This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

6419 

Vol. 73, No. 23 

Monday, February 4, 2008 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27229; Directorate 

Identifier 2007–NE–03–AD; Amendment 39– 

15359; AD 2008–03–09] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A. CFM56–7B Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for CFM 

International, S.A. CFM56–7B series 

turbofan engines. This AD requires 

revising the Airworthiness Limitations 

Section (ALS) in the Engine Shop 

Manual (ESM) and the air carrier’s 

approved continuous airworthiness 

maintenance program (CAMP) to add 

mandatory inspections of certain low 

pressure turbine rear frames (TRFs) to 

the ALS or CAMP. This AD results from 

a refined lifing analysis by the engine 

manufacturer that shows the need to 

identify an initial threshold for 

inspecting certain TRFs. We are issuing 

this AD to prevent failure of the TRF 

from low-cycle fatigue cracks. Failure of 

the TRF could result in engine 

separation from the airplane, which 

could lead to loss of control of the 

airplane. 

DATES: This AD becomes effective 

March 10, 2008. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Antonio Cancelliere, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; telephone (781) 

238–7751; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to CFM International, S.A. 

CFM56–7B series turbofan engines. We 

published the proposed AD in the 

Federal Register on April 23, 2007 (72 

FR 20075). That action proposed to 

require revising the ALS in the Engine 

Shop Manual and the air carrier’s 

approved continuous airworthiness 

maintenance program (CAMP) to add 

mandatory inspections of certain low 

pressure turbine rear frames (TRFs) to 

the ALS or CAMP. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 street address for 

the Docket Operations office (telephone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Update Table for Figure 805 

Delta Airlines requests that we change 

the wording in the table for Figure 805 

because CFM International updated 

CFM56–7B Engine Shop Manual section 

05–21–03, with Temporary Revision 05– 

0080, dated December 5, 2006. We agree 

and have reworded the table for Figure 

805 to reflect wording used by the 

original equipment manufacturer 

(OEM). For clarification, we also moved 

the titles for Figures 806 and 807 to the 

beginning of the figures. 

Guidance on Future Revisions 

Delta Airlines also suggests that we 

provide guidance on making future 

OEM revisions to ESM section 05–21–03 

while maintaining compliance with the 

AD. We disagree. The information 

contained within sections (j) and (k) of 

the AD is adequate. Any future OEM 

changes to the ALS that affect 

compliance with this AD will require an 

AD revision or supersedure, depending 

on the specific situation. Airlines 

should make changes to items outside of 

this specific area and incorporate them 

into their ESM or CAMP per their 

normal procedures. 

Add Part Numbers (P/Ns) to 

Applicability 

Finally, Delta Airlines requests that 

we add P/Ns 340–166–251–0, 340–166– 

252–0 and 340–166–253–0 to the 

Applicability section and clarify 

whether these P/Ns will be applicable to 

the business jet application as well as 

the commercial application. We 

disagree. The intent of this AD is to 

make operators aware of the life limit/ 

mandatory inspections recently 

introduced by CFM International in the 

Airworthiness Limitations Section of 

the CFM56–7B Engine Shop Manual 

that affect P/Ns that were not previously 

limited. Ignoring these new limitations 

could create a potentially unsafe 

condition. The P/Ns listed above were 

subject to a life limit and mandatory 

inspection when first introduced to the 

ESM, therefore, there is no potential 

unsafe condition. Business jet and 

commercial engine model applicability 

of the new P/Ns is as listed in the ESM. 

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. 

Costs of Compliance 

We estimate that this AD will affect 

1,228 engines installed on airplanes of 

U.S. registry. While the cost of making 

the manual change is negligible, the 

resulting inspections must be discussed. 

Since life extensions are possible on 

condition, the cost of the AD is limited 

to performing TRF inspections. We 

estimate that it will take about 3.0 workhours per engine to perform the actions, 

including the TRF inspections, and that 

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hour. No parts are required. Based on 

these figures, we estimate the total cost 

of the AD to U.S. operators to be 

$294,720. 

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, 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 adding 

the following new airworthiness 

directive: 

2008–03–09 CFM International, S.A.: 

Amendment 39–15359. Docket No. 

FAA–2007–27229; Directorate Identifier 

2007–NE–03–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 10, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to CFM International, 

S.A. CFM56–7B18, –7B20, –7B22, –7B24, 

–7B26, –7B27, –7B22/B1, –7B24/B1, –7B26/ 

B1, –7B27/B1, –7B22/B2, –7B26/B2, –7B27/ 

B3 turbofan engines with turbine rear frame 

(TRF), part numbers 340–166–205–0, 340–

166–206–0, 340–166–207–0, 340–166–208–0, 

340–166–209–0, and 340–166–210–0, 

installed. These engines are installed on, but 

not limited to, Boeing 737 series airplanes. 

Unsafe Condition 

(d) This AD results from a refined lifing 

analysis by the engine manufacturer that 

shows the need to identify an initial 

threshold for inspecting certain TRFs. We are 

issuing this AD to prevent failure of the TRF 

from low-cycle fatigue cracks. Failure of the 

TRF could result in engine separation from 

the airplane, which could lead to loss of 

control of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

30 days after the effective date of this AD, 

unless the actions have already been done. 

Mandatory Inspections 

(f) Within the next 30 days after the 

effective date of this AD, revise the 

applicable inspection program for the 

Business Jet and Air Carrier engine models 

by adding the Mandatory Inspection Intervals 

as specified in this AD, and revise the 

Airworthiness Limitations Section (ALS) 

(chapter 05–21–03) of the CFM56–7B Engine 

Shop Manual, CFMI–TP–SM.10 by adding 

the following: 

TURBINE REAR FRAME WITH 

TANGENTIAL STRUTS—MANDATORY 

INSPECTIONS—LIFE LIMITS 

TASK 05–21–03–200–001 

1. General 

A. This section contains the FAA and 

EASA mandatory Eddy Current inspection 

intervals for the turbine rear frame with 

tangential struts. The inspection uses: 

—A threshold limit, specified in flight cycles 

—Inspection intervals, specified in flight 

cycles 

B. The threshold limit is the timing of the 

first required inspection. First inspection 

must be done before that part has reached the 

threshold number of flight cycles. 

C. The inspection intervals specify the 

timing of inspections to be done after the 

threshold inspection has been reached. 

Inspections are repetitive without any limit. 

2. Mandatory Inspection Intervals for the 

Critical Areas of the Turbine Rear Frame with 

Tangential Struts (4 Mount Struts, No. 1, 2, 

15, and 16). 

C. Turbine Rear Frame Part Numbers 340–

166–205–0, 340–166–206–0, 340–166–207–0, 

340–166–208–0, 340–166–209–0, 340–166–

210–0, for all CFM56–7B SAC engine models 

(except –7B27A engine models). Refer to 

figure 805. 

Figure index No. Inspection location Inspection threshold (cycles since 

new) Inspection intervals (cycles) Inspection reference 

805 ........................ Strut/outer ring fillet radius on 

trailing edge (A).

25,000 * for –7B SAC (except 

business jet) engine models.

Refer to Figure 806 * for –7B SAC 

(except business jet) engine 

models.

Refer to SB 72–0579.* 

Strut/hub fillet radius on leading 

edge (B).

19,000 * for –7B SAC business jet 

engine models.

Refer to Figure 807 * for –7B SAC 

business jet engine models.

Strut/outer ring fillet radius on 

trailing edge (C1 below outer 

ring).

Strut/outer ring fillet radius on 

trailing edge (C2 above outer 

ring).

Note: * Applicable to all inspection locations. If inspection is not performed, part must be removed. 

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(g) After the effective date of this AD, we 

will not approve any alternative inspection 

intervals for these parts except as provided 

for in paragraph (j) of this AD. 

TRFs With Unknown Cycles 

(h) If you cannot establish the number of 

cycles accumulated since new, remove or 

inspect the TRF within 300 cycles-in-service 

after the effective date of this AD. The 

CFM56–7B Engine Shop Manual (ESM) or air 

carrier’s approved continuous airworthiness 

maintenance program (CAMP) contains 

information for inspecting the TRF. 

(i) You may install a TRF removed in 

paragraph (h) of this AD after the TRF passes 

an initial inspection for cracks. The CFM56–

7B ESM or CAMP contains information on 

inspecting the TRF. 

Alternative Methods of Compliance 

(j) 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. 

Maintaining Records of the Mandatory 

Inspections 

(k) You have met the requirements of this 

AD by making the changes to the Engine 

Shop Manual as specified in paragraph (f) of 

this AD, and, for air carriers operating under 

part 121 of the Federal Aviation Regulations 

(14 CFR part 121), by modifying your 

continuous airworthiness maintenance plan 

to reflect those changes. You must maintain 

records of the mandatory inspections that 

result from those changes to the ALS 

according to the regulations governing your 

operation. You do not need to record each 

inspection as compliance to this AD. For air 

carriers operating under part 121, you may 

use the system established to comply with 

section 121.369. 

Related Information 

(l) CFM International Service Bulletin 

CFM56–7B S/B 72–0579, Revision 1, dated 

October 27, 2006, contains information about 

Eddy Current inspection. 

(m) Contact Antonio Cancelliere, 

Aerospace Engineer, Engine Certification 

Office, FAA, Engine and Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA 01803; telephone (781) 238–

7751; fax (781) 238–7199, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

January 23, 2008. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–1830 Filed 2–1–08; 8:45 am] 

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