Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules 39189 

Issued in Renton, Washington, on June 25, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16606 Filed 7–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0674; Directorate 

Identifier 2010–NM–012–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Model 747 airplanes. This proposed AD 

would require repetitive inspections for 

cracking in the body skin around the aft 

corners of the nose wheel well; for 

certain airplanes, repetitive inspections 

for cracking in the skin splice plate at 

the aft corners of the nose wheel well; 

and related investigative and corrective 

actions if necessary. This proposed AD 

would also require repetitive postmodification inspections for cracking in 

the body skin and the skin splice plate; 

for certain airplanes, an inspection for 

steel cross-shaped doublers on the larger 

aluminum doublers; and corrective 

action if necessary. This proposed AD 

would also require repetitive surface 

high frequency eddy current (HFEC) 

inspections of a certain bulkhead outer 

chord, skin splice plate, and outer chord 

radius filler for cracking; repetitive 

detailed inspections for cracking of the 

bulkhead frame web and body skin; and 

corrective actions if necessary. This 

proposed AD would provide for 

optional terminating action for certain 

repetitive inspections. This proposed 

AD results from reports of cracking of 

the fuselage skin and adjacent internal 

skin splice plate at the left and right 

nose wheel well aft corners, and the 

outer chord of the body station (BS) 400 

bulkhead. We are proposing this AD to 

detect and correct cracking of the 

fuselage skin or splice plate, which, 

together with cracking of the bulkhead 

outer chord, could result in large skin 

cracks and subsequent in-flight rapid 

decompression of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 23, 2010. 

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. 

For service information identified in 

this proposed 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; e-mail 

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 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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

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–2010–0674; Directorate Identifier 

2010–NM–012–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 have received reports of cracking 

of the fuselage skin and adjacent 

internal skin splice plate at the left and 

right nose wheel well aft corners, and 

the outer chord of the body station (BS) 

400 bulkhead. Cracks were found in the 

skin on an airplane that had 

accumulated about 6,355 total flight 

cycles. In addition, small cracks were 

found in the outer chord of the body 

station (BS) 400 bulkhead on airplanes 

that had accumulated fewer than 20,000 

total flight cycles. Cracking of the 

fuselage skin or splice plate, together 

with cracking of the bulkhead outer 

chord, if not detected and corrected, 

could result in large skin cracks and 

subsequent in-flight rapid 

decompression of the airplane. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2305, Revision 

2, dated January 15, 2009. The service 

bulletin describes procedures for 

repetitive external detailed inspections 

for cracking in the body skin around the 

aft corners of the nose wheel well; for 

certain airplanes, repetitive external 

detailed inspections for cracking in the 

skin splice plate at the aft corners of the 

nose wheel well, and modification of 

any cracked aft corners of the nose 

wheel well by installing modification 

doublers; and, for certain airplanes, and 

a one-time external general visual 

inspection for steel cross-shaped 

doublers. The modification, which, if 

accomplished to repair cracks or to 

eliminate the need for certain repetitive 

inspections, includes related 

investigative actions and corrective 

actions if necessary. The related 

investigative actions include an openhole HFEC inspection for cracking at 

fasteners common to the bulkhead outer 

chord, and a surface HFEC inspection or 

penetrant inspection for cracking of the 

skin if necessary. The corrective actions 

include repairing the crack, installing 

cross-shaped doublers, and contacting 

Boeing for repair instructions and doing 

the repair. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
39190 Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules 

The service bulletin also describes 

procedures for repetitive postmodification inspections, which consist 

of an external low frequency eddy 

current (LFEC) inspection for cracking 

in the skin around fasteners at the 

periphery of modification doublers, and 

contacting Boeing for instructions to 

repair cracks and doing the repair. The 

service bulletin also describes 

procedures for repetitive surface HFEC 

inspections for cracking of a certain 

bulkhead outer chord, skin splice plate, 

and outer chord radius filler; repetitive 

detailed inspections for cracking of the 

bulkhead frame web and body skin, and 

corrective actions if necessary. The 

corrective actions include repairing the 

crack, or contacting Boeing for repair 

instructions and repairing if necessary. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

described below. 

Differences Between Proposed Rule and 

Service Bulletin 

Boeing Service Bulletin 747– 

53A2305, Revision 2, dated January 15, 

2009, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 160 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 

TABLE—ESTIMATED COSTS

Action Work hours Average labor 

rate per hour 

Cost per 

product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspections: Body skin and skin splice plate ............... 1 $85 $85 160 ................... $13,600. 

Modification: Groups 1–3 1 ........................................... 180 85 15,300 Up to 27 ........... Up to $413,100. 

Modification: Groups 1–3 2 ........................................... 320 85 27,200 Up to 27 ........... Up to $734,400. 

Modification: Groups 4–8 3 ........................................... 180 85 15,300 Up to 133 ......... Up to $2,034,900. 

Modification: Groups 4–7 4 ........................................... 40 85 3,400 Up to 44 ........... Up to $149,600. 

Post-Mod LFEC Inspection 5 ........................................ 6 85 510 Up to 160 .......... Up to $81,600. 

Inspections: Bulkhead Outer Chord 6 ........................... 4 85 340 Up to 160 ......... Up to $54,400. 

1 Installation of skin and splice plate doubler for Groups 1–3 airplanes that have not done Boeing Service Bulletin 747–53–2150 or Figure 35 of 

Section 53–30–03 of the Boeing 747 Structural Repair Manual. 2 Installation of skin and splice plate doubler for Groups 1–3 airplanes that have done Boeing Service Bulletin 747–53–2150 or Figure 35 of 

Section 53–30–03 of the Boeing 747 Structural Repair Manual. 3 Installation of skin and splice plate doubler for Groups 4–8 airplanes. 

4 Installation of splice plate doubler for Groups 4–7 airplanes changed before Boeing Alert Service Bulletin 747–53A2305, Revision 2, dated 

January 15, 2009. 5 Inspection for skin cracks around the fasteners at the periphery of the modification doublers. 

6 Includes inspection of the frame web and body skin. 

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: 

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: 

The Boeing Company: Docket No. FAA– 

2010–0674; Directorate Identifier 2010– 

NM–012–AD. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules 39191 

Comments Due Date 

(a) We must receive comments by August 

23, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747–400F, 

747SR, and 747SP series airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reports of cracking 

of the fuselage skin and adjacent internal 

skin splice plate at the left and right nose 

wheel well aft corners, and the outer chord 

of the body station (BS) 400 bulkhead. The 

Federal Aviation Administration is issuing 

this AD to detect and correct cracking of the 

fuselage skin or splice plate, which, together 

with cracking of the bulkhead outer chord, 

could result in large skin cracks and 

subsequent in-flight rapid decompression of 

the airplane. 

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. 

Pre-Modification Inspections 

(g) For airplanes in Groups 1 through 3, as 

identified in Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, that have not been modified in 

accordance with Boeing Service Bulletin 

747–53–2150; have not been repaired in 

accordance with Figure 35 of Section 53–30– 

03 of Boeing 747 Structural Repair Manual 

(SRM); and have not been modified in 

accordance with Boeing Alert Service 

Bulletin 747–53A2305: Before the 

accumulation of 3,000 total flight cycles, or 

within 1,500 flight cycles after the effective 

date of this AD, whichever occurs later, do 

an external detailed inspection for cracks in 

the body skin around the aft corners of the 

nose wheel well, and skin splice plate at the 

aft corners of the nose wheel well, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009. 

(h) For airplanes in Groups 1 through 3, as 

identified in Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, that have been modified in accordance 

with Boeing Service Bulletin 747–53–2150; 

or repaired in accordance with Boeing 747 

Figure 35 of Section 53–30–03 of Boeing 747 

SRM: Within 6,000 flight cycles after doing 

the modification or repair, or within 1,500 

flight cycles after the effective date of this 

AD, whichever occurs later, do an external 

detailed inspection for cracks in the body 

skin around the aft corners of the nose wheel 

well, and skin splice plate at the aft corners 

of the nose wheel well, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009. 

(i) For airplanes in Groups 4 through 7, as 

identified in Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, that have not been modified in 

accordance with Boeing Alert Service 

Bulletin 747–53A2305: Prior to the 

accumulation of 3,000 total flight cycles, or 

within 1,500 flight cycles after the effective 

date of this AD, whichever occurs later, do 

an external detailed inspection for cracks in 

the body skin around the aft corners of the 

nose wheel well, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009. 

(j) For airplanes in Groups 4 through 7, as 

identified in Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, that have been modified in accordance 

with Boeing Service Bulletin 747–53–2305, 

dated June 27, 1991; or Revision 1, dated 

May 22, 1997: Within 1,000 flight cycles after 

the effective date of this AD, do a one-time 

external general visual inspection for steel 

cross-shaped doublers, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009. If no 

cross-shaped doublers are installed, within 

1,500 flight cycles after the effective date of 

this AD, install cross-shaped doublers, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009. 

(k) For airplanes in Group 8, as identified 

in Boeing Alert Service Bulletin 747– 

53A2305, Revision 2, dated January 15, 2009: 

Prior to the accumulation of 3,000 total flight 

cycles, or within 1,500 flight cycles after the 

effective date of this AD, whichever occurs 

later, do an external detailed inspection for 

cracks in the body skin around the aft corners 

of the nose wheel well, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009. 

(l) If no crack is found during any 

inspection required by paragraph (g), (h), (i), 

or (k) of this AD, repeat the applicable 

inspection specified in paragraph (g), (h), (i), 

or (k) of this AD thereafter at intervals not to 

exceed 1,500 flight cycles, until the 

modification specified in paragraph (n) of 

this AD is accomplished. 

(m) If any crack is found during any 

inspection required by paragraph (g), (h), (i), 

(k), or (l) of this AD, before further flight, 

modify the aft corners of the nose wheel well 

by installing modification doublers and 

doing all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009, except as required by 

paragraph (t) of this AD. 

Optional Terminating Action 

(n) Modification of the aft corners of the 

nose wheel well by installing modification 

doublers and doing all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, terminates the repetitive inspections 

required by paragraph (l) of this AD for the 

modified side only. Where Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009, specifies to contact 

Boeing for appropriate action, repair using a 

method approved in accordance with the 

procedures specified in paragraph (u) of this 

AD. 

Post-Modification Repetitive Inspections 

(o) For airplanes on which the 

modification specified in Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009, has been done: At the 

applicable time specified in paragraph (o)(1) 

or (o)(2) of this AD, do an external low 

frequency eddy current inspection for skin 

cracks around the fasteners at the periphery 

of the modification doublers, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009. 

(1) For airplanes on which the edge row 

fastener holes common to the external 

modification doublers have been zero-timed 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009: Within 15,000 flight cycles after 

accomplishing the modification, or within 

1,500 flight cycles after the effective date of 

this AD, whichever occurs later. 

(2) For airplanes on which the edge row 

fastener holes common to the external 

modification doublers have not been zerotimed in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009: Prior to the 

accumulation of 15,000 total flight cycles, or 

within 1,500 flight cycles after the effective 

date of this AD, whichever occurs later. 

(p) If no cracking is found during the 

inspection required by paragraph (o) of this 

AD, repeat the inspection specified in 

paragraph (o) of this AD thereafter at 

intervals not to exceed 1,500 flight cycles. 

(q) If any cracking is found during any 

inspection required by paragraph (o) or (p) of 

this AD, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (u) of this 

AD. 

Body Station (BS) 400 Bulkhead Outer 

Chord Inspection 

(r) For all airplanes: At the latest of the 

times specified in paragraphs (r)(1), (r)(2), 

and (r)(3) of this AD, do a surface HFEC for 

cracking in the BS 400 bulkhead outer chord, 

skin splice plate, and outer chord radius 

filler; and a detailed inspection for cracking 

of the bulkhead frame web and body skin; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009. If no cracking is found during any 

inspection, repeat the inspection one time 

within 6,000 flight cycles, and thereafter at 

intervals not to exceed 3,000 flight cycles. 

(1) Before the accumulation of 20,000 total 

flight cycles. 

(2) Within 3,000 flight cycles after doing 

the HFEC inspection required by AD 2004– 


srobinson on DSKHWCL6B1PROD with PROPOSALS
39192 Federal Register / Vol. 75, No. 130 / Thursday, July 8, 2010 / Proposed Rules 

07–22 R1, Amendment 39–15326, for 

structural significant item (SSI) F–4B of the 

Boeing Document No. D6–35022, 

‘‘Supplemental Structural Inspection 

Document (SSID) for Model 747 Airplanes,’’ 

Revision G, dated December 2000. 

(3) Within 1,500 flight cycles after the 

effective date of this AD. 

(s) If any cracking is found during any 

inspection required by paragraph (r) of this 

AD, before further flight, repair in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009, except as 

required by paragraph (t) of this AD. Within 

6,000 flight cycles after doing the repair, do 

the inspections specified in paragraph (r) of 

this AD, and repeat the inspections thereafter 

at intervals not to exceed 3,000 flight cycles. 

Service Bulletin Exception 

(t) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009, 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 (u) of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(u)(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: Ivan 

Li, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6437; fax (425) 917–6590. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that 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 June 29, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16551 Filed 7–7–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0564; Directorate 

Identifier 2010–SW–13–AD] 

RIN 2120–AA64 

Airworthiness Directives; Arrow 

Falcon Exporters, Inc. (Previously Utah 

State University), et al., Model HH–1K, 

TH–1F, TH–1L, UH–1A, UH–1B, UH–1E, 

UH–1F, UH–1H, UH–1L, and UH–1P 

Helicopters; and Southwest Florida 

Aviation Model UH–1B (SW204 and 

SW204HP) and UH–1H (SW205) 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

adopting a new airworthiness directive 

(AD) for the specified type-certificated 

military surplus helicopters. The AD 

would require: Creating a component 

history card or equivalent record for 

each main rotor grip (grip); determining 

and recording the total hours time-inservice (TIS) for each grip; visually 

inspecting the upper and lower tangs of 

the grip for a crack; inspecting the grip 

buffer pads for delamination and if 

delamination is present, inspecting the 

grip surface for corrosion or other 

damage; inspecting the grip for a crack 

using ultrasonic (UT) and fluorescentpenetrant inspection methods; and 

establishing a retirement life for certain 

grips. This proposal is prompted by 

three in-flight failures of grips installed 

on Bell Helicopter Textron, Inc. (BHTI) 

Model 212 helicopters, which resulted 

from cracks originating in the lower 

main rotor blade bolt lug. The actions 

specified by the proposed AD are 

intended to prevent failure of the grip, 

separation of a main rotor blade, and 

subsequent loss of control of the 

helicopter. 

DATES: Comments must be received on 

or before September 7, 2010. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD: 

• 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. 

You may get the service information 

identified in this proposed AD from Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101, telephone (817) 

280–3391, fax (817) 280–6466, or at 

http://www.bellcustomer.com/files/. 

You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Michael 

Kohner, ASW–170, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Rotorcraft Certification Office, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax 

(817) 222–5783. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any written 

data, views, or arguments regarding this 

proposed AD. Send your comments to 

the address listed under the caption 

ADDRESSES. Include the docket number 

‘‘FAA–2010–0564, Directorate Identifier 

2010–SW–13–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light 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 with FAA 

personnel concerning this proposed 

rulemaking. Using the search function 

of our docket Web site, you can find and 

read the comments to any of our 

dockets, including the name of the 

individual who sent or signed the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

Examining the Docket 

You may examine the docket that 

contains the proposed AD, any 

comments, and other information in 

person at the Docket Operations office 

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

through Friday, except Federal holidays. 

The Docket Operations office (telephone 


srobinson on DSKHWCL6B1PROD with PROPOSALS