12060 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 

M. Congressional Notification 

As required by 5 U.S.C. 801, DOE will 

submit to Congress a report regarding 

the issuance of today’s Final Rule prior 

to the effective date set forth at the 

outset of this Final Rule. The report will 

state that it has been determined that 

the rule is not a ‘‘major rule’’ as defined 

by 5 U.S.C. 801(2). 

VIII. Approval by the Office of the 

Secretary 

The issuance of this Final Rule for the 

Replacement Fuel Goal modification has 

been approved by the Office of the 

Secretary. 

List of Subjects in 10 CFR Part 490 

Administrative practice and 

procedure, Energy conservation, Fuel 

economy, Gasoline, Motor vehicles, 

Natural gas, Penalties, Petroleum, 

Reporting, and recordkeeping 

requirements. 

Issued in Washington, DC, on March 6, 

2007. 

Alexander A. Karsner, 

Assistant Secretary, Energy Efficiency and 

Renewable Energy. 

■ For the reasons set forth in the 

Preamble, the Department of Energy is 

amending Chapter II of title 10 of the 

Code of Federal Regulations as set forth 

below: 

PART 490—ALTERNATIVE FUEL 

TRANSPORTATION PROGRAM 

■ 1. The authority citation for part 490 

is revised to read as follows: 

Authority: 42 U.S.C. 7191 et seq.; 42 U.S.C. 

13201, 13211, 13220, 13251 et seq. 

■ 2. In § 490.1 of subpart A, paragraph 

(b) is revised to read as follows: 

§ 490.1 Purpose and Scope. 

* * * * * 

(b) The provisions of this subpart 

cover: 

(1) The definitions applicable 

throughout this part; 

(2) Procedures to obtain an 

interpretive ruling and to petition for a 

generally applicable rule to amend this 

part; and 

(3) The goal of the replacement fuel 

supply and demand program 

established under section 502(a) of the 

Act (42 U.S.C. 13252(a)). 

■ 3. Subpart A is amended by adding 

§ 490.8 to read as follows: 

§ 490.8 Replacement fuel production goal. 

The goal of the replacement fuel 

supply and demand program 

established by section 502(b)(2) of the 

Act (42 U.S.C. 13252(b)(2)) and revised 

by DOE pursuant to section 504(b) of the 

Act (42 U.S.C. 13254(b)) is to achieve a 

production capacity of replacement 

fuels sufficient to replace, on an energy 

equivalent basis, at least 30 percent of 

motor fuel consumption in the United 

States by the year 2030. 

[FR Doc. E7–4324 Filed 3–14–07; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27267; Directorate 

Identifier 2002–NE–40–AD; Amendment 39–

14991; AD 2007–06–10] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–524 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Rolls Royce plc (RR) RB211–524 series 

turbofan engines with certain part 

number (P/N) intermediate pressure 

compressor (IPC) stage 5 disks installed. 

That AD currently requires new reduced 

IPC stage 5 disk cyclic limits. This AD 

requires the same reduced IPC stage 5 

disk cyclic limits, requires removal from 

service of affected disks that already 

exceed the new reduced cyclic limit, 

and, removal from service of other 

affected disks before exceeding their 

cyclic limits using a drawdown 

schedule. This AD also exempts disks 

reworked to RR Service Bulletin (SB) 

No. RB.211–72–E182, Revision 1, dated 

July 30, 2004, and allows an on-wing 

eddy current inspection (ECI) on 

RB211–524G and RB211–524H series 

engines. This AD results from the 

manufacturer issuing a revised Alert 

Service Bulletin (ASB) to remove certain 

disks from applicability, and to allow an 

on-wing ECI on RB211–524G and 

RB211–524H series engines. We are 

issuing this AD to prevent failure of the 

IPC stage 5 disk, which could result in 

uncontained engine failure and possible 

damage to the airplane. 

DATES: This AD becomes effective April 

19, 2007. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of April 19, 2007. 

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce plc, P.O. Box 31 Derby, 

DE248BJ, United Kingdom; telephone 

011–44–1332–242424; fax 011–44–

1332–249936. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7178; fax (781) 

238–7199; e-mail: ian.dargin@faa.gov. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to RR RB211–524 series turbofan 

engines with certain P/N IPC stage 5 

disks installed. We published the 

proposed AD in the Federal Register on 

July 11, 2006 (71 FR 39025). That action 

proposed to require: 

• Establishing new reduced IPC stage 

5 disk cyclic limits. 

• Removing from service affected 

disks that already exceed the new 

reduced cyclic limit. 

• Removing from service other 

affected disks before exceeding their 

cyclic limits, using a drawdown 

schedule. 

• Allowing optional inspections at 

each shop visit or an on-wing ECI to 

extend the disk life beyond the specified 

life. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The Docket Office (telephone 

(800) 647–5227) is located on the plaza 

level of the Department of 

Transportation Nassif Building at the 

street address stated in ADDRESSES. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Request To Add a Note 

One commenter, Rolls-Royce plc, 

requests that we add a note, just above 

compliance paragraph (j)(5), that states: 

‘‘To qualify for maximum alleviation 

since last NDT inspection (see Table 5 

of this AD) it is recommended that discs 

be ECI inspected using paragraph 3.D. of 

the Accomplishment Instructions of RR 


rmajette on PROD1PC67 with RULES
Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 12061 

Alert Service Bulletin No. RB.211–72–

AD428, Revision 5, dated March 18, 

2005.’’ The commenter feels that this 

note adds clarification to the AD 

compliance. We do not agree. The note 

is identified in the service bulletin that 

is incorporated by reference, and need 

not be included in the text of the AD. 

We did not change the AD. 

Request To Add Engine Series 

Rolls-Royce plc requests that we add 

the RB211–524B/B3 engine series to 

compliance paragraph (k)(1), and add 

the RB211–524H2 and RB211–524H2–T 

engine series to compliance paragraph 

(k)(2), as they need to be included, the 

same as they appear in the service 

bulletin. We agree and added those 

engine series to the paragraphs. 

Clarification of Paragraph (g) 

Since we issued the proposed AD, we 

reviewed the wording in paragraph (g) 

and realized that the compliance times 

in that paragraph were in conflict. We 

clarified that paragraph. It now states to 

comply with the reduced cyclic life 

limits in Table 3 of this AD within 30 

days after the effective date of this AD, 

or conduct optional qualifying 

nondestructive test (NDT) inspections 

before December 1, 2008, to extend the 

IPC stage 5 disk life as specified in 

paragraph (i) of this AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Docket Number Change 

We are transferring the docket for this 

AD to the Docket Management System 

as part of our on-going docket 

management consolidation efforts. The 

new Docket No. is FAA–2007–27267. 

The old Docket No. became the 

Directorate Identifier, which is 2002–

NE–40–AD. This AD might get logged 

into the DMS docket, ahead of the 

previously collected documents from 

the old docket file, as we are in the 

process of sending those items to the 

DMS. 

Costs of Compliance 

We estimate this AD will not affect 

any engines installed on airplanes of 

U.S. registry. Based on this, we estimate 

this AD will not have any cost to U.S. 

operators. 

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); and 

(3) 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. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

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 Federal Aviation Administration 

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 Amendment 39–14202 (70 FR 

43036, July 26, 2005) and by adding a 

new airworthiness directive, 

Amendment 39–14991, to read as 

follows: 

2007–06–10 Rolls-Royce plc: Amendment 

39–14991. Docket No. FAA–2007–27267; 

Directorate Identifier 2002–NE–40–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 19, 2007. 

Affected ADs 

(b) This AD supersedes AD 2005–15–13, 

Amendment 39–14202. 

Applicability 

(c) This AD applies to the Rolls-Royce plc 

(RR) RB211–524 series turbofan engines 

listed in the following Table 1, with 

intermediate pressure compressor (IPC) stage 

5 disk part numbers (P/Ns) listed in Table 2 

of this AD, installed. 

TABLE 1.—ENGINE MODELS AFFECTED

–524B–02 –524B–B–02 –524B3–02 –524B4–02 –524B4–D–02 

–524B2–19 –524B2–B–19 –524C2–19 –524C2–B–19 –524D4–19 

–524D4–B–19 –524D4X–19 –524D4X–B–19 –524D4–39 –524D4–B–39 

–524G2–19 –524G2–T–19 –524G3–19 –524G3–T–19 –524H2–19 

–524H2–T–19 –524H–36 –524H–T–36 

These engines are installed on, but not 

limited to, Boeing 747, 767, and Lockheed L–

1011 series airplanes. 


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TABLE 2.—IPC STAGE 5 DISK P/NS AFFECTED

LK60130 LK65932 LK69021 LK81269 LK83282 

LK83283 UL12290 UL15743 UL15744 UL15745 

UL19132 UL20785 UL20832 UL23291 UL25011 

UL36821 UL36977 UL36978 UL36979 UL36980 

UL36981 UL36982 UL36983 UL37078 UL37079 

UL37080 UL37081 UL37082 UL37083 UL37084 

Unsafe Condition 

(d) This AD results from the manufacturer 

issuing a revised Alert Service Bulletin (ASB) 

to remove certain disks from applicability 

and to allow an on-wing eddy current 

inspection (ECI) on RB211–524G and RB211–

524H series engines. The actions specified in 

this AD are intended to prevent failure of the 

IPC stage 5 disk, which could result in 

uncontained engine failure and possible 

damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Exempted Disks 

(f) For engines with an IPC stage 5 disk P/ 

N listed in Table 2 of this AD, reworked to 

RR SB No. RB.211–72–E182, Revision 1, 

dated July 30, 2004, no further action is 

necessary. 

Cycle Limits 

(g) Comply with the reduced cyclic life 

limits in Table 3 of this AD within 30 days 

after the effective date of this AD, or conduct 

optional qualifying nondestructive test (NDT) 

inspections before December 1, 2008 to 

extend the IPC stage 5 disk life, as specified 

in paragraph (i) of this AD. 

TABLE 3.—CYCLIC LIFE LIMITS WITHOUT QUALIFYING NDT INSPECTION

Date of reduced life limit 

Engine models 

–524G2, G2–T, G3, G3–T, 

H2, H2–T, H–36, H–T–36 

–524D4, D4–B, D4–B–39, 

D4X, D4X–B, D4–39 –524B2, B2–B, C2, C2–B –524B–02, B–B–02, B3–02, B4–02, B4–D–02 

November 30, 2002 ........... 13,500 cycles-in-service 

(CIS).

16,150 CIS ........................ 16,000 CIS ........................ 16,200 CIS. 

April 1, 2003 ...................... 13,500 CIS ........................ 13,500 CIS ........................ 13,500 CIS ........................ 14,000 CIS. 

December 1, 2003 ............. 12,000 CIS ........................ 13,500 CIS ........................ 13,500 CIS ........................ 14,000 CIS. 

December 1, 2004 ............. 11,000 CIS ........................ 13,500 CIS ........................ 12,000 CIS ........................ 12,000 CIS. 

December 1, 2005 ............. 11,000 CIS ........................ 12,000 CIS ........................ 12,000 CIS ........................ 12,000 CIS. 

(h) On December 1, 2008, the revised cyclic 

life limits specified in Table 4 of this AD 

become effective. Incorporate the revised 

cyclic life limits specified in Table 4 of this 

AD into the RR Time Limits Manual, 05–10–

01. 

TABLE 4.—CYCLIC LIFE LIMITS ON DECEMBER 1, 2008 

Date of reduced life limit 

Engine models 

–524G2, G2–T, G3, G3–T, 

H2, H2–T, H–36, H–T–36 

–524D4, D4–B, D4–B–39, 

D4X, D4X–B, D4–39 –524B2, B2–B, C2, C2–B –524B–02, B–B–02, B3–02, B4–02, B4–D–02 

December 1, 2008 ............. 7,830 CIS .......................... 8,700 CIS .......................... 8,900 CIS .......................... 9,000 CIS. 

Optional Inspections 

(i) Before December 1, 2008, you may 

perform an optional NDT inspection on-wing 

or at each shop visit to extend the disk life. 

Guidance for these inspections is provided in 

paragraphs (j) or (k) of this AD. 

Optional Inspections at Shop Visit 

(j) Perform optional inspections at shop 

visit, as follows: 

(1) Remove corrosion protection from IPC 

stage 5 disk. Information on corrosion 

protection removal can be found in the 

Engine Maintenance Manual. 

(2) Perform a visual inspection and a 

binocular inspection of the IPC stage 5 disk 

for corrosion pitting at the cooling air holes 

and defender holes in the disk front spacer 

arm. Follow paragraph 3.C. of the 

Accomplishment Instructions of RR ASB No. 

RB.211–72–AD428, Revision 5, dated March 

18, 2005. The RR Engine Maintenance 

Manual, Inspection Check-00 (ATA 72–32–

31–200–000), contains limits for corrosion 

pitting of the IPC stage 5 disk. 

(3) If the disk has corrosion pitting in 

excess of limits, remove the disk from 

service. 

(4) If the disk is free from corrosion pitting, 

perform a magnetic penetrant inspection 

(MPI) of the entire disk as follows: 

(i) For RB211–524G2–T, RB211–524G3–T, 

and RB211–524H–T series engines, the RR 

Engine Maintenance Manual, Inspection 

Check 08 (ATA 72–32–31–200–008), contains 

limits for corrosion pitting of the IPC stage 

5 disk. 

(ii) For RB211–524G2, RB211–524G3, and 

RB211–524H series engines, the RR Engine 

Maintenance Manual, Inspection Check 09 

(ATA 72–32–31–200–009), contains limits for 

corrosion pitting of the IPC stage 5 disk. 

(iii) If the disk passes the MPI and you find 

no cracks, complete all other inspections, reapply corrosion protection to the disk, and 

return the disk to service using the cyclic 

limits allowed by paragraph (m) of this AD. 

RR Repair FRS5900 contains information on 

re-applying corrosion protection. 

(5) If the disk has corrosion pitting that is 

within limits, do the following: 

(i) Perform an ECI on all disk cooling air 

holes, defender holes, and inner and outer 

faces. Use paragraph 3.D. of the 

Accomplishment Instructions of RR ASB No. 

RB.211–72–AD428, Revision 5, dated March 

18, 2005. The RR Engine Maintenance 

Manual, Inspection Check-00 (ATA 72–32–

31–200–000), contains limits for corrosion 

pitting of the IPC stage 5 disk. 

(ii) If the disk passes the ECI and you find 

no cracks, perform an MPI on the entire disk. 

(iii) If the disk passes the MPI and you find 

no cracks, re-apply corrosion protection to 

the disk, and return the disk to service using 

the cyclic limits allowed by paragraph (m) of 

this AD. 


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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 12063 

Optional On-Wing Eddy Current Inspections 

(k) You may perform an optional on-wing 

ECI of the IPC stage 5 disk only once between 

shop visit inspections as follows: 

(1) For RB211–524B2/C2, RB211–524B/B3, 

and RB211–524B4/D4 series engines, use 

paragraphs 3.A. through 3.F. of the 

Accomplishment Instructions of RR SB No. 

RB.211–72–E148, dated March 13, 2003, and 

RR SB No. RB.211–72–E150, Revision 1, 

dated June 4, 2003. 

(2) For RB211–524G2, RB211–524G2–T, 

RB211–524G3, RB211–524G3–T, RB211–

524H, RB211–524H–T, RB211–524H2, and 

RB211–524H2–T series engines, use 

paragraphs 3.A. through 3.M. of the 

Accomplishment Instructions of RR SB No. 

RB.211–72–E171, Revision 1, dated February 

8, 2005. 

(3) If the disk passes the ECI and you find 

no cracks, you may extend the cycle life as 

specified in paragraph (m) of this AD. 

Definition of Shop Visit 

(l) The manufacturer defines a shop visit as 

the separation of an engine major case flange. 

This definition excludes shop visits when 

only field maintenance type activities are 

performed in lieu of performing them onwing (such as to perform an on-wing 

inspection of a tail engine installation on a 

Lockheed L–1011 series airplane). 

Cyclic Life Extension 

(m) Disks that pass an optional inspection 

may remain in service after that inspection 

for the additional cycles listed in the 

following Table 5, until the next inspection, 

until the cyclic life limit published in the RR 

Time Limits Manual, 05–10–01, is reached, 

or December 1, 2008, whichever occurs first. 

TABLE 5.—CYCLIC LIFE EXTENSION

Type of extension 

Engine models 

–524G2, G2–

T, G3, G3–T, 

H2, H2–T, H–

36, H–T–36 

(cycles) 

–524D4, D4–

B, D4–B–39, 

D4X, D4X–B, 

D4–39 

(cycles) 

–524B2, B2–

B, C2, C2–B 

(cycles) 

–524B–02, B–

B–02, B3–02, 

B4–02, B4–D–

02 

(cycles) 

Extension After Passing MPI ........................................................................... 1,600 2,000 2,000 2,000 

Extension After Passing In-Shop ECI ............................................................. 3,800 4,500 4,500 4,500 

Extension After Passing On-Wing ECI ............................................................ 1,000 1,200 1,200 1,200 

Disks That Have Been Intermixed Between 

Engine Models 

(n) The RR Time Limits Manual, 05–00–01, 

contains information on intermixing disks 

between engine models. 

Alternative Methods of Compliance 

(o) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Credit for Previous Inspections 

(p) Inspections done using RR SB No. 

RB.211–72–E150, dated April 17, 2003, SB 

No. RB.211–72–E171, dated December 14, 

2004, SB No. RB.211–72–D428, Revision 3, 

dated June 30, 2003, and ASB No. RB.211–

72–AD428, Revision 4, dated March 7, 2005, 

meet the requirements of this AD. 

Reporting Requirement 

(q) Report findings of all inspections of the 

IPC stage 5 disk using paragraph 3.B.(2) of 

the Accomplishment Instructions of RR No. 

ASB RB.211–72–AD428, Revision 5, dated 

March 18, 2005. The Office of Management 

and Budget (OMB) has approved the 

reporting requirements specified in 

Paragraph 3.B. of the Accomplishment 

Instructions of RR No. ASB RB.211–72–

AD428, Revision 5, dated March 18, 2005, 

and assigned OMB control number 2120–

0056. 

Related Information 

(r) CAA airworthiness directive G–2005–

0008, dated March 8, 2005, also addresses the 

subject of this AD. 

(s) Contact Ian Dargin, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone (781) 238–7178; fax (781) 238–

7199; e-mail: ian.dargin@faa.gov for more 

information about this AD. 

Material Incorporated by Reference 

(t) You must use the service information 

specified in Table 6 to perform the actions 

required by this AD. The Director of the 

Federal Register approved the incorporation 

by reference of the documents listed in Table 

6 of this AD in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact RollsRoyce plc, P.O. Box 31 Derby, DE248BJ, 

United Kingdom; telephone 011–44–1332–

242424; fax 011–44–1332–249936 for a copy 

of this service information. You may review 

copies at the FAA, New England Region, 

Office of the Regional Counsel, 12 New 

England Executive Park, Burlington, MA; or 

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. 

TABLE 6.—INCORPORATION BY REFERENCE

Rolls-Royce plc Service Bulletin (SB)/Alert Service Bulletin (ASB) No. Page Revision Date 

SB No. RB.211–72–E148 ..................................................................................................... All ................ Original ........ March 13, 2003. 

Total Pages: 83 

SB No. RB.211–72–E150 ..................................................................................................... All ................ 1 .................. June 4, 2003. 

Total Pages: 72 

SB No. RB.211–72–E171 ..................................................................................................... All ................ 1 .................. February 8, 2005 

Total Pages: 71 

ASB No. RB.211–72–AD428 ................................................................................................ All ................ 5 .................. March 18, 2005. 

Total Pages: 27 

Appendix 1 of ASB No. RB.211–72–AD428 ........................................................................ All ................ 5 .................. March 18, 2005. 

Total Pages: 4 

Appendix 2 of ASB No. RB.211–72–AD428 ........................................................................ All ................ 5 .................. March 18, 2005. 

Total Pages: 2 

Appendix 3 of ASB No. RB.211–72–AD428 ........................................................................ All ................ 5 .................. March 18, 2005. 

Total Pages: 5 

Appendix 4 of ASB No. RB.211–72–AD428 ........................................................................ All ................ 5 .................. March 18, 2005. 

Total Pages: 2 


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12064 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 

Issued in Burlington, Massachusetts, on 

March 7, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–4536 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26497; Directorate 

Identifier 2006–CE–082–AD; Amendment 

39–14989; AD 2007–06–08] 

RIN 2120–AA64 

Airworthiness Directives; 

Przedsiebiorstwo DoswiadczalnoProdukcyjne Szybownictwa ‘‘PZL–

Bielsko’’ Model SZD–50–3 ‘‘Puchacz’’

Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. 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: 

Some cases of turnbuckle adjusting screws 

fatigue failure have occurred, due to lateral 

load component applied by pilot’s foot. Such 

events may lead to rudder and pedals 

disconnection. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective April 

19, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 19, 2007. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Gregory Davison, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4130; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

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 January 5, 2007 (72 FR 485). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states that some 

cases of turnbuckle adjusting screws 

fatigue failure have occurred, due to 

lateral load component applied by 

pilot’s foot. Such events may lead to 

rudder and pedals disconnection. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 8 

products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $100 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $2,080, or 

$260 per product. 

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 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 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); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 


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