50576 Federal Register / Vol. 77, No. 163 / Wednesday, August 22, 2012 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Parts 27 and 29 

[Docket No. FAA–2009–0660; Amdt. Nos. 

27–47, 29–54] 

RIN 2120–AJ52 

Damage Tolerance and Fatigue 

Evaluation of Composite Rotorcraft 

Structures; OMB Approval of 

Information Collection 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; OMB approval of 

information collection. 

SUMMARY: This document notifies the 

public of the Office of Management and 

Budget’s (OMB’s) approval of the 

information collection requirement 

contained in the FAA’s final rule, 

‘‘Damage Tolerance and Fatigue 

Evaluation of Composite Rotorcraft 

Structures,’’ which was published on 

December 1, 2011. 

DATES: The rule published on December 

1, 2011, and became effective on 

January 30, 2012. However, at the time 

of publication, the new information 

collection requirements imposed by 14 

CFR 27.573 and 29.573 lacked OMB 

approval. This document announces 

receipt of OMB’s June 28, 2012 

approval. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Sharon Y. Miles, 

Regulations and Policy Group, 

Rotorcraft Directorate, ASW–111, 

Federal Aviation Administration, 2601 

Meacham Boulevard, Fort Worth, Texas 

76137–0111; telephone (817) 222–5122; 

facsimile (817) 222–5961; email 

sharon.y.miles@faa.gov. For legal 

questions concerning this action, 

contact Theresa D. Dunn, Directorate 

Counsel, ASW–7G8, Federal Aviation 

Administration, 2601 Meacham 

Boulevard, Fort Worth, Texas 76137– 

0007, telephone (817) 222–5099; 

facsimile (817) 222–5945, email: 

theresa.dunn@faa.gov. 

SUPPLEMENTARY INFORMATION: The final 

rule, ‘‘Damage Tolerance and Fatigue 

Evaluation of Composite Rotorcraft 

Structures,’’ published in the Federal 

Register (76 FR 74655) on December 1, 

2011. In that rule, the FAA amended its 

regulations to require evaluation of 

fatigue and residual static strength of 

composite rotorcraft structures using a 

damage tolerance evaluation, or a 

fatigue evaluation if the applicant 

establishes that a damage tolerance 

evaluation is impractical. 

In a correction document (77 FR 

4890), published February 1, 2012, the 

FAA revised the DATES section of the 

final rule, noting that affected parties 

were not required to comply with the 

new information collection 

requirements in §§ 27.573 and 29.573 

until OMB approved the FAA’s request 

to collect the information. Sections 

27.573 and 29.573 include new 

provisions requiring an applicant to 

submit damage tolerance and fatigue 

evaluation information for principal 

composite structural elements or 

components, detail design points, and 

fabrication techniques. OMB approval 

for the information collection 

requirement was pending at the time of 

§§ 27.573 and 29.573 publication. 

Under the Paperwork Reduction Act, 

the FAA submitted the new information 

collection requirements for OMB 

review. OMB approved the collection on 

June 28, 2012, and assigned the 

information collection OMB Control 

Number 2120–0753, which expires on 

December 31, 2012. 

This publication informs affected 

parties of the approval and announces 

that as of June 28, 2012, affected parties 

are required to comply with the new 

information collection requirements in 

§§ 27.573 and 29.573. 

Issued in Washington, DC, on August 13, 

2012. 

Lirio Liu, 

Acting Director, Office of Rulemaking. 

[FR Doc. 2012–20685 Filed 8–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 29 

[Docket No. FAA–2009–0413; Amdt. No. 29– 

55] 

RIN 2120–AJ51 

Fatigue Tolerance Evaluation of 

Metallic Structures; OMB Approval of 

Information Collection 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; OMB approval of 

information collection. 

SUMMARY: This document notifies the 

public of the Office of Management and 

Budget’s (OMB’s) approval of the 

information collection requirement 

contained in the FAA’s final rule, 

‘‘Fatigue Tolerance Evaluation of 

Metallic Structures,’’ which was 

published on December 2, 2011. 

DATES: The rule published on December 

2, 2011, and became effective on 

January 31, 2012. However, at the time 

of publication, the new information 

collection requirements imposed by 14 

CFR 29.571, lacked OMB approval. This 

document announces receipt of OMB’s 

June 28, 2012 approval. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Sharon Y. Miles, 

Regulations and Policy Group, 

Rotorcraft Directorate, ASW–111, 

Federal Aviation Administration, 2601 

Meacham Blvd., Fort Worth, Texas 

76137–0111; telephone number (817) 

222–5122; facsimile (817) 222–5961; 

email sharon.y.miles@faa.gov. For legal 

questions concerning this action, 

contact Theresa D. Dunn, Directorate 

Counsel, ASW–7G8, Federal Aviation 

Administration, 2601 Meacham Blvd., 

Fort Worth, Texas 76137–0007; 

telephone (817) 222–5099; facsimile 

(817) 222–5945; email: 

theresa.dunn@faa.gov. 

SUPPLEMENTARY INFORMATION: The final 

rule, ‘‘Fatigue Tolerance Evaluation of 

Metallic Structures,’’ published in the 

Federal Register (76 FR 75435) on 

December 2, 2011. In that rule, the FAA 

addresses advances in structural fatigue 

substantiation technology for metallic 

structures that provides an increased 

level of safety by avoiding or reducing 

the likelihood of the catastrophic fatigue 

failure of a metallic structure. These 

increased safety requirements help 

ensure that should serious accidental 

damage occur during manufacturing or 

within the operational life of the 

rotorcraft, the remaining structure could 

withstand, without failure, any fatigue 

loads that are likely to occur, until the 

damage is detected or the part is 

replaced. 

In a correction document (77 FR 

4890), published February 1, 2012, the 

FAA revised the DATES section of the 

final rule, noting that affected parties 

were not required to comply with the 

new information collection 

requirements in § 29.571 until OMB 

approved the FAA’s request to collect 

the information. Section 29.571 

includes new provisions requiring an 

applicant, when trying to obtain type 

certification of a rotorcraft, to submit 

substantiating data to show that the 

rotorcraft complies with specific 

certification requirements. OMB’s 

approval for the information collection 

requirement was pending at the time of 

§ 29.571 publication. 

Under the Paperwork Reduction Act, 

the FAA submitted the new information 

collection requirements for OMB 

review. OMB approved the collection on 


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Federal Register / Vol. 77, No. 163 / Wednesday, August 22, 2012 / Rules and Regulations 50577 

June 28, 2012, and assigned the 

information collection OMB Control 

Number 2120–0752, which expires on 

June 30, 2015. 

This publication informs affected 

parties of the approval and announces 

that as of June 28, 2012, affected parties 

are required to comply with the new 

information collection requirements in 

§ 29.571. 

Issued in Washington, DC, on August 13, 

2012. 

Lirio Liu, 

Acting Director, Office of Rulemaking. 

[FR Doc. 2012–20684 Filed 8–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1093; Directorate 

Identifier 2010–NM–149–AD; Amendment 

39–17163; AD 2012–16–16] 

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 all The 

Boeing Company Model 757 airplanes. 

This AD was prompted by a report of 

extensive corrosion of the ballscrew of 

the drive mechanism of the horizontal 

stabilizer trim actuator. This AD 

requires repetitive detailed inspections 

for discrepancies of the horizontal 

stabilizer ballscrew assembly; repetitive 

lubrication of the horizontal stabilizer 

trim control system; repetitive 

measurements for discrepancies of the 

ballscrew to ballnut freeplay; and 

corrective actions, if necessary. We are 

issuing this AD to prevent undetected 

failure of the primary and secondary 

load paths for the ballscrew in the 

horizontal stabilizer, which could lead 

to loss of control of the horizontal 

stabilizer and consequent loss of control 

of the airplane. 

DATES: This AD is effective September 

26, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 26, 2012. 

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; 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: 

Kenneth Frey, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6468; fax: (425) 917–6590; email: 

kenneth.frey@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 published in the Federal 

Register on October 25, 2011 (76 FR 

65991). That NPRM proposed to require 

repetitive detailed inspections for 

discrepancies of the horizontal stabilizer 

ballscrew assembly; repetitive 

lubrication of the horizontal stabilizer 

trim control system; repetitive 

measurements for discrepancies of the 

ballscrew to ballnut freeplay; and 

corrective actions, if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 65991, 

October 25, 2011) and the FAA’s 

response to each comment. 

Requests To Withdraw the NPRM (76 

FR 65991, October 25, 2011) 

Airlines for America (A4A), on behalf 

of its member American Airlines (AAL), 

asked that the NPRM (76 FR 65991, 

October 25, 2011) be withdrawn. A4A 

stated that in view of previously 

implemented maintenance procedures 

designed to prevent malfunctions of the 

horizontal stabilizer trim actuator 

(HSTA), and maintenance data gathered 

in accomplishing those and other 

related procedures, the NPRM is not 

necessary. A4A added that those 

procedures include instructions 

mandated by AD 2005–12–18, 

Amendment 39–14134 (70 FR 35166, 

June 17, 2005), which requires 

inspection and overhaul of the primary 

brake of the HSTA, ‘‘upgrades to HSTA 

maintenance in the Boeing maintenance 

planning document (MPD), and 

corresponding upgrades to air carrier 

maintenance programs.’’ AAL stated 

that the ‘‘Discussion’’ section of the 

NPRM specifies ‘‘Jackscrews and 

ballscrews are similar in function and 

have similar airplane level failure 

modes.’’ AAL noted that this statement 

is not accurate in defining the risk 

posed by the ballscrew design. AAL 

added that the ballscrew uses ball 

bearings for the primary load path, and 

a male thread nut for the secondary load 

path is more tolerant of inadequate 

lubrication conditions than the 

jackscrew/acme nut design used on 

Model MD–80 airplanes. AAL also 

stated that the NPRM specifies that the 

unsafe condition is likely to exist or 

develop on other products of the same 

type design, which misrepresents the 

level of risk to the Model 757 

worldwide fleet. 

We disagree with the requests to 

withdraw the NPRM (76 FR 65991, 

October 25, 2011). Although the 

maintenance procedures in AD 2005– 

12–18, Amendment 39–14134 (70 FR 

35166, June 17, 2005), will prevent 

grease contamination on the primary 

HSTA brake, the repetitive intervals for 

the subject actions are not frequent 

enough to prevent corrosion in the 

ballscrew of the drive mechanism of the 

HSTA, which could result in undetected 

failure of both the primary and 

secondary load paths. In light of this, we 

have determined that the unsafe 

condition is likely to exist or develop on 

the affected airplanes. As a result of that 

determination, we are issuing this AD in 

order to eliminate the unsafe condition 

by requiring that the actions be done at 

the required intervals. 

Request To Issue Emergency 

Airworthiness Directive 

Captain Rick Petersen, a private 

citizen, asked that a ‘‘more deliberate 

emergency type directive’’ be issued 

instead of an NPRM (76 FR 65991, 

October 25, 2011). The commenter 

stated that extensive corrosion found on 


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