10406 Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / Proposed Rules 

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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

Aircraft Certification Office (ACO) to make 

those findings. For a repair method to be 

approved, the repair must meet the 

certification basis of the airplane and 14 CFR 

25.571, Amendment 45, and the approval 

must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6590; email: berhane.alazar@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; email me.boecom@boeing.com; 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 February 

9, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–4161 Filed 2–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0147; Directorate 

Identifier 2011–NM–067–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 767–200 and –300 

series airplanes. The existing AD 

requires replacement of the existing 

deactivation pin, aft cascade pin 

bushing, and pin insert on each thrust 

reverser half with new, improved 

components. Since we issued that AD, 

we received reports that certain 

airplanes require installation of a new 

bushing and deactivation pin with 

increased load carrying capability and 

all airplanes powered by Pratt & 

Whitney JT9D series engines require 

installation of a new bracket for stowing 

the deactivation pin. This proposed AD 

would add a dye penetrant inspection 

for cracking of the rivet holes of the 

bushing plate and repair or replacement, 

if necessary. For certain airplanes, this 

proposed AD would require replacing 

the existing bushing with a new bushing 

and deactivation pin; and installing a 

new or serviceable stowage bracket for 

the deactivation pins on all airplanes 

powered by Pratt & Whitney JT9D series 

engines. We are proposing this AD to 

prevent failure of the thrust reverser 

deactivation pins, which could fail to 

prevent a deployment of a deactivated 

thrust reverser in flight and consequent 

reduced controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 9, 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 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; email 

me.boecom@boeing.com; 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: 

Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6509; fax: 425–917–6590; email: 

rebel.nichols@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–2012–0147; Directorate Identifier 

2011–NM–067–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 

On September 19, 2002, we issued AD 

2002–19–11, Amendment 39–12891 (67 

FR 61478, October 1, 2002), for certain 

Model 767–200 and –300 series 

airplanes powered by Pratt & Whitney 

JT9D series engines. The existing AD 

requires replacement of the existing 

deactivation pin, aft cascade pin 

bushing, and pin insert on each thrust 

reverser half, with new, improved 

components. The existing AD resulted 

from reports that the pin insert for the 

deactivation pin was not able to 

withstand the load of a powered 

deployment and could fail on some 

airplanes. We issued that AD to prevent 

failure of the thrust reverser 

deactivation pins, which could fail to 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / Proposed Rules 10407 

prevent a deployment of a deactivated 

thrust reverser in flight and consequent 

reduced controllability of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2002–19–11, 

Amendment 39–12891 (67 FR 61478, 

October 1, 2002), we received reports 

indicating that certain airplanes require 

installation of a new bushing and pin 

with increased load carrying capability, 

and all airplanes powered by Pratt & 

Whitney JT9D series engines require 

installation of a new bracket for stowing 

the deactivation pin. Specifically, we 

have been advised that the part number 

(P/N) 315T3222–3 bushing could not be 

replaced by the P/N 315T3222–10 

bushing due to inadequate edge margin 

on the early thrust reverser 

configuration. 

Relevant Service Information 

AD 2002–19–11, Amendment 39– 

12891 (67 FR 61478, October 1, 2002), 

refers to Boeing Alert Service Bulletin 

767–78A0089, Revision 1, dated May 

30, 2002, as the appropriate source of 

service information for the required 

actions. Boeing has since revised this 

service information. We reviewed 

Boeing Alert Service Bulletin 767– 

78A0089, Revision 5, dated June 9, 

2009, which identifies additional work 

that needs to be performed on 

specifically configured Group 2 

airplanes for doing a dye penetrant 

inspection for cracking of the rivet holes 

of the bushing plate; repair or 

replacement of the bushing plate with a 

new or serviceable bushing plate if 

necessary; and replacing any existing 

P/N 315T3222–3 or P/N 315T3222–10 

bushing and deactivation pin with a 

new P/N 315T3221–1 bushing and new 

P/N 315T1604–6 deactivation pin to 

provide adequate edge margin. Boeing 

Alert Service Bulletin 767–78A0089, 

Revision 5, dated June 9, 2009, also 

identifies additional work for installing 

a new or serviceable stowage bracket for 

the deactivation pins on all airplanes 

powered by Pratt & Whitney JT9D series 

engines. 

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 retain all 

requirements of AD 2002–19–11, 

Amendment 39–12891 (67 FR 61478, 

October 1, 2002). This proposed AD 

would also require accomplishing the 

actions specified in the service 

information described previously. 

Change to Existing AD 

Since AD 2002–19–11, Amendment 

39–12891 (67 FR 61478, October 1, 

2002), was issued, the AD format has 

been revised, and certain paragraphs 

have been rearranged. As a result, 

paragraphs (a) and (b) of AD 2002–19– 

11 Amendment 39–12891 (67 FR 61478, 

October 1, 2002), have been reidentified as paragraphs (g) and (h) in 

this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 23 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 

Number of U.S. 

registered 

airplanes 

Cost on U.S. 

operators 

Replace deactivation pin, pin bushing, and 

pin insert (retained actions from existing AD 

2002–19–11, Amendment 39-12891 (67 FR 

61478, October 1, 2002).

12 work-hours × $85 

per hour = $1,020 

per inspection cycle.

$12,108 $13,128 23 $301,944 

Group 1: Install stowage bracket for deactivation pin (new proposed action).17 work-hours × $85 

per hour = $1,445.

14,644 16,089 16 257,424 

Group 2: Replace bushing and deactivation 

pin and install stowage bracket for thrust 

reverser deactivation pin (new proposed 

action).

17 work-hours × $85 

per hour = $1,445.

19,972 21,417 7 149,919 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

(repair or replacement of bushing plate) 

specified in this proposed AD. 

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 have 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 that the 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. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
10408 Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / 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 

removing airworthiness directive (AD) 

2002–19–11, Amendment 39–12891 (67 

FR 61478, October 1, 2002), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2012–0147; Directorate Identifier 2011– 

NM–067–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by April 9, 2012. 

(b) Affected ADs 

This AD supersedes AD 2002–19–11, 

Amendment 39–12891 (67 FR 61478, October 

1, 2002). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200 and –300 series airplanes, 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 767–78A0089, 

Revision 5, dated June 9, 2009. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 7830, Thrust Reverser. 

(e) Unsafe Condition 

This AD was prompted by reports that 

certain airplanes require installation of a new 

bushing and deactivation pin with increased 

load carrying capability and all airplanes 

powered by Pratt & Whitney JT9D series 

engines require installation of a new bracket 

for stowing the deactivation pin. We are 

issuing this AD to prevent failure of the 

thrust reverser deactivation pins, which 

could fail to prevent a deployment of a 

deactivated thrust reverser in flight and 

consequent reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

Restatement of Requirements of AD 2002– 

19–11, Amendment 39–12891 (67 FR 61478, 

October 1, 2002), With Revised Service 

Information 

(g) Replacement of Deactivation Pin, Pin 

Bushing, and Pin Insert 

Within 24 months after November 5, 2002 

(the effective date of AD 2002–19–11, 

Amendment 39–12891 (67 FR 61478, October 

1, 2002)), replace the existing deactivation 

pin, pin bushing in the aft cascade mounting 

ring, and pin insert on each thrust reverser 

half, with new, improved components, in 

accordance with Boeing Alert Service 

Bulletin 767–78A0089, Revision 1, dated 

May 30, 2002; or Boeing Alert Service 

Bulletin 767–78A0089, Revision 5, dated 

June 9, 2009. After the effective date of this 

AD, only Boeing Alert Service Bulletin 767– 

78A0089, Revision 5, dated June 9, 2009, 

may be used. 

Note to paragraph (g): The new, improved 

insert flange and pin bushing does not 

physically preclude use of a deactivation pin 

having P/N 315T1604–2 or –5. However, use 

of deactivation pins having P/N 315T1604– 

2 or –5 may not prevent the thrust reversers 

from deploying in the event of a full powered 

deployment. Therefore, thrust reversers 

modified per AD 2002–19–11, Amendment 

39–12891 (67 FR 61478, October 1, 2002), are 

required to be installed with the new, longer 

deactivation pins having P/N 315T1604–6, as 

specified in Boeing Alert Service Bulletin 

767–78A0089, Revision 1, dated May 30, 

2002, or Boeing Alert Service Bulletin 767– 

78A0089, Revision 5, dated June 9, 2009. 

After the effective date of this AD, only 

Boeing Alert Service Bulletin 767–78A0089, 

Revision 5, dated June 9, 2009, may be used. 

New Requirements of This AD 

(h) Inspection, Bushing and Pin 

Replacement, and Installation of Stowage 

Bracket 

Within 24 months after the effective date 

of this AD, do the applicable actions 

specified in paragraphs (h)(1) and (h)(2) of 

this AD. 

(1) For Group 2 airplanes as identified in 

Boeing Alert Service Bulletin 767–78A0089, 

Revision 5, dated June 9, 2009, do a dye 

penetrant inspection for cracking of the rivet 

holes and replace any P/N 315T3222–3 or 

P/N 315T3222–10 bushing and deactivation 

pin with a new or serviceable P/N 315T3221– 

1 bushing and new P/N 315T1604–6 

deactivation pin, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 767–78A0089, Revision 5, 

dated June 9, 2009. If any crack is found in 

the rivet holes of the bushing plate, before 

further flight, repair or replace the bushing 

plate with a new or serviceable bushing 

plate, as applicable, using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

(2) For both Group 1 and Group 2 

airplanes, as identified in Boeing Alert 

Service Bulletin 767–78A0089, Revision 5, 

dated June 9, 2009, install a new or 

serviceable stowage bracket assembly (P/N 

015T0196–4 for the right thrust reverser, 

P/N 015T0196–5 for the left thrust reverser), 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–78A0089, Revision 5, dated June 9, 

2009. 

(i) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Actions accomplished before the effective 

date of this AD in accordance with Boeing 

Alert Service Bulletin 767–78A0089, 

Revision 2, dated March 13, 2003; Boeing 

Alert Service Bulletin 767–78A0089, 

Revision 3, dated December 18, 2003; or 

Boeing Alert Service Bulletin 767–78A0089, 

Revision 4, dated March 6, 2008; are 

considered acceptable for compliance with 

the corresponding requirements of paragraph 

(g) of 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. 

(3) AMOCs approved for AD 2002–19–11, 

Amendment 39–12891 (67 FR 61478, October 

1, 2002), are approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6509; fax: 425–917– 

6590; email: rebel.nichols@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; email me.boecom@boeing.com; 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 February 

10, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–4162 Filed 2–21–12; 8:45 am] 

BILLING CODE 4910–13–P 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS