Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 16683 

Appendix B to Part 29—Airworthiness 

Criteria for Helicopter Instrument 

Flight 

* * * * * 

X. Electrical and electronic system 

lightning protection. For regulations 

concerning lightning protection for electrical 

and electronic systems, see § 27.1316. 

PART 29—AIRWORTHINESS 

STANDARDS: TRANSPORT 

CATEGORY ROTORCRAFT 

10. The authority citation for part 29 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

11. Amend § 29.610 by revising 

paragraph (d)(4) to read as follows: 

§ 29.610 Lightning and static electricity 

protection. 

* * * * * 

(d) * * * 

(4) Reduce to an acceptable level the 

effects of static electricity on the 

functioning of essential electrical and 

electronic equipment. 

§ 29.1309 [Amended] 

12. Amend § 29.1309 by removing 

paragraph (h). 

13. Add new § 29.1316 to read as 

follows: 

§ 29.1316 Electrical and electronic system 

lightning protection. 

(a) Each electrical and electronic 

system that performs a function, for 

which failure would prevent the 

continued safe flight and landing of the 

rotorcraft, must be designed and 

installed so that— 

(1) The function is not adversely 

affected during and after the time the 

rotorcraft is exposed to lightning; and 

(2) The system automatically recovers 

normal operation of that function in a 

timely manner after the rotorcraft is 

exposed to lightning. 

(b) Each electrical and electronic 

system that performs a function, for 

which failure would reduce the 

capability of the airplane or the ability 

of the flightcrew to respond to an 

adverse operating condition, must be 

designed and installed so that— 

(1) The system is not damaged after 

the rotorcraft is exposed to lightning; 

and 

(2) The function recovers normal 

operation in a timely manner after the 

rotorcraft is exposed to lightning. 

Issued in Washington, DC, on March 29, 

2010. 

Kalene C. Yanamura, 

Acting Director, Aircraft Certification Service. 

[FR Doc. 2010–7525 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0280; Directorate 

Identifier 2009–NM–259–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777–200LR and 

–300ER Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Model 777–200LR and –300ER series 

airplanes. This proposed AD would 

require doing a high frequency eddy 

current inspection for cracking of the 

keyway of the fuel tank access door 

cutout on the left and right wings 

between wing rib numbers 8 (wing 

station 387) and 9 (wing station 414.5), 

and related investigative and corrective 

actions if necessary. This proposed AD 

results from reports of cracks emanating 

from the keyway of the fuel tank access 

door cutout of the lower wing skin 

between wing rib numbers 8 and 9. We 

are proposing this AD to prevent loss of 

the lower wing skin load path, which 

could cause catastrophic structural 

failure of the wing. 

DATES: We must receive comments on 

this proposed AD by May 17, 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: 

Duong Tran, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6452; 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–2010–0280; Directorate Identifier 

2009–NM–259–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 cracks 

emanating from the keyway of the fuel 

tank access door cutout of the lower 

wing skin between wing rib numbers 8 

and 9. The keyway is found on Model 

777–200LR and 777–300ER airplanes at 

this location as the access door has a 

fuel measuring stick installed. The 

keyway is used to ensure that the fuel 

measuring stick is oriented properly in 

the access door cutout. The crack is the 

result of fatigue due to the position of 

the keyway. After the crack initiates, if 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
16684 Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 

it grows unchecked, it could result in 

the loss of the lower wing skin load path 

with catastrophic structural failure of 

the wing. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 777–57A0069, dated 

November 5, 2009. The service bulletin 

describes procedures for doing a high 

frequency eddy current (HFEC) 

inspection for cracking at the keyway of 

the fuel tank access door cutout on the 

left and right wings between wing rib 

numbers 8 and 9, and corrective actions 

if necessary. Corrective actions include 

making an insurance cut of the keyway 

of the fuel tank access door cutout on 

the left and right wings; contacting 

Boeing for repair instructions and doing 

the repair; and changing the profile of 

the keyway of the fuel tank access door 

cutout on the left and right wings 

including doing a related investigative 

action. The related investigative action 

is an HFEC inspection of the machined 

areas for cracks. 

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 

discussed under ‘‘Differences between 

the Proposed AD and Service Bulletin.’’ 

Differences Between the Proposed AD 

and Service Bulletin 

Boeing Alert Service Bulletin 777– 

57A0069, dated November 5, 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. 

Other Rulemaking 

The lower wing skins on The Boeing 

Company Model 737–900ER airplanes 

have fuel tank access door cutouts with 

the same configuration as those of the 

affected fuel tank access door cutouts on 

Model 777–200LR and 777–300ER 

airplanes. Therefore, Model 737–900ER 

airplanes may be subject to the 

identified unsafe condition. We are 

considering similar rulemaking related 

to the identified unsafe condition for 

certain Model 737–900ER airplanes. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 16 airplanes of U.S. 

registry. We also estimate that it would 

take 2 work-hours per product to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this proposed AD to the U.S. 

operators to be $2,720, or $170 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: 

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– 

2010–0280; Directorate Identifier 2009– 

NM–259–AD. 

Comments Due Date 

(a) We must receive comments by May 17, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 777–200LR and –300ER 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

777–57A0069, dated November 5, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Unsafe Condition 

(e) This AD results from reports of cracks 

emanating from the keyway of the fuel tank 

access door cutout of the lower wing skin 

between wing rib numbers 8 and 9. The 

Federal Aviation Administration is issuing 

this AD to prevent loss of the lower wing 

skin load path, which could cause 

catastrophic structural failure of the wing. 

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. 

Inspection 

(g) At the applicable time specified in 

paragraphs (g)(1) and (g)(2) of this AD, do a 

high frequency eddy current (HFEC) 

inspection for cracking of the keyway of the 

fuel tank access door cutout on the left and 

right wings between wing rib numbers 8 

(wing station 387) and 9 (wing station 414.5), 

and do all applicable corrective actions 

including applicable related investigative 

action (an HFEC inspection for cracking of 

machined areas), in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–57A0069, dated 

November 5, 2009, except as required by 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Federal Register / Vol. 75, No. 63 / Friday, April 2, 2010 / Proposed Rules 16685 

paragraph (h) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. 

(1) For Group 1, Configuration 1 airplanes, 

as identified in Boeing Alert Service Bulletin 

777–57A0069, dated November 5, 2009: 

Before the accumulation of 3,500 total flight 

cycles, or within 500 flight cycles after the 

effective date of this AD, whichever occurs 

later. 

(2) For Group 1, Configuration 2 airplanes 

and Group 2 airplanes, as identified in 

Boeing Alert Service Bulletin 777–57A0069, 

dated November 5, 2009, on which a crack 

was found in the cutout keyway when the 

cutout keyway was changed: Within 1,125 

days after the effective date of this AD. 

Note 1: For Group 1, Configuration 2 

airplanes and Group 2 airplanes, as identified 

in Boeing Alert Service Bulletin 777– 

57A0069, dated November 5, 2009, on which 

no crack was found in the cutout keyway 

when the cutout keyway was changed: No 

further action is required by this AD. 

Exceptions to Service Bulletin 

(h) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 777–57A0069, dated 

November 5, 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 (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: 

Duong Tran, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle ACO, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6452; fax 

(425) 917–6590. Or, e-mail information to 9- 

ANM-Seattle-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 March 

25, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–7458 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0281; Directorate 

Identifier 2009–NM–184–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300–600 and A310 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated 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: Surface defects were 

visually detected on the rudder of one 

Airbus A319 and one A321 in-service 

aeroplane. Investigation has determined 

that the defects reported on both 

rudders corresponded to areas that had 

been reworked in production. The 

investigation confirmed that the defects 

were the result of de-bonding between 

the skin and honeycomb core. Such 

reworks were also performed on some 

rudders fitted on A310 and A300–600 

aeroplanes. An extended de-bonding, if 

not detected and corrected, may degrade 

the structural integrity of the rudder. 

The loss of the rudder leads to 

degradation of the handling qualities 

and reduces the controllability of the 

aeroplane. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by May 17, 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 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.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 Operations office 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 Operations 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

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–2010–0281; Directorate Identifier 

2009–NM–184–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 based on those comments. 

We have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1