplanes, this AD requires an additional 

modification of the escape slide. We are 

issuing this AD to prevent failure of an 

escape slide to deploy, which could 

result in the slide being unusable during 

an emergency evacuation and increased 

likelihood of injury to passengers or 

crewmembers due to the difficulty in 

evacuating the airplane. 

DATES: This AD is effective January 31, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of January 31, 2013. 

ADDRESSES: For service information 

identified in this AD, Goodrich 

Corporation, Aircraft Interior Products 

ATTN: Technical Publications, 3414 

South Fifth Street, Phoenix, Arizona 

85040; phone: 602–243–2270; 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, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

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

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sarah Piccola, Aerospace Engineer, 

Cabin Safety & Environmental Systems 

Branch, ANM–150S, Seattle Aircraft 

Certification Office (ACO), FAA, 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6483; fax: 425– 

917–6590; email: sarah.piccola@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on August 31, 2012 (77 FR 

53155). The original NPRM (76 FR 

69159, November 8, 2011) proposed to 

require checking the escape slide girt for 

serviceability, and replacement if 

necessary; modifying the cable routing 

provision; replacing the regulator 

padding; modifying the aspirator 

orientation; and modifying the valise. 

The original NPRM also proposed to 

require, for certain airplanes, modifying 

or replacing the Vespel piston, 

modifying the pilot valve regulator, 

installing a new firing cable and safety 

pin, and modifying the slide valise. The 

SNPRM proposed to add airplanes to 

the applicability of the original NPRM, 

and specify revised service information. 

For certain other airplanes, this AD 

requires an additional modification of 

the escape slide. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Support for the SNPRM (77 FR 53155, 

August 31, 2012) 

Boeing stated that it concurs with the 

contents of the SNPRM (77 FR 53155, 

August 31, 2012), and therefore, no 

additional comments will be 

forthcoming. 

Goodrich Corporation stated that the 

comments it submitted to the original 

NPRM (76 FR 69159, November 8, 2011) 

have been satisfactorily addressed, and 

therefore, it has no additional comments 

or changes to offer. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed–except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM (77 FR 

53155, August 31, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (77 FR 53155, 

August 31, 2012). 

Additional Change Made to This Final 

Rule 

We have removed the girt 

replacement on-condition cost specified 

in the SNPRM (77 FR 53155, August 31, 

2012) from this AD, because the 

proposed girt check for continued 

serviceability was removed from the 

SNPRM and is not included in this AD. 

Costs of Compliance 

We estimate that this AD affects 557 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 77, No. 248 / Thursday, December 27, 2012 / Rules and Regulations 76231 

ESTIMATED COSTS

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

Modify girt and valise, and 

replace padding.

2 work-hours × $85 per 

hour = $170.

$223 .................................. $393 .................................. $218,901. 

Modify regulator valve, install cable and pin, and 

modify slide valise.

1 work-hour × $85 per 

hour = $85.

Between $1,749 and 

$1,836.

Between $1,834 and 

$1,921.

Between $1,021,538 and 

$1,069,997. 

Modify Vespel piston ......... 1 work-hour × $85 per 

hour = $85.

$0 ...................................... $85 .................................... $47,345. 

Optional Vespel piston replacement.Up to 1 work-hour × $85 

per hour = $85.

Up to $612 ........................ Up to $697 ........................ Up to $388,229. 

According to the parts supplier, some 

of the costs of this 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 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–25–05 The Boeing Company: 

Amendment 39–17286; Docket No. 

FAA–2011–1222; Directorate Identifier 

2010–NM–268–AD. 

(a) Effective Date 

This AD is effective January 31, 2013. 

(b) Affected ADs 

This AD affects AD 2008–24–08, 

Amendment 39–15748 (73 FR 72320, 

November 28, 2008). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–600, –700, –700C, –800, –900, 

and –900ER series airplanes, certificated in 

any category, with Goodrich Corporation 

door escape slide part number (P/N) 5A3307– 

1, –3, –5, or –301, serial numbers (S/N) 

BNG0001 through BNG14499 inclusive. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 25, Equipment/Furnishings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

escape slides failing to deploy from the 

forward and aft right-hand doors during 

scheduled maintenance slide deployments. 

We are issuing this AD to prevent failure of 

an escape slide to deploy, which could result 

in the slide being unusable during an 

emergency evacuation and increased 

likelihood of injury to passengers or 

crewmembers due to the difficulty in 

evacuating the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Slide Modification 

Within 36 months after the effective date 

of this AD: Modify the escape slide, in 

accordance with the Accomplishment 

Instructions of Goodrich Service Bulletin 

5A3307–25–389, Revision 2, dated May 4, 

2012. 

(h) Concurrent Requirements 

(1) For slide P/N 5A3307–301: Prior to or 

concurrently with accomplishing the actions 

required by paragraph (g) of this AD, modify 

the escape slide, in accordance with the 

Accomplishment Instructions of Goodrich 

Service Bulletin 5A3307–25–339, Revision 5, 

dated May 4, 2012. 

(2) For slide P/N 5A3307–301 or 5A3307– 

5: Prior to or concurrently with 

accomplishing the actions required by 

paragraph (g) of this AD, modify the Vespel 

piston in the regulator valves, or replace the 

Vespel piston with a new or serviceable 

Vespel piston P/N 3A3566–2 or 3A3832–2, as 

applicable, in accordance with the 

Accomplishment Instructions of Goodrich 

Service Bulletin 25–349, Revision 1, dated 

January 11, 2010. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (h)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using the service 

bulletins specified in paragraphs (i)(1)(i) 

through (i)(1)(iv) of this AD, which are not 

incorporated by reference in this AD. 

(i) Goodrich Service Bulletin 5A3307–25– 

339, Revision 1, dated September 26, 2003. 

(ii) Goodrich Service Bulletin 5A3307–25– 

339, Revision 2, dated March 31, 2004. 

(iii) Goodrich Service Bulletin 5A3307–25– 

339, Revision 3, dated May 8, 2009. 

(iv) Goodrich Service Bulletin 5A3307–25– 

339, Revision 4, dated October 1, 2011. 

(2) This paragraph provides credit for the 

modification or replacement of the Vespel 

piston in the regulator valves required by 

paragraph (h)(2) of this AD, if those actions 


pmangrum on DSK3VPTVN1PROD with 
76232 Federal Register / Vol. 77, No. 248 / Thursday, December 27, 2012 / Rules and Regulations 

were performed before the effective date of 

this AD using Goodrich Service Bulletin 25– 

349, dated September 15, 2004, which is not 

incorporated by reference in this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(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 emailed 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Sarah Piccola, Aerospace Engineer, 

Cabin Safety & Environmental Systems 

Branch, ANM–150S, Seattle Aircraft 

Certification Office (ACO), FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6483; fax: 425–917–6590; 

email: sarah.piccola@faa.gov. 

(2) For Goodrich 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; Internet: http:// 

www.goodrich.com/TechPubs. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Goodrich Service Bulletin 25–349, 

Revision 1, dated January 11, 2010. 

(ii) Goodrich Service Bulletin 5A3307–25– 

339, Revision 5, dated May 4, 2012. 

(iii) Goodrich Service Bulletin 5A3307–25– 

389, Revision 2, dated May 4, 2012. 

(3) For Goodrich 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; Internet: http:// 

www.goodrich.com/TechPubs. 

(4) You may review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

December 4, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–29999 Filed 12–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0946; Directorate 

Identifier 2012–CE–037–AD; Amendment 

39–17294; AD 2012–18–10 R1] 

RIN 2120–AA64 

Airworthiness Directives; GA200 (Pty) 

Ltd Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for all 

GA200 (Pty) Ltd Models GA200 and 

GA200C airplanes. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as failure 

of the wing strut bolt through the main 

spar. We are issuing this AD to require 

actions to address the unsafe condition 

on these products. 

DATES: This AD is effective January 31, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of January 31, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of September 14, 2012 (77 FR 

55686, September 11, 2012). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

For service information identified in 

this AD, contact GippsAero, P.O. Box 

881, Morwell, Victoria 3840, Australia, 

telephone: + 61 (0) 3 5172 1200; fax + 

61 (0) 3 5172 1201; email: 

support@gippsaero.com; Internet: 

www.gippsaero.com. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on October 15, 2012 (77 FR 

62466), and proposed to revise AD 

2012–18–10, Amendment 39–17187 (77 

FR 55686, September 11, 2012). 

Since we issued AD 2012–18–10, 

Amendment 39–17187 (77 FR 55686, 

September 11, 2012), the Civil Aviation 

Safety Authority (CASA), which is the 

aviation authority for the 

Commonwealth of Australia, has issued 

AD AD/GA200/1, Amendment 1, dated 

September 21, 2012 (referred to after 

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

condition for the specified products. 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states that: 

As a result of a reported case of failure of 

a strut on a GA200C aircraft, GippsAero has 

issued a mandatory service bulletin to alert 

operators and maintenance organisations and 

to provide inspection and rectification 

actions. 

This Airworthiness Directive makes this 

inspection and rectification action 

mandatory. Failure to complete the actions 

required by this service bulletin may result 

in wing strut bolt failure, resulting in wing 

structural failure. 

Amendment 1 is issued to revise the repeat 

inspection compliance time to 500 hours 

(previously 100 hours). The requirement 

service bulletin is also revised to provide a 

corrective action if the inboard (upper) strut 

fitting hole is found to be larger than 

specified. The initial inspection compliance 

time of 10 hours remains unchanged. 

This AD retains the actions required 

in AD 2012–18–10, Amendment 39– 

17187 (77 FR 55686, September 11, 

2012), changes the compliance time for 

the repetitive inspections from intervals 

of 100 hours time-in-service (TIS) to 

intervals of 500 hours TIS, and 

incorporates the revised service bulletin 

that includes repair instructions in lieu 


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