9776 Federal Register / Vol. 74, No. 43 / Friday, March 6, 2009 / Proposed Rules 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Certain Requirement of AD 98–06–07 

Airplane Flight Manual (AFM) Revision 

(g) Within 72 hours after March 27, 1998 

(the effective date of AD 98–06–07), revise 

the Limitations Section of the FAA-approved 

AFM to add the following. This may be 

accomplished by inserting a copy of this AD 

in the AFM. 

‘‘LIMITATIONS POWERPLANT AND APU 

LIMITATIONS 

OPERATING LIMITS 

• To avoid high fan blade stresses, 

stabilized operation in the speed range 

between 60% and 75% Low Pressure 

Rotational Speed (N1) is not permitted 

during Ground Operations in Forward or 

Reverse Thrust, except that passing through 

this range while increasing or decreasing 

thrust is permitted. 

THRUST REVERSER 

Thrust reversers are intended for ground 

use only. Intentional use of reverse thrust in 

flight is prohibited. After reverse thrust has 

been initiated, a full stop landing must be 

made. 

Maximum Reverse Thrust Lever Positions 

Normal Operation: 

—The idle detent position shall not be 

exceeded in normal operation. 

—Momentarily exceeding the idle detent 

position, while selecting idle reverse, is 

acceptable. 

Emergency Operation: 

—In case of emergency, the emergency 

maximum reverse thrust may be used. 

—If directional control problems occur, 

reduce to idle reverse or select forward 

idle. 

—Stabilized operation with the reverse lever 

in an intermediate position between idle 

reverse and emergency maximum reverse 

is prohibited, except (where approved) 

during Power-Back operations.’’ 

Note 1: Fokker Services Manual Change 

Notification—Operational Documentation 

(MCNO) No. F100–006, dated November 27, 

1997, contains information that pertains to 

this subject. Rolls-Royce PLC Engine 

Operating Instruction Manual Reference F– 

TAY–3RR, revised by transmittal letter No. 

13, dated October 15, 1997, also pertains to 

this subject. 

New Actions Required by This AD 

Removal of Normal Maximum Detent 

(h) Within 12 months after the effective 

date of this AD, remove the normal 

maximum (second) detent for the reversethrust control, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–76–014, Revision 2, 

dated December 12, 2007. Accomplishing the 

removal terminates the requirements of 

paragraph (g) of this AD. 

(i) Actions done before the effective date of 

this AD in accordance with Fokker Service 

Bulletin SBF100–76–014, dated October 1, 

2001; or Revision 1, dated June 1, 2002; are 

acceptable for compliance with the 

requirements of paragraph (h) of this AD. 

AFM Revision 

(j) Concurrently with the requirements of 

paragraph (h) of this AD, revise the 

Limitations Section of the Fokker F.28 Mark 

0100 AFM to include the following (this may 

be accomplished by inserting a copy of this 

AD into the AFM): 

‘‘THRUST REVERSERS 

Thrust reversers are intended for ground 

use only. Intentional use of reverse thrust in 

flight is prohibited. 

The use of Max Reverse thrust is limited 

to operations on short runways or on 

runways with a reduced runway surface 

friction coefficient or in emergency 

conditions. Max Reverse thrust shall not be 

used at airspeeds below 60 knots except in 

emergency conditions. 

Reverse thrust selections between Idle 

Reverse thrust and Max Reverse thrust are 

prohibited.’’ 

Note 2: Fokker Manual Change 

Notification—Operational Documentation 

(MCNO) F100–032, Revision 1, dated 

September 21, 2007, contains information 

related to the AFM revision required by 

paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k) The Manager, International Branch, 

ANM–116, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. Send 

information to ATTN: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

Related Information 

(l) The European Aviation Safety Agency 

Airworthiness Directive 2008–0089, dated 

May 13, 2008, also addresses the subject of 

this AD. 

Issued in Renton, Washington, on February 

20, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–4731 Filed 3–5–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0669; Directorate 

Identifier 2007–NM–350–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–600, –700, and –800 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Boeing Model 737–600, –700, 

and –800 series airplanes. The original 

NPRM would have required an 

inspection of the free flange of the lower 

stringers of the wing center section for 

drill starts, and applicable related 

investigative and corrective actions. The 

original NPRM resulted from drill starts 

being found on the free flange of the 

lower stringers of the wing center 

section during a quality assurance 

inspection at the final assembly plant. 

This action revises the original NPRM 

by expanding the inspection area to 

include the free flange, the vertical web, 

and the fillet radius between the vertical 

web and the free flange. We are 

proposing this supplemental NPRM to 

prevent cracks from propagating from 

drill starts in the free flange, vertical 

web, and radius between the free flange 

and vertical web of the lower stringers 

of the wing center section lower 

stringers, which could cause a loss of 

structural integrity of the wing center 

section and may result in a fuel leak. 

DATES: We must receive comments on 

this supplemental NPRM by March 31, 

2009. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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Federal Register / Vol. 74, No. 43 / Friday, March 6, 2009 / Proposed Rules 9777 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207; 

telephone 206–544–9990; fax 206–766– 

5682; e-mail DDCS@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 

or 425–227–1152. 

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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590. 

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–2008–0669; Directorate Identifier 

2007–NM–350–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 

We issued a notice of proposed 

rulemaking (NPRM) (the ‘‘original 

NPRM’’) to amend 14 CFR part 39 to 

include an airworthiness directive (AD) 

that would apply to certain Boeing 

Model 737–600, –700, and –800 series 

airplanes. That original NPRM was 

published in the Federal Register on 

June 24, 2008 (73 FR 35593). That 

original NPRM proposed to require 

inspecting the free flange of the lower 

stringers of the wing center section for 

drill starts, and applicable related 

investigative and corrective actions. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Clarify Inspection 

Requirements 

Boeing notes that the original NPRM 

would have required an inspection of 

the free flange of the stringer, whereas 

paragraph 3.B.2. of the Accomplishment 

Instructions in Boeing Alert Service 

Bulletin 737–57A1294, dated April 23, 

2007, calls for inspection as given in 

Figure 1 of the service bulletin. Figure 

1 specifies that the free flange, vertical 

web, and radius between the free flange 

and vertical web must be inspected. 

(The original NPRM referred to this 

service bulletin as the appropriate 

source of service information for the 

proposed actions.) The commenter 

requests that we clarify whether the 

inspection area is to include the free 

flange, vertical web, and the fillet 

radius. 

We agree that the original NPRM is 

unclear whether the inspection area 

includes all three parts of the stringer. 

The service bulletin does not 

consistently include all three parts of 

the stringer. The ‘‘Background’’ section, 

the ‘‘Action’’ section, Paragraph 1.C., 

‘‘Reason,’’ Paragraph 1.D., 

‘‘Description,’’ and Paragraph 3.B., 

‘‘Work Instructions,’’ refer only to the 

free flange for the inspection. Only a 

note in Figure 1, Sheet 4, contains any 

reference to all three areas of 

inspection—free flange, vertical web, 

and the fillet radius. We have 

determined that all three areas must be 

inspected to adequately address the 

identified unsafe condition. We have 

revised paragraph (g) of the 

supplemental NRPM to explicitly state 

these three areas of inspection. We have 

also revised the description of the area 

in the summary and paragraph (e) of the 

supplemental NPRM. 

Actions Since the Original NPRM Was 

Issued 

We have added a new paragraph (d) 

to this proposed AD to specify the Air 

Transport Association (ATA) of America 

code identifying the subject, and reidentified the subsequent paragraphs 

accordingly. 

FAA’s Determination and Proposed 

Requirements of the Supplemental 

NPRM 

We are proposing this supplemental 

NPRM because we evaluated all 

pertinent information and determined 

an unsafe condition exists and is likely 

to exist or develop on other products of 

the same type design. The change 

described above expands the scope of 

the original NPRM. As a result, we have 

determined that it is necessary to reopen 

the comment period to provide 

additional opportunity for the public to 

comment on this supplemental NPRM. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 17 airplanes of U.S. 

registry. We also estimate that it would 

take 7 work-hours per product to 

comply with this proposed AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 

cost of this proposed AD to the U.S. 

operators to be $9,520, or $560 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 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 this proposed regulation: 

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9778 Federal Register / Vol. 74, No. 43 / Friday, March 6, 2009 / Proposed Rules 

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), 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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 adding 

the following new AD: 

Boeing: Docket No. FAA–2008–0669; 

Directorate Identifier 2007–NM–350–AD. 

Comments Due Date 

(a) We must receive comments by March 

31, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737– 

600, –700, and –800 series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 737–57A1294, 

dated April 23, 2007. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from drill starts being 

found on the free flange of the lower stringers 

of the wing center section during a quality 

assurance inspection at the final assembly 

plant. We are issuing this AD to prevent 

cracks from propagating from drill starts in 

the free flange, vertical web, and radius 

between the free flange and vertical web of 

the lower stringers of the wing center section 

lower stringers, which could cause a loss of 

structural integrity of the wing center section 

and may result in a fuel leak. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Inspection and Related Investigative and 

Corrective Actions 

(g) Before the accumulation of 18,000 total 

flight cycles, or within 90 days after the 

effective date of this AD, whichever occurs 

later, do a detailed inspection of the free 

flange, vertical web, and radius between the 

free flange and vertical web of the lower 

stringers of the wing center section for any 

drill start, and do all applicable related 

investigative and corrective actions, by 

accomplishing all the applicable actions 

specified in paragraphs 3.B.2 and 3.B.4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–57A1294, dated April 

23, 2007; except as provided in paragraph (h) 

of this AD. The applicable related 

investigative and corrective actions must be 

done before further flight. 

(h) If any crack is found during any 

inspection required by paragraph (g) of this 

AD, and Boeing Alert Service Bulletin 737– 

57A1294, dated April 23, 2007, specifies to 

contact Boeing for appropriate action: Before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(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. Send information to ATTN: 

Nancy Marsh, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(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 an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Issued in Renton, Washington, on February 

20, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–4732 Filed 3–5–09; 8:45 am] 

BILLING CODE 4910–13–P 

mstockstill on PROD1PC66 with PROPOSALS