Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations 41895 

Issued in Renton, Washington, on June 28, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–16637 Filed 7–16–12; 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; Amendment 

39–17116; AD 2012–14–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

767–200 and –300 series airplanes. That 

AD currently requires replacement of 

the existing deactivation pin, aft cascade 

pin bushing, and pin insert on each 

thrust reverser half with new, improved 

components. This new AD requires a 

dye penetrant inspection for cracking of 

the rivet holes of the bushing plate and 

repair or replacement, if necessary; and 

for certain airplanes, 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. 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. 

DATES: This AD is effective August 21, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 5, 2002 (67 FR 

61478, October 1, 2002). 

ADDRESSES: 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 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: 

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: 

Discussion 

We issued a Notice of Proposed 

Rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2002–19–11, 

Amendment 39–12891 (67 FR 61478, 

October 1, 2002). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

February 22, 2012 (77 FR 10406). That 

NPRM proposed to continue to require 

replacement of the existing deactivation 

pin, aft cascade pin bushing, and pin 

insert on each thrust reverser half with 

new, improved components. That 

NPRM also proposed to require a dye 

penetrant inspection for cracking of the 

rivet holes of the bushing plate and 

repair or replacement, if necessary; and 

for certain airplanes, 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 10406, 

February 22, 2012) and the FAA’s 

response to each comment. 

Support for Proposed Rule (77 FR 

10406, February 22, 2012) 

Boeing concurs with the content of 

the proposed rule (77 FR 10406, 

February 22, 2012). 

Request To Provide Credit for Previous 

Actions 

Atlas Air requested that we revise the 

NPRM (77 FR 10406, February 22, 2012) 

to provide credit for actions required by 

paragraph (h)(2) of the NPRM, if those 

actions were accomplished before the 

effective date of the AD using Boeing 

Service Bulletin 767–78A0089, Revision 

3, dated December 18, 2003. 

We agree. Paragraph (i) of the NPRM 

(77 FR 10406, February 22, 2012) 

provided credit for actions required by 

paragraph (g) of the NPRM if those 

actions were performed before the 

effective date of the NPRM using Boeing 

Service Bulletin 767–78A0089, Revision 

2, dated March 13, 2003; Boeing Service 

Bulletin 767–78A0089, Revision 3, 

dated December 18, 2003; or Boeing 

Service Bulletin 767–78A0089, Revision 

4, dated March 6, 2008. We have revised 

paragraph (i) of this final rule to also 

provide credit for actions required by 

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

actions were performed before the 

effective date of this AD. 

Explanation of Changes Made to This 

AD 

We have revised certain headings 

throughout this AD and revised Note 1 

of the NPRM (77 FR 10406, February 22, 

2012) to paragraph (g)(2) of this AD. We 

have also revised paragraph (i) of this 

AD. These changes have not affected the 

intent of those paragraphs. 

Explanation of Updated Credit 

Language 

We have revised the heading and 

wording for paragraph (i) of this AD to 

provide appropriate credit for previous 

accomplishment of certain actions. This 

change does not affect the intent of that 

paragraph. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 


sroberts on DSK5SPTVN1PROD with RULES
41896 Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations 

with the change described previously. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

10406, February 22, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 10406, 

February 22, 2012). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 23 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this 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 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 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 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 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 

removing airworthiness directive (AD) 

2002–19–11, Amendment 39–12891 (67 

FR 61478, October 1, 2002), and adding 

the following new AD: 

2012–14–02 The Boeing Company: 

Amendment 39–17116; Docket No. 

FAA–2012–0147; Directorate Identifier 

2011–NM–067–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 21, 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. 

(g) Retained Replacement of Deactivation 

Pin, Pin Bushing, and Pin Insert 

(1) This paragraph restates the 

requirements of paragraph (a) of AD 2002– 

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

October 1, 2002), with revised service 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 137 / Tuesday, July 17, 2012 / Rules and Regulations 41897 

information. 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. 

(2) 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 to install the 

new, longer deactivation pins. 

(h) New 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 Previous Actions 

This paragraph provides credit for the 

actions specified in paragraphs (g) and (h)(2) 

of this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Service Bulletin 767–78A0089, 

Revision 2, dated March 13, 2003; Boeing 

Service Bulletin 767–78A0089, Revision 3, 

dated December 18, 2003; or Boeing Service 

Bulletin 767–78A0089, Revision 4, dated 

March 6, 2008. 

(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 previously in 

accordance with 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 

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. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 767– 

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

(3) The following service information was 

approved for IBR on November 5, 2002 (67 

FR 61478, October 1, 2002). 

(i) Boeing Alert Service Bulletin 767– 

78A0089, Revision 1, dated May 30, 2002. 

(4) 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. 

(5) You may review copies of the 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. 

(6) You may also review copies of the 

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/ibr_locations.html. 

Issued in Renton, Washington, on June 29, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–16933 Filed 7–16–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0703; Directorate 

Identifier 2010–SW–019–AD; Amendment 

39–17112; AD 2012–13–10] 

RIN 2120–AA64 

Airworthiness Directives; PZL Swidnik 

S.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the PZL 

Swidnik S.A. (PZL) Model PZL W–3A 

helicopter with a certain generator air 

outlet collector (collector) installed. 

This AD requires modifying the 

generator air outlet collector 

attachments (collector attachments). 

This AD is prompted by an incident 

where cyclic control stick movement 

was restricted due to rotation of a loose 

collector, resulting in locking of the 

longitudinal control system hydraulic 

actuator fork end. These actions are 

intended to prevent rotation of the 

collector, which could lead to restricted 

cyclic control stick movement, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective 

August 1, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of August 1, 2012. 

We must receive comments on this 

AD by September 17, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 


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