48620 Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules 

this proposed AD. See the AD docket to 

examine the economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend part 

39 of the Federal Aviation Regulations 

(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. Section 39.13 is amended by 

adding a new airworthiness directive to 

read as follows: 

Eurocopter France: Docket No. FAA–2010– 

0781; Directorate Identifier 2007–SW– 

49–AD. 

Applicability: Model AS–365N2, AS 365 

N3, and SA–365N1 helicopters, with an 

aluminum tail rotor (T/R) blade pitch control 

shaft, part number (P/N) 365A33.6161.20 or 

P/N 365A33.6161.21, installed, certificated in 

any category. 

Compliance: Required within 100 hours 

time-in-service, unless accomplished 

previously. 

To prevent failure of the T/R blade pitch 

control shaft, loss of T/R control, and 

subsequent loss of control of the helicopter, 

accomplish the following: 

(a) Remove the aluminum T/R blade pitch 

control shaft, P/N 365A33.6161.20 or P/N 

365A33.6161.21, and replace it with a steel 

T/R blade pitch control shaft, P/N 

365A33.6214.20, in accordance with the 

Accomplishment Instructions, Operational 

Procedure, paragraphs 2.B.1. through 2.B.3., 

of Eurocopter Alert Service Bulletin No. 

01.00.59, dated June 21, 2007. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, Rotorcraft Directorate, 

FAA, ATTN: Jim Grigg, Aviation Safety 

Engineer, 2601 Meacham Blvd., Fort Worth, 

Texas 76137, telephone (817) 222–5126, fax 

(817) 222–5961. 

(c) The Joint Aircraft System/Component 

(JASC) Code is 6500: Tail Rotor Drive 

System. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency AD No. 

2007–0220, dated August 13, 2007. 

Issued in Fort Worth, Texas, on August 2, 

2010. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19823 Filed 8–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0761; Directorate 

Identifier 2010–NM–069–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 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 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. This 

proposed AD would require installing 

two warning level indicator lights on 

the P2–2 center instrument panel in the 

flight compartment for certain airplanes. 

For a certain other airplane, this 

proposed AD would require activating 

the cabin altitude warning and takeoff 

configuration warning lights. For all 

airplanes, this proposed AD also would 

require revising the airplane flight 

manual to remove certain requirements 

included by previous AD actions, to 

require new pressure altitude 

limitations for certain airplanes, and to 

advise the flightcrew of the following 

changes: revised emergency procedures 

to use when a cabin altitude warning or 

rapid depressurization occurs, and 

revised cabin pressurization procedures 

for normal operations. This proposed 

AD results from a design change in the 

cabin altitude warning system that 

would address the identified unsafe 

condition. We are proposing this AD to 

prevent failure of the flightcrew to 

recognize and react to a valid cabin 

altitude warning horn, which could 

result in incapacitation of the flightcrew 

due to hypoxia (lack of oxygen in body), 

and consequent loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by September 27, 

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. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules 48621 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey W. Palmer, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6472; 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–2010–0761; Directorate Identifier 

2010–NM–069–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 

The Model 737 cabin altitude warning 

is an intermittent horn that sounds 

when cabin altitude exceeds 10,000 feet. 

The same intermittent warning horn 

sound is utilized by the takeoff 

configuration warning system (TCWS) 

to warn of unsafe airplane configuration 

for takeoff. The TCWS warning 

functionality is inhibited by air/ground 

logic when the airplane is in flight. 

However, the Model 737 cabin altitude 

warning system design does not 

currently incorporate a dedicated means 

of positively identifying the warning 

horn as a cabin altitude warning or a 

takeoff configuration warning. There are 

approximately 25 known instances 

where flightcrews have misinterpreted a 

valid cabin altitude warning as a takeoff 

configuration warning. 

Failure of the flightcrew to recognize 

and react to a valid cabin altitude 

warning horn could result in 

incapacitation of the flightcrew due to 

hypoxia (lack of oxygen in body), and 

consequent loss of control of the 

airplane. To address this unsafe 

condition, we issued the following ADs. 

On November 7, 2003, we issued 

related AD 2003–03–15 R1, Amendment 

39–13366 (68 FR 64802, November 17, 

2003), for various The Boeing Company 

and McDonnell Douglas Corporation 

transport category airplanes. That AD 

requires revising the airplane flight 

manual (AFM) to advise the flightcrew 

to don oxygen masks as a first and 

immediate step when the cabin altitude 

warning occurs. We issued that AD to 

prevent incapacitation of the flightcrew 

due to lack of oxygen, which could 

result in loss of control of the airplane. 

On June 15, 2006, we issued related 

AD 2006–13–13, Amendment 39–14666 

(71 FR 35781, June 22, 2006). (A 

correction of that AD was published in 

the Federal Register on July 3, 2006 (71 

FR 37980).) That AD applies to all 

Model 737 airplanes. That AD requires 

revising the AFM to advise the 

flightcrew of improved procedures for 

pre-flight setup of the cabin 

pressurization system, as well as 

improved procedures for interpreting 

and responding to the cabin altitude/ 

configuration warning horn. That AD 

resulted from reports that airplanes had 

failed to pressurize, and that the 

flightcrews failed to react properly to 

the cabin altitude warning horn. We 

issued that AD to prevent failure of the 

airplane to pressurize and subsequent 

failure of the flightcrew to recognize and 

react to a valid cabin altitude warning 

horn, which could result in 

incapacitation of the flightcrew due to 

hypoxia (lack of oxygen in body) and 

consequent loss of airplane control. 

On October 24, 2008, we issued 

related AD 2008–23–07, Amendment 

39–15728 (73 FR 66512, November 10, 

2008), for all Model 737 airplanes. That 

AD requires revising the AFM to 

include a new flightcrew briefing that 

must be done before the first flight of 

the day and following any change in 

flightcrew members, and to advise the 

flightcrew of this additional briefing. 

That AD resulted from continuing 

reports that flightcrews have failed to 

recognize and react properly to the 

cabin altitude warning horn. We issued 

that AD to prevent failure of the 

flightcrew to recognize and react 

properly to a valid cabin altitude 

warning horn, which could result in 

incapacitation of the flightcrew due to 

hypoxia (lack of oxygen in body) and 

consequent loss of airplane control. 

The preambles to AD 2006–13–13 and 

AD 2008–23–07 explain that the 

revisions to the AFM required by those 

ADs are considered to be interim action. 

The manufacturer had advised us that it 

was developing a design change in the 

cabin altitude warning system that 

would address the identified unsafe 

condition(s), and that once this design 

change was developed, approved, and 

available, the FAA might consider 

additional rulemaking. The 

manufacturer now has developed such a 

modification, and we have determined 

that further rulemaking is necessary; 

this proposed AD follows from that 

determination. We can better ensure 

long-term continued operational safety 

by modifications or design changes to 

remove the source of the problem, rather 

than by AFM revisions alone. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 737–31A1325, dated 

January 11, 2010 (for Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes). This service bulletin 

describes procedures for installing two 

warning level indicator lights on the 

P2–2 center instrument panel in the 

flight compartment. This installation 

includes changing three wire bundles. 

We have also reviewed Boeing Alert 

Service Bulletin 737–31A1398, dated 

January 7, 2010 (for Model 737–400 

series airplane, variable number 

PW234). This service bulletin describes 

procedures for activating the cabin 

altitude warning and takeoff 

configuration warning lights. The 

activation includes changing the wiring 

in the W066 wire bundle and removing 

the INOP markers from the cabin 

altitude warning and takeoff 

configuration warning lights. 

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. The proposed AD 

would also require revising the AFM to 

remove certain requirements included 

by previous AD actions, to require new 

pressure altitude limitations for certain 

airplanes, and to advise the flightcrew 

of the following changes: revised 

emergency procedures to use when a 

cabin altitude warning or rapid 

depressurization occurs, and revised 

cabin pressurization procedures for 

normal operations. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 741 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
48622 Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules 

TABLE—ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per 

product 

Number 

of U.S.- 

registered 

airplanes 

Fleet cost 

Installation of warning indicator lights ...... 20 $85 $2,738 $4,438 740 $3,284,120 

Activation of the cabin altitude warning 

system/takeoff configuration warning 

lights ..................................................... 1 85 0 85 1 85 

AFM revision ............................................ 1 85 0 85 741 62,985 

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– 

2010–0761; Directorate Identifier 2010– 

NM–069–AD. 

Comments Due Date 

(a) We must receive comments by 

September 27, 2010. 

Affected ADs 

(b) This AD affects the ADs identified in 

paragraphs (b)(1), (b)(2), and (b)(3) of this AD. 

This AD does not supersede the requirements 

of these ADs. 

(1) AD 2008–23–07, Amendment 39– 

15728. 

(2) AD 2006–13–13, Amendment 39– 

14666. 

(3) AD 2003–03–15 R1, Amendment 39– 

13366. 

Applicability 

(c) This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) The Boeing Company Model 737–100, 

–200, –200C, –300, –400, and –500 series 

airplanes identified in Boeing Alert Service 

Bulletin 737–31A1325, dated January 11, 

2010. 

(2) The Boeing Company Model 737–400 

series airplanes identified in Boeing Alert 

Service Bulletin 737–31A1398, dated January 

7, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 31: Instruments. 

Unsafe Condition 

(e) This AD results from a design change 

in the cabin altitude warning system that 

would address the identified unsafe 

condition. The Federal Aviation 

Administration is issuing this AD to prevent 

failure of the flightcrew to recognize and 

react properly to a valid cabin altitude 

warning horn, which could result in 

incapacitation of the flightcrew due to 

hypoxia (lack of oxygen in body) and 

consequent loss of airplane control. 

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. 

Installation of Warning Indicator Lights 

(g) For airplanes identified in Boeing Alert 

Service Bulletin 737–31A1325, dated January 

11, 2010: Within 36 months after the effective 

date of this AD, install two warning level 

indicator lights on the P2–2 center 

instrument panel in the flight compartment, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–31A1325, dated January 11, 2010. 

Activation of Warning Indicator Lights 

(h) For airplanes identified in Boeing Alert 

Service Bulletin 737–31A1398, dated January 

7, 2010: Within 36 months after the effective 

date of this AD, activate the cabin altitude 

warning and takeoff configuration warning 

lights, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–31A1398, dated January 

7, 2010. 

Airplane Flight Manual (AFM) Revisions 

(i) Before further flight after doing the 

installation or activation of the warning 

lights required by paragraph (g) or (h) of this 

AD, do the actions specified in paragraphs 

(i)(1), (i)(2), and (i)(3) of this AD. 

(1) Revise the Limitations Section of the 

applicable Boeing 737 AFM by doing the 

actions specified in paragraphs (i)(1)(i) and 

(i)(1)(ii) of this AD. 

(i) Delete the ‘‘CABIN ALTITUDE 

WARNING TAKEOFF BRIEFING’’ added by 

AD 2008–23–07. 

(ii) Add the following statement. This may 

be done by inserting a copy of this AD into 

the applicable AFM. 

‘‘For airplanes approved for maximum 

takeoff and landing altitudes above 8,400 feet 

pressure altitude, change the limitation for 

Maximum Takeoff and Landing pressure 

altitude as follows: With the CABIN 

ALTITUDE and TAKEOFF CONFIG lights 

installed and operative on those airplanes 

without the High Altitude Landing switch 

installed, maximum takeoff and landing 

altitude is limited to 9,000 feet pressure 

altitude.’’ 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules 48623 

(2) Revise the Emergency Procedures 

Section of the applicable Boeing 737 AFM by 

doing the actions specified in paragraphs 

(i)(2)(i), (i)(2)(ii), (i)(2)(iii), and (i)(2)(iv) of 

this AD. 

(i) Delete the procedure ‘‘WARNING 

HORN—CABIN ALTITUDE OR 

CONFIGURATION’’ added by AD 2006–13– 

13. 

(ii) Delete the procedure entitled ‘‘CABIN 

ALTITUDE WARNING OR RAPID 

DEPRESSURIZATION’’ added by AD 2006– 

13–13. 

(iii) If the procedure entitled ‘‘CABIN 

ALTITUDE (Airplanes with the CABIN 

ALTITUDE lights installed)’’ is currently 

contained in the applicable Boeing 737 AFM, 

delete the procedure entitled ‘‘CABIN 

ALTITUDE (Airplanes with the CABIN 

ALTITUDE lights installed).’’ 

(iv) Add the following statement. This may 

be done by inserting a copy of this AD into 

the applicable AFM. 

‘‘CABIN ALTITUDE WARNING OR RAPID 

DEPRESSURIZATION (required by this ad) 

Condition: The CABIN ALTITUDE warning 

light illuminates or the intermittent warning 

horn sounds in flight above 10,000 ft MSL. 

RECALL: 

Oxygen Masks and Regulators.On, 100% 

Crew Communications ....... Establish 

REFERENCE: 

Pressurization Mode Selector.Manual 

Outflow Valve Switch ........ Close 

Passenger Oxygen (If Required).On 

Descent (If Required) .......... Initiate 

(3) Revise the Normal Procedures Section 

of the applicable Boeing 737 AFM by doing 

the actions specified in paragraphs (i)(3)(i) 

and (i)(3)(ii) of this AD. 

(i) Delete the ‘‘CABIN ALTITUDE 

WARNING TAKEOFF BRIEFING’’ procedure 

added by AD 2008–23–07. 

(ii) Add the following statement. This may 

be done by inserting a copy of this AD into 

the applicable AFM. 

‘‘For normal operations, the pressurization 

mode selector should be in AUTO prior to 

takeoff. (Required by this AD)’’ 

Note 1: When statements identical to those 

specified in paragraphs (i)(1)(ii), (i)(2)(iv), 

and (i)(3)(ii) of this AD have been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copies of this AD may be 

removed from the AFM. 

Terminating Action for Affected ADs 

(j) Accomplishment of the requirements of 

this AD terminates the specified 

requirements of the ADs identified in 

paragraphs (j)(1), (j)(2), and (j)(3) of this AD, 

for only the airplanes identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) AD 2008–23–07: All requirements of 

that AD. 

(2) AD 2006–13–13: All requirements of 

that AD. 

(3) AD 2003–03–15 R1: The requirements 

specified in paragraph (a), Table 2, and 

Figures 2 and 3 of that AD. 

Special Flight Permit 

(k) Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(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: 

Jeffrey W. Palmer, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6472; fax 

(425) 917–6590. Information may be e-mailed 

to: 9-ANM-Seattle-ACO-AMOCRequests@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. 

Issued in Renton, Washington, on July 28, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19834 Filed 8–10–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0796; Directorate 

Identifier 2010–NM–007–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767–300 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 767–300 series airplanes. This 

proposed AD would require repetitive 

inspections for cracks in the fuselage 

skin and backup structure at the lower 

very high frequency (VHF) antenna 

cutout at station 1197 + 99 between 

stringers 39L and 39R, and corrective 

actions if necessary. Certain repairs 

would terminate certain inspection 

requirements. This proposed AD results 

from reports of cracking found in the 

section 46 fuselage lower skin around 

the periphery of the VHF antenna 

baseplate at station 1197 + 99. We are 

proposing this AD to detect and correct 

fatigue cracks in the fuselage skin and 

internal backup structure, which could 

result in rapid decompression of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by September 27, 

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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 


jlentini on DSKJ8SOYB1PROD with PROPOSALS