55770 Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Proposed Rules 

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): 

The Boeing Company: Docket No. FAA– 

2012–0932; Directorate Identifier 2012– 

NM–014–AD. 

(a) Comments Due Date 

We must receive comments by October 26, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

777F series airplanes; certificated in any 

category; as identified in Boeing Special 

Attention Service Bulletin 777–35–0024, 

dated September 1, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 35, Oxygen. 

(e) Unsafe Condition 

This AD was prompted by a report that 

during a test of the oxygen system, an 

operator found that the passenger oxygen 

masks did not properly flow oxygen and that 

a loud noise occurred in the overhead area, 

which was caused by the flex line separating 

from the hard line due to a missing clamshell 

coupler. We are issuing this AD to prevent 

the oxygen system flex line from separating 

from the hard line, which could cause an 

oxygen leak and a drop in the oxygen system 

pressure, resulting in improper flow of 

oxygen through the passenger masks and 

injury to passengers if emergency oxygen is 

needed. 

(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, do the applicable actions in 

paragraph (g)(1) or (g)(2) of this AD. 

(1) For Groups 1–6, 8 and 9 airplanes, as 

identified in Boeing Special Attention 

Service Bulletin 777–35–0024, dated 

September 1, 2011: Do a detailed inspection 

of certain areas of the airplane oxygen system 

to ensure clamshell couplers are installed 

and fully latched, and perform and meet the 

requirements of the low pressure leak test, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–35–0024, dated 

September 1, 2011. 

(2) For Group 7 airplanes, as identified in 

Boeing Special Attention Service Bulletin 

777–35–0024, dated September 1, 2011: 

Perform and meet the low pressure leak test, 

in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–35–0024, dated 

September 1, 2011. 

(h) Corrective Action if Clamshell Coupler Is 

Not Fully Latched 

If, during any inspection required by 

paragraph (g) of this AD, any clamshell 

coupler is not fully latched: Before further 

flight, latch the clamshell coupler, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–35–0024, dated 

September 1, 2011. 

(i) Corrective Action if Clamshell Coupler Is 

Not Installed 

If, during any inspection required by 

paragraph (g) of this AD, any clamshell 

coupler is not installed: Before further flight, 

install a clamshell coupler. 

Note 1 to paragraph (i) of this AD: 

Guidance on installation of the clamshell 

coupler may be found in Subject 35–00–00, 

Oxygen, of Chapter 35, Oxygen, of Part II, 

Practices and Procedures, of the Boeing 777 

Aircraft Maintenance Manual, Revision 65, 

May 5, 2012. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 Susan Monroe, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6457; fax: 425–917–6590; email: 

susan.l.monroe@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

5680; Internet https:// 

www.myboeingfleet.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. 

Issued in Renton, Washington, on 

September 4, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–22341 Filed 9–10–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0962; Directorate 

Identifier 2012–CE–033–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company Models 

172RG, R182, TR182, FR182, 210N, 

T210N, 210R, T210R, P210N, P210R, 

and T303 airplanes. This proposed AD 

was prompted by a report of a cockpit 

fire that appeared to originate from the 

area of the landing gear’s hydraulic 

power pack system. This proposed AD 

would require you inspect the aircraft’s 

hydraulic power pack wiring for 

incorrect installation, and if needed, 

correct the installation. We are 

proposing this AD to correct the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 26, 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: 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 Cessna 

Aircraft Company, Customer Service, 

P.O. Box 7706, Wichita, KS 67277; 

telephone: (316) 517–5800; fax: (316) 

517–7271; Internet: http:// 

www.cessna.com/customer-service/ 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Proposed Rules 55771 

technical-publications.html. 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:// 

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: 

Richard Rejniak, Aerospace Engineer, 

Wichita Aircraft Certification Office, 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; phone: (316) 946–4128; 

fax: (316) 946–4107; email: 

richard.rejniak@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0962; Directorate Identifier 2012– 

CE–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 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 received a report of an accident of 

a Cessna Aircraft Company Model 

172RG airplane where a fire started inflight on the cabin side of the firewall 

and rapidly accelerated. The fire 

originated from the area of the landing 

gear’s hydraulic power pack system and 

resulted in a complete hull loss with 

reported injuries. 

The investigation concluded that an 

in-flight fire may result from improper 

installation of the terminal lugs, 

improper installation of (or missing) 

terminal covers and associated wiring to 

the landing gear hydraulic power pack 

motor wiring, which was not properly 

protected or adequately secured. The 

cause for the rapid acceleration of the 

fire was indicative of the presence of 

flammable materials or a flammable 

material source near or in contact with 

the hydraulic power pack system within 

the aircraft’s cockpit/cabin. 

This style of hydraulic power pack is 

also used on Cessna Aircraft Company 

Models R182, TR182, FR182, 210N, 

T210N, 210R, T210R, P210N, P210R, 

and T303 airplanes. 

This condition, if not corrected, could 

result in a fire in the aircraft’s cockpit, 

damage and or loss of aircraft, and 

injuries and or fatalities. 

Relevant Service Information 

We reviewed Cessna Aircraft 

Company Service Letter MEL–29–01, 

dated July 14, 2012; and Service Letter 

SEL–29–01, dated July 16, 2012. The 

service information describes 

procedures for inspection of the 

aircraft’s hydraulic power pack system 

for proper wire routing, protective 

cover, and hydraulic leaks, and if 

needed, installation of a protective 

cover and rerouting of wiring. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

affects 2,961 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 

Hydraulic power pack system wiring inspection.1 work-hour × $85 per hour = $85 ........... Not applicable ........... $85 $251,685 

We estimate the following costs to do 

any necessary hydraulic power pack 

terminal lug protective cap installation 

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 this 

installation: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Hydraulic power pack system wiring installation .......... 1 work-hour × $85 per hour = $85 ............................... $29 $114 

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 


srobinson on DSK4SPTVN1PROD with PROPOSALS
55772 Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Proposed Rules 

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), 

(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 adding 

the following new airworthiness 

directive (AD): 

Cessna Aircraft Company: Docket No. FAA– 

2012–0962+; Directorate Identifier 2012– 

CE–033–AD. 

(a) Comments Due Date 

We must receive comments by October 26, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Cessna 

Aircraft Company airplanes, certificated in 

any category, as identified in table 1, 

paragraph (c), of this AD: 

TABLE 1 TO PARAGRAPH (c) OF THIS AD—APPLICABILITY

Model Serial Nos. 

(1) 172RG ......................................................................................................................................................... 172RG000l through 172RG1191. 

(2) R182 and TR182 ......................................................................................................................................... R18200584 through Rl8202039. 

(3) FR182 .......................................................................................................................................................... FR18200021 through FR18200070. 

(4) 210N, T210N, 210R, and T210R ................................................................................................................ 21062955 through 21065009. 

(5) P210N .......................................................................................................................................................... P21000151 through P21000834. 

(6) P210R .......................................................................................................................................................... P21000835 through P21000874. 

(7) T303 ............................................................................................................................................................. T30300001 through T30300315. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 32, Landing Gear. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

cockpit fire that appeared to originate from 

the area of the landing gear’s hydraulic 

power pack system. We are issuing this AD 

to correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect the Hydraulic Power Pack Wiring 

for Correct Installation 

(1) Single engine aircraft: Within the next 

100 hours time-in-service (TIS) after the 

effective date of this AD or within the next 

12 calendar months after the effective date of 

this AD, whichever occurs first, inspect the 

hydraulic power pack wiring for correct 

installation. Follow Cessna Aircraft Company 

Service Letter SEL–29–01, dated July 16, 

2012. 

(2) Multi-engine aircraft: Within the next 

100 hours TIS after the effective date of this 

AD or within the next 12 calendar months 

after the effective date of this AD, whichever 

occurs first, inspect the hydraulic power 

pack wiring for correct installation. Follow 

Cessna Aircraft Company Service Letter 

MEL–29–01, dated July 14, 2012. 

(h) Correct the Installation of the Hydraulic 

Power Pack Wiring 

(1) Single engine aircraft: If you find 

evidence of incorrect installation of the 

hydraulic power pack wiring as a result of 

the inspection required by paragraph (g)(1) of 

this AD, before further flight, correct the 

installation. Follow Cessna Aircraft Company 

Service Letter SEL–29–01, dated July 16, 

2012. 

(2) Multi-engine aircraft: If you find 

evidence of incorrect installation of the 

hydraulic power pack wiring as a result of 

the inspection required by paragraph (g)(2) of 

this AD, before further flight, correct the 

installation. Follow Cessna Aircraft Company 

Service Letter MEL–29–01, dated July 14, 

2012. 

(i) Special Flight Permit 

Special flight permits are permitted with 

the following limitation: visual flight rules 

(VFR) day conditions. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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. 

(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 Richard Rejniak, Aerospace Engineer, 

Wichita ACO, 1801 Airport Road, Room 100, 

Wichita, Kansas 67209; phone: (316) 946– 

4128; fax: (316) 946–4107; email: 

richard.rejniak@faa.gov. 

(2) For service information identified in 

this AD, contact Cessna Aircraft Company, 

Customer service, P.O. Box 7706, Wichita, KS 

67277; telephone: (316) 517–5800; fax: (316) 

517–7271; Internet: http:// 

www.cessnasupport.com/customer-service/ 

technical-publications.html. 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. 


srobinson on DSK4SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Proposed Rules 55773 

Issued in Kansas City, Missouri, on 

September 5, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–22332 Filed 9–10–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0909; Directorate 

Identifier 2011–NM–027–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 all The Boeing Company Model DC– 

9–81 (MD–81), DC–9–82 (MD–82), DC– 

9–83 (MD–83), DC–9–87 (MD–87), and 

MD–88 airplanes. That NPRM proposed 

repetitive high frequency eddy current 

(HFEC) inspections for cracking of the 

left and right rib hinge bearing lugs of 

the aft face of the center section of the 

horizontal stabilizer; measuring crack 

length and blending out cracks; and 

replacing the horizontal stabilizer center 

section rib, if necessary. That NPRM 

was prompted by reports of cracks of the 

hinge bearing lugs of the center section 

ribs of the horizontal stabilizer. This 

action revises that NPRM by adding the 

requirement for rib replacement if 

cracking is found during certain 

inspections of this proposed AD. We are 

proposing this supplemental NPRM to 

detect and correct cracking in the hinge 

bearing lugs of the horizontal stabilizer 

center section ribs, which could result 

in failure of the lugs, resulting in the 

inability of the horizontal stabilizer to 

sustain the required limit loads and 

consequent loss of control of the 

airplane. 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 October 26, 

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 proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; Internet https:// 

www.myboeingfleet.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 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: 

Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; phone: (562) 627–5233; 

fax: (562) 627–5210; email: 

roger.durbin@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–2011–0909; Directorate Identifier 

2011–NM–027–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 The Boeing Company Model 

DC–9–81 (MD–81), DC–9–82 (MD–82), 

DC–9–83 (MD–83), DC–9–87 (MD–87), 

and MD–88 airplanes. That NPRM 

published in the Federal Register on 

August 26, 2011 (76 FR 53346). That 

NPRM proposed to require repetitive 

HFEC inspections for cracking of the left 

and right rib hinge bearing lugs of the 

aft face of the center section of the 

horizontal stabilizer; measuring crack 

length and blending out cracks; and 

replacing the horizontal stabilizer center 

section rib, if necessary. 

Actions Since NPRM (76 FR 53346, 

August 26, 2011) Was Issued 

Since we issued the previous NPRM 

(76 FR 53346, August 26, 2011), we 

determined a required corrective action 

was not specified by Boeing Alert 

Service Bulletin MD80–55A069, dated 

January 19, 2011. Therefore, we propose 

to add a requirement for rib replacement 

if cracking is found during certain 

inspections required by this 

supplemental NPRM. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM (76 FR 

53346, August 26, 2011). The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Support for the NPRM (76 FR 53346, 

August 26, 2011) 

Boeing stated it supports the NPRM 

(76 FR 53346, August 26, 2011). 

Recognition That Reporting of Findings 

Is Not Required 

American Airlines stated it recognizes 

that reporting of findings requested by 

Boeing Alert Service Bulletin MD80– 

55A069, dated January 19, 2011, is not 

required by the NPRM (76 FR 53346, 

August 26, 2011). 

We acknowledge American Airlines’s 

comment. Reporting is not required by 

the supplemental NPRM. We have not 


srobinson on DSK4SPTVN1PROD with PROPOSALS